Russian Nuclear Forces

FAS Military Affairs Network

Russian Nuclear Forces

R-7 - SS-6 SAPWOOD The R-7/SS-6 Sapwood, the first Soviet intercontinental ballistic missile developed and programmed for operational deployment in the USSR, is a one and one-half stage, cryogenic liquid-propellant missile. According to Western estimates it was capable of delivering a 9000 lb reentry vehicle to a maximum operational range of 6500 nm with a CEP of approximately 2 nm. The R-7 missile became the first Soviet intercontinental ballistic missile. It was based on plans laid out in the governmental order from February 13, 1953 to develop a two-stage ballistic missile with a range of 7000-8000 km. The original design plans provided for a total weight of the nose cone plus warhead of 3 tons. However, soon after the first tests in October 1953 were carried out, the design was substantially changed. The total weight of the nose cone was increased to carry a thermonuclear warhead of 3 tons. To preserve the previous maximum range it was necessary to redesign the missile completely since the launch weight was increased from 170 up to 280 ton. The development of this two-stage ballistic missile was approved on May 20, 1954. The R-7 missile employs a unique parallel division of stages, consisting of one central sustainer and four strap-on boosters, all of which were started simultaneously at liftoff. The strap-on boosters formed the first stage, and the central sustainer constituted the second stage. This tandem structure allowed the start and control of all engines at normal atmospheric pressure [the Atlas first-generation American ICBM employed a similar principle, while using common propellant tanks for both booster and sustainer engines]. Each of the stages featured a four-chamber open-cycle rocket engine using liquid oxygen and kerosene. Flight control was achieved by vernier engines located on the strapon boosters and the core sustainer. Aerodynamic fins located on the aft bay of the strap-ons also provided for flight control. The missile had a combined command structure consisting of both an independent autonomous system and a radio command system. The independent autonomous system provided attitude control for the missile with respect to the vehicle's center of mass and motion on the planned trajectory. It also controlled the synchronous draining of the propellant tanks in all units of the first stage. The system of radio control carried out inflight trajectory corrections and provided for an increase of delivery accuracy. The flight tests of the 8K71 missile began on 15 May 1957. The spectacular launch of the first Sputnik satellite in October 1957 revealed a rocket with a thrust far in excess of anything the United States could then produce. The Soviet feat caused the United States to review its missile programs in order to narrow the rocket-booster gap. To sustain morale, several small American satellites using the Jupiter and Vanguard boosters were launched in 1958, but it would take considerable time to construct engines equaling those already developed by the Russians.

The results of the first six tested R-7 (two of which were used in a modified version to place the first two Sputnik satellites into orbit) led to a modification of the nose cone and its mode of separation. During the first launches the nose cone collided after its' separation with a missile body and was destroyed during atmospheric reentry. Between 29 March and 10 July 1958 the new design with a modified nose cone was successfully tested and between 24 1958 and 27 November 1959 16 flight tests were conducted to assure the reliability of the design. Following the completion of tests in December 1959 the first launch complexes were put on an alert, and on 20 January 1960 deployment of the R-7 missile started.. During the test phase of the R-7 missile, on 02 July 1958, a ministerial decree was issued for the development of an improved ICBM based on the R-7 design. The new R-7A (8K74) included a modernized lighter warhead, more powerful engines and an increased propellant volume. Thus maximum range was increased from 8000 up to 12000 km. A newly developed gyroscopic inertial navigation system, replacing the previous radiocommand control system, improved the missile's accuracy. Flight tests of this variant were conducted from December 1959 through July 1960. In January 1960 for the first time a successful test of a long-range missile carried out with successful delivery of the nose cone into the Pacific Ocean. Eight missile launches were carried out of which seven were successful. In early 1960 theR-7A missile was put on active alert. The 8K71 and 8K74 missiles were put on alert at test facilities at the Baikonur cosmodrome and at "Angara" in the Arkhangelsk area (subsequently known as Plesetsk). They were deployed at five sites that consisted of six launch facilities in total. The SS-6 ICBM system has had limited deployment in fixed soft sites in northwestern USSR. The system reaction time in the normal readiness condition was approximately ten hours. Because of the cryogenic oxidizer, the allowable hold time in the maximum alert condition (reaction time equals five to ten minutes) was approximately one hour. By mid1968 the SS-6 ICBM had been phased out of the operational inventory. Use of the SS-6 is now restricted to space applications.

Specifications DIA

SS-6

SS-6

NATO

Sapwood

Sapwood

Service

R-7

R-7A, R-7M

OKB/Industry

8K71

8K74/8K710

Design

OKB-1 (Acad. S. P. Korolev),

OKB-1 (Acad. S. P. Korolev),

NII-88

NII-88

Bilateral

Bureaus

Approved

5/20/1954

7/2/1958

Years of R&D

1954 -1959

1954 -1959

Engineering and Testing

1957 - 59

1959 - 60

First Flight Test

5/15/57

12/23/59

IOC

1960

1960

Deployment Date

1/20/1960

9/12/1960

Type of Warhead

Single

Single

Warheads

1

1

Yield (Mt)

3-5

3-5

Payload (t)

5.3 -5.5

3.0 -3.7 or 2.2

Total length (m)

34.22 - 33 31.07

31.070

Total length w/o warhead (m)

28

28

Missile Diameter (m)

2.95 core sustainer Total = 10.3

2.95 core sustainer Total = 10.3

Launch Weight (t)

Total = 280 283

274.5 Total = 276

Fuel Weight (t)

Total = 253

Total = 250

Range (km)

8,000-8,5008,800

9,000-9,500 or 12,00014,000

CEP (m) (Russian Sources)

2,500 -5,000

5,000

3,700

3,000 -3,700

CEP (m) (Western Sources) Number of Stages Canister length (m) Canister length w/o Front meters (m) Canister diameter (m) Booster guidance system

2 N/A N/A

N/A Autonomous inertial plus radio control

Length (m) Body diameter (m) Fueled weight (t)

1st stage four Strap-on's 19.2 2.68 tapered cone 4 x 42.5=170.0 4 x 39.2=156.8

Dry weight (t)

2nd stage Sustainer Core 28.0 2.15 -2.95 hammerhead shape 1st. 30.08+2nd. 79.92=110 total -5.5 warhead=104.5 or 5.5 + core 93.355 +11.145=110-5.5=104.5 or 95.400 + Payload Mass ~22 total + Payload Mass or 6.525 + Payload Mass

~22 -24.5 total + Payload Mass or 3.784 x 4=15.1360 Engine Designation Four RD-107 's RD-108 (8D75) (8D74) Design bureau Acad. V. P. Glushko Acad. V. P. Glushko OKB-456 OKB-456 Years of R&D 1954-1957 1954-57 Propellants Liquid Liquid Fuel Kerosene, (T-1) Kerosene, (T-1) Oxidizer Liquid Oxygen Liquid Oxygen Burning time (sec.) 120-118 + 10 start 310 - 320 + 10 start time Verniers Thrust Sea 8 x ~ 3.9 = 31.2 4 x ~3.9 = 15.6 Vac. Total Level/Vacuum (Tonnes) Vac. Total Main engines Thrust Sea 4 x 83.77=334.8 / 4 1 x 75.90 / 90-93- 94.1-96 Vac. Level/Vacuum (Tonnes) x 99-102=408 Total thrust launch 403.4/9 - 410.7 1st. shutdown thrust 497 (Tonnes) Specific Impulse (sec.) Basing Mode Launching Mode Deployed boosters Test Boosters Warheads Deployed Deployment Sites Training Launchers Space Booster Variant

257-259 / 305-308 248 / 305-309-315-316 Ground Based Hot launch 0 0 5 launch pads -3 Plesetsk, 2 Baikonur Yes SL-1/A, Sputnik SL-3, A-1, Lunik, Vostok SL-4/A-2, Soyuz

SL-6/A-2-e, Molniya SL-4/ A-2 / Soyuz-2

Historical Review - Western Estimates First system flight test

January 30, 1958

Operational training flights began

October 1959

Initial operational capability

Early 1960

Deployed missiles retrofitted with 9000 lb reentry vehicle Late

1960-Early 1961

Maximum operational deployment (four missiles) reached

1962

Last missile test firing

1966

Phase-out completed

1968

R-9 - SS-8 SASIN The R-9/SS-8 Sasin intercontinental ballistic missile is a two-stage, tandem, cryogenic liquid-propellant missile. According to Western assessements it was capable of delivering a 3500 lb reentry vehicle to a maximum operational range of 6000 nm with a CEP of about 1.0 nm. The R-9 was the last Soviet ICBM using cryogenic propellant. This two-stage ICBM had sequential stages that were connected by a truss. The first stage was equipped with a closed cycle engine with four combustion chambers that used a liquid cryogenic propellant developed by NPO Energomash Imeni V.P. Glushko (OKB-456). For the second stage an open-cycle four combustion chamber engine developed by KB Khimavtomakiki (OKB-154) was employed. The flight control during the first stage flight used a new system of gimbaled combustion chambers of the sustainer stage. The flight control of the second stage was provided through control nozzles using exhaust gas from the turbopump unit. As the separation of the first stage occurred at an altitude where the influence of aerodynamic forces was still essential, the application of stabilizers was necessary. To maintain aerodynamic stability during the first seconds of flight of the second stage four aerodynamic fins were placed on its aft bay. They opened after the separation from the first stage. Several seconds afterwards the aft bay of the second stage was also separated. The R-9 was the first Soviet ICBM to incorporate pressurization of the main propellant in the fuel tanks, which obviated the need for special bottles with a pressuring gas. The original missile had a combined command structure with a radio engineering channels. The inertial system provided flight control during almost all the active trajectory except for the last ten seconds which were controlled by a radio-correctionsystem. Subsequently however, the use of a radio engineering channel was discarded, and the command system of the missile allowed to execute autonomous monitoring of missile flight parameters. . The missile could be equipped with two different nose cones according to different payloads: a light nose cone capable of containing a warhead with a yield of 1.7 MT and a heavier one with a warhead of 2.09 MT. The original missile was intended to be surface launched, but in 1960 the development of a silo-launched version was begun. In total three different launch complexes were developed: Two ground-launch complexes (Desna-N/Valley) and a silo-launch complex ("Desna-V").were developed. Two launchers, a command center, missile and propellant depots and radio command guidance system formed part of the "Desna-N" launch complex. The "Valley" complex had a similar structure, but was equipped with an automatic system that could carry out a launch within 20 minutes. Within this time the missile could be transported from the depot to the launch-complex, installed, fueled prepared and targeted. The minimal interval for the next missile firing lasted from nine minutes for the next launcher up to 2.5 hours for a repeat launch from one pad.

The silo-launch complex "Desna-V" consists of three silos, located in a straight line close to each other an underground command center, underground depots of propellant components and compressed gases and a radio control complex. The silos were 36 m deep with a minimum diameter of 7.8 m and a canister diameter of 5.5 m. For the first time a hot launch of a missile from the silo was accomplished through the use of oxygen that was previously cooled to –186C. The missile could be held in readiness up to 1 year, and in the fueled condition up to 24 hours. The proposals of the chief designers for the development of a new ICBM with an oxygen-kerosene propellant and an initial weight of about 100 tons (i.e. almost three times less than that of the R-7) were submitted to the government in April 1958. The order of the ministerial council to build the R-9 missile was issued on 13 May 1959 and the designated head developer was S. P. Korolev's OKB-1. The flight tests of a missile were conducted at the Baikonur cosmodrome. They were first carried out on 09 April 1961 at a modified launch complex, then proceeded on an experimental ground-launch launch complex "Desna-N" until 14 February 1963. The test of the ground-launched version were finished on the "Valley" battle complexes and tests of the silo-launched version were finished on 02 February 1964. Due to serious engine problems 15 of the first 32 launches terminated in emergencies. In total 54 missile tests were carried out. The SS-8 system was deployed at both soft and hard sites.On July 21, 1965 the deployment of SS-8 missiles began. They were capable of ground and silo-launch from the "Valley" and "Desna-V" launch complexes. The "Desna-N" complex was not deployed, since launch preparation took at least 2 hours. According to Western assessments, the reaction time for soft systems in the normal readiness condition was one to three hours, and for hard systems from 30 to 45 minutes. Because of the cryogenic oxidizer, the allowable hold time in the highest degree of pre-launch alert (reaction time equals five to ten minutes) was assessed at about one hour. According to Western intelligence, soft-site initial operational capability was achieved in November, 1963, and hard-site IOC followed in April 1964. In fact, Russian sources suggest that the first missile regiments equipped with missiles R-9A, were put on alert in December 1964 (4 regiments with surface-based missiles and one regiment with missiles of silo basing). The maximum operational launcher inventory of 23 was reached in 1963 and 1964. Soft-site phase out began in 1971, and in 1976 the R-9A missiles were phased out entirely.

Specifications DIA

SS-8

SS-8

SS-8

NATO

Sasin

Sasin

Sasin

R-9,

R-9A,

R-9B

Bilateral Service

OKB/Industry

8K75,

8K75A,

8K76

Design Bureau

OKB -1 (Acad. S. P. Korolev)

OKB -1 (Acad. S. P. Korolev)

OKB -1 (Acad. S. P. Korolev)

Approved

5/13/1959

Years of R&D Engineering and 1959 - 1961 Testing 1965 First Flight Test

4/9/61

IOC

Dec. 14 /15,1964,

Deployment Date

02-22-63

7/21/1965

Type of Warhead

Single

Single

Single

Warheads

1

1

1

Yield (Mt)

1.65, 2.1-2.5

1.65 - 3.0 -5.0

Payload (t)

1.7- 2.2,

1.1,-1.65 -2.1

Total length (m) 24.18,

24.227

Total length w/o warhead (m) Missile Diameter (m)

2.68

2.68

2.68

Launch Weight (t)

81.0 - 82.0

81.0 - 82.0

81.0 - 82.0

Fuel Weight (t)

1st. 81.0 - 25.4 = 55.6, 2nd.18.2 15.3= 2.9 ? Total (71.1)

1st. 81.0 - 25.4 = 55.6, 2nd.18.2 15.3= 2.9 ? Total (71.1)

1st. 81.0 - 25.4 = 55.6, 2nd.18.2 15.3= 2.9 ? Total (71.1)

Range (km)

12,000 -13,000

16,000 -12,500

CEP (m) (Russian Sources)

3,000 - 3,500

CEP (m) Western Sources)

1,800 - 2,000

Number of Stages Canister length (m)

2 N/A

Canister length w/o

N/A

Front meters (m) Canister diameter (m) N/A Booster guidance system Radio/Inertial autonomous st 1 stage 2nd stage Length (m) 14.79 9.40 Body diameter (m) 2.68 2.68 Fueled weight (t) (71.1) total Dry weight (t) 7.2 3.1 9.3 - 9.9 total Engine Designation RD-111, 8D716 RD-0106 (RO-9) 8D715 Design Bureau Glushko OKB-456 Kosberg OKB-154 Years of R&D 1959-1962 1959-1961 Propellants Liquid Liquid Fuel T-1, Kerosene T-1, Kerosene Oxidizer Liquid Oxygen Liquid Oxygen Burning time (sec.) 104-105 105 & 108 Verniers Thrust Sea 141.24 -143.3 / 30.5 -30.62 -31.0 - 31.5 Vacuum Level/Vacuum (Tonnes) 162.8 -163 -166 Specific Impulse Sea 270.4 - 274 -275 / 330 Vacuum Level/vacuum (sec.) 310 -317 Basing Mode Ground and silo Hardness Launching Technique Hot launch Deployed boosters 0 Test Boosters Warheads Deployed 0 Training Launchers Space Booster Variant N/A Deployment Sites START Kozel=sk

Locale US-Designation Kozelsk

GR-1 / SS-X-10 SCRAG The 1961 Global Rocket 1 (GR-1) requirement chartered a competition for the development of a Fractional Orbital Bombardment System. Yangel offered the R-36. Korolev proposed the 8K713, which was cancelled in 1964 prior to flight testing due to engine delays. Chelomei proposed the UR-200, which was cancelled following the October 1964 ouster of downfall of Khrushchev, who had been Chelomey's political patron. The GR-1 (8K713) Fractional Orbital Bombardment System [FOBS] intended to overcome the ABM-system that the USA was about to deploy in order to protect selective ICBM deployment sites from a Soviet nuclear strike. The GR-1 orbital missile was supposed to be capable of placing a warhead in a low earth orbit of 150 km, braking during its trajectory and targeting the warhead on the earth surface. Its target accuracy was 5 km along range and 3 km on azimuth deviation at unlimited range. The three-stage liquid cryogenic propellant missile had a launch weight of 117 tons and carried a single warhead with a yield of 2.2 MT. Since the R-9A was reaching the end of their service, it was planned that the GR-1 missile would use the same launching sites as the R-9A missile. The design of a missile that could serve both as a ballistic and an orbital missile began at Korolev's OKB-1 in 1961. The development of the GR-1 missile was officially authorized by the Ministerial Council on 24 September 1962. Further development of the GR-1 missile was halted in 1964 in preference of the orbital R-36 missile (8K69). Although the GR-1 missile had not been flight tested, it was paraded in Red Square and did receive the US-designation SS-X-10 SCRAG. It was displayed in a 1965 parade, where it was described as a sister to the manned spacecraft launch vehicles. This missile was correctly identified as being a FOBS configuration, although open sources at the time evidently assumed that the FOBS parading in Red Square and the FOBS undergoing flight tests were the same system. In fact, the initial FOBS flight tests were conducted by the competing UR-200 missile, and subsequent orgital tests by a variant of the R-36. It is unclear when US intelligence understood that the parade missile and the test missile were two different systems.

Specifications DIA NATO

Scrag

Bilateral Service

GR-1

OKB/Industry

8K713

Design Bureau

OKB-1 (Acad. S. P. Korolev)

Approved

9/24/1962

Years of R&D Engineering and Testing First Flight Test

10/20/64 One to eight flights suggested. All missed through 1967 by U.S. Intelligence.

IOC

Canceled 11/19/68

Deployment Date

Not deployed

Type of Warhead

Single/Orbital

Warheads

1

Yield

2.2

Payload

2.5

Total length

35.305

Total length w/o warhead

33.9

Missile Diameter (m)

2.85

Launch Weight (t)

116

Fuel Weight (t)

1st 116 -38.94, = 77.06 2nd 30.76 -10.24,= 20.52 3rd 7.44 -3.84 = 3.6 Total 101.18

Dry weight total (t)

14.82 - 2.5 payload mass = 12.32

Range (km)

12,000/40,000

CEP (m) (Russian Sources)

5,000/3,000

CEP (m) (Western Sources) Number of Stages Canister length (m) Canister length w/o

3 N/A N/A

front meters (m) Canister diameter (m) Booster guidance system

N/A Inertial autonomous

Length (m) Body diameter (m) Fueled weight (t) Dry weight (t) Engine Designation

Design Bureau

Years of R &D Propellants Liquid Fuel

1st stage 18.0 2.85 77.06 8.18 NK-9 (8D717)

2nd stage 7.7 2.7 20.52 2.8 NK-9V /

3rd stage 6.4 2.35 3.6 1.34 Derivation of the

Acad. N. D. Kuznetsov, OKB-276

(NK-19) Acad. N. D. Kuznetsov, OKB-276

S1.5400, 8D726 Acad. A.M. Isayev,

OKB-2 1959-1965 1959-1965 1962-1965 Liquid Liquid Liquid RG-1, Kerosene RG-1, Kerosene RG-1, Kerosene Oxygen

Oxidizer Oxygen Oxygen Burning time (sec.) Thrust Sea 4 x 36.5=147/ 4 44.6-45-46.1 6.87-8.5 Level/Vacuum (tonnes) x 38=152 Specific Impulse 285 - 327 330 - 341 344 Level/Vacuum (sec.) Basing Mode Silo Hardness Launching Technique Hot Launch Deployed boosters 0 Test Boosters 1-8? Warheads Deployed 0 Deployment Sites 0 Training Launchers 0 Space Booster Variant Yes GR-1

R-16 / SS-7 SADDLER The R-16/SS-7 intercontinental ballistic missile is a two-stage, tandem, storable liquidpropellant missile capable of delivering a single 3500 lb reentry vehicle to a maximum operational range of 7000 nm,or a 4200 lb reentry vehicle to a range of 6000 nm. The SS7 is about 100 feet long and 10 feet in diameter. The missile guidance system was inertial with a CEP estimated by the West at 1.0-1.25 nm. The propulsion system of the first stage consists of three motors with two combustion chambers (similar to those used on the R-14 missile) and a four-chamber control engine. The pivoted combustion chambers of the control engine were placed on an external surface under fairings, which also served as aerodynamic stabilizers. The second stage had a two combustion chamber engine with that had a greater nozzle as the first stage and a four-chamber control engine. Dedicated retrorockets were used to separate the sustainer stages and the warhead. A novel and more reliable autonomous guidance control system that was protected from radio-jamming was designed for this missile. Three versions of the R-16 missile were developed differing with regard to the number and the yield of warheads and the ensuing maximum range. Four variants of the reentry vehicle were detected by Western intelligence during the R&D program. Only the Mod 2 (ballistic coefficient equals 700 lb per sq ft; yield assesed by the West to be 2.0 to 3.5 MT) and the Mod 3 (ballistic coefficient equals 850 lb per sq ft; yield assessed by the West to be 3.0 to 5.0 MT) were deployed extensively. The order to build an intercontinental ballistic missile designated as R-16 (8K64) was approved by the ministerial Council of the USSR on 17 December 1956. The developer was Yangel's OKB-586. Test flights were to be started on 24 October 1960 at the Baikonur cosmodrome. However during preparation of a fueled rocket to resume a delayed launch there was an accidental engine ignition of the second stage. As a consequence of the ensuing explosion and fire about 100 people were killed, including Strategic Rocket Forces Marshal Mitrofan Nedelin. The incident was shrouded in mystery, and was first described in [not entirely correct] detail by James Oberg's books "Red Star in Orbit" and "Uncovering Soviet Disasters." Initially it was thought in the West that the disaster was associated with a failed attempt to launch a probe to Mars, and only subsequently was it understood to be a test of a new ICBM. Flight tests resumed on 02 February 1961, and the SS-7's first successful flight test occurred on 02 April 1961. By late 1961 the first R-16 missile regiment was put on alert, though the system was not believed by Western intelligence to be operational until January 1962. The missile was fired from the surface launch complex "Desna-N", which consisted of two open launchers, a command center and a fuel depot.

In May 1960 the development of a missile designated as R-16U and its corresponding silo launch complex "Desna-V" began. The R-16U was to become the first silo launched ICBM but it also had a surface-launch capability. The launch complex consisted of three silos located in a straight line 60 meters away from each other, along with four underground command centers and fuel depots. The silo launchers had a depth of 45.6 m, a diameter of 8.3 m and a door diameter of 4.64 m. The flight tests of the ground launched R-16U were conducted from 10 October 1961 through February 1962. The flight tests of the silo launched version began in January, 1962. The first surface-launched missile firing was conducted on 13 July1962, and this version was initially deployed on 15 June 1963. The silo launched version became operational on 15 July 1963 (simultaneously with the R-12U and R-14U missiles). The first three ground based R-16 regiments were put on alert on 01 November 1961, while the first regiment with silo based P-16U missiles was put on alert on 05 February 1963. The system was deployed in both soft and hard sites. Between 1961 and 1965 a total of 186 mostly sufrace-based R-16 and R-16U were deployed. The SS-7 reaction time in the normal readiness condition is one to three hours for soft sites and five to fifteen minutes for hard sites. The allowable hold time in the highest alert condition (reaction time equals three to five minutes) is many hours for soft sites and days for hard sites. Maximum operational launcher inventory occurred in 1965 with some phase-out of both soft and hard sites occurring in 1971. Both missiles were phased out in 1976.

Specifications Mod-1

Mod-2

Mod-3

DIA

SS-7

SS-7

SS-7

NATO

Saddler

Saddler

Saddler

Bilateral

R-16

R-16

R-16

Service

R-16(U) 1

R-16(U)1

R-16(U)

OKB/Industry

8K64(U)

8K64(U)

8K64(U)

OKB-586

OKB-586

(Acad. M. K. Yangel)

(Acad. M. K. Yangel)

(Acad. M. K. Yangel)

Approved

12/17/1956

05/30/1960,

04/27/1961

Years of R&D

1956-1961

Engineering and Testing

1961-1962

1961-1963

First Flight Test 10/24/1960

10/10/1961

Design Bureau OKB-586

07/13/1962

failure

11/22/1963

02/02/1961 success IOC

1961

1963

Deployment Date

11/__ /1961

02/05/1963, 6/15/1963 2

Type of Warhead

Single

Single

Single

Warheads

1

1

1

Yield (Mt)

3, 5-6

3, 5-6

3, 5-6

Payload (t)

1.475-1.5

2.175-2.2

2.175-2.2

Total length (m)

32.4 – 30.44/31

30.44/31

34.3

3

3

3

Launch Weight 140.6, 141.2 (t)

146.6

148

Fuel Weight (t) 130

130

130

Range (km)

11,000 -13,000

10,500

Total length w/o warhead (m) Missile Diameter (m)

13,000, 10,500 11,000

CEP (m) (Russian Sources)

2,700

2,700

2,700

CEP (m) (Western Sources)

2,750-2,800

2,750-2,800

2,750-2,800

Basing Mode

Soft site ground based

Silo based

Silo based

Number of Stages Canister length w/o front meters (m)

(12) 2 N/A

Canister diameter (m)

Canister length (m)

Booster guidance system Inertial autonomous 1st stage 2nd stage Length (m) 14.5, 16.8 10.8 ~12.7 Body diameter (m) 3.0 2.4 Fueled weight (t) Total 130.0 Dry weight (t) Total 10.6 Engine Designation Acad. V. P. Glushko, Acad. V. P. Glushko, RD-218 (8D712) RD-219 (8D713) Configuration Cluster of three engines One engine + Yuzhnoy + Yuzhnoy Vernier engine Vernier engine

Design Bureau Years of R&D Propellants Fuel Oxidizer

RD – 68 / RD-851 Acad. V. P. Glushko OKB-456 1958-1961 Liquid Storable UDMH (heptyl) AK-27 I, ,= 73%HNO3 + 27% N204 (NTO), Nitrogen Tetroxide concentrated in Nitric Acid N02 90 28.850 / 38.7518

RD – 69 / RD-852 Acad. V. P. Glushko OKB-456 1958-1961 Liquid Storable UDMH (heptyl) AK-27 I,= 73%HNO3 + 27% N204 (NTO), Nitrogen Tetroxide concentrated in Nitric Acid N02

Burning time (sec.) 125 Verniers Thrust Sea 4.920 - 5.0173 Level/Vacuum (Tonnes) Main engines Thrust 225.886 / 264.8379 90.1 Vacuum Sea Level/Vacuum (Tonnes) Total Thrust Sea 254.736 -255.4/ 95.02 – 95.1173 Vacuum Level/Vacuum (Tonnes) 303.5897 Altitude Specific Impulse Sea 246-247/266 altitude 293 Vacuum Level/Vacuum (sec.) 290 Vacuum Hardness Launching Technique Soft site and silo Deployed boosters 0 Test Boosters Warheads Deployed 0 Training Launchers Space Booster Variant N/A

Deployment Sites START Bershet= Drovyanaya

Locale US-Designation Perm Drovyanaya Itatka Kostroma Kozelsk Gladkaya Verknnyaya Salda

Kostroma Kozel=sk Krasnoyarsk Nizhniy Tagil Novosibirsk Svobodny Teykovo

Svobodny Teykovo Tyumen Yedrovo Olovyannaya Yoshkar Ola Yurya

Vypolzovo Yasnaya Yoshkar Ola Yur=ya

1. The R-16U is almost identical to the R-16b ballistic missile except for its basing mode. It was deployed on above ground soft sites as well as in silos. 2. This was the above ground soft site deployment date for the R-16U. The silo based version of the R-16U was deployed one month later.

Historical Review - Western Estimates Flight testing First successful attempt

April 2, 1961

First Mod 2 reentry vehicle

October 11, 1962

First Mod 3 reentry vehicle

November 22, 1962

First Mod 4 reentry vehicle

August 30, 1963

Initial operational capability Soft sites, Mod 1 reentry vehicle

January 1962

Hard sites December

1962

Mod 2 reentry vehicle

1962

Mod 3 reentry vehicle

1963

Maximum operational launcher inventory

1965

Phase-out began

1971

R-26 / "SS-8 SASIN" The R-26 (8K66) missile was one of the first strategic missiles of the second generation with integrated fuel tanks. The development of this R-26 missile was approved on 23 May 1960 and KB Yuzhnoye (OKB-586) was the leading developer. The flight-design tests were supposed to begin in December 1961, but development of the R-26 was halted by governmental order on 09 July 1962. The reason for the suspension of the development were partly technical and lay partly in design bureau rivalries concerning the development of a light liquid propellant missile. NPO Mashinotroyeniya (OKB-52) successfully proposed the development of the UR-100 missile known as SS-11 SEGO. After it had been cancelled, examples of the R-26 were paraded in Red Square, and identified in the West as the SS-8 SASIN. In fact, the entirely unrelated R-9A missile was the deployed SS-8 SASIN. It is not apparent at what point Western intelligence understood that the missile shown on parades in Red Square in Moscow and the missiles actually deployed elsewhere in Russia were in fact different and entirely unrelated missiles.

Specifications DIA

Mistaken for SS-8/R-9,R-9A

NATO

Sasin mistaken for SS-8/R-9, R9A

Bilateral

N/A

Service

Not deployed

OKB/Industry

R-26, 8K66

Design Bureau

OKB-586 (Acad. M. K. Yangel)

Approved

5/23/1960

Years of R&D Engineering and Testing

1960-1961

First Flight Test

Project canceled 07/09/1962

IOC

Not operational

Deployment Date

Not deployed

Type of Warhead

Single

Warheads

1

Yield (Mt)

5

Payload (t)

3-3.500

Total length (m)

24.38

Total length w/o warhead (m)

22

Missile Diameter (m)

2.75

Launch Weight (t)

85-87

Fuel Weight (t) Range (km)

10,500-11,000-12,000

CEP (m) (Russian Sources)

1,500-2,000

CEP (m) Western Sources)

?

Number of Stages Canister length (m) Canister length w/o

2 N/A N/A

front meters (m) Canister diameter (m) Booster guidance system

N/A Inertial

Length (m) Body diameter (m) Fueled weight (t) Dry weight (t) Engine Designation configuration Design Bureau Years of R & D Propellants Fuel Oxidizer

1st stage 11.4 2.75

RD-216 (11D614) two engine cluster Acad. V. P. Glushko OKB-456 1958-1960 Liquid Storable UDMH AT=AK-27P,= Nitrogen tetroxide, N204 in N02

2nd stage 10.05 2.4

Z-RD-? 1 engine Yuzhnoy?

Liquid Storable UDMH AT=AK-27P,= Nitrogen tetroxide, N204 in N02 120 160 43.65 vacuum

Burning time (sec.) Thrust Sea 151.499/177.9115 Level/Vacuum (Tonnes) Specific Impulse Sea 248/291.3 Level/Vacuum (sec.) Basing Mode Soft site and Silo Hardness Launching Technique Hot launch Deployed boosters 0 Test Boosters Warheads Deployed 0

Deployment Sites Training Launchers Space Booster Variant

N/A

R-36 / SS-9 SCARP The R-36 (8K67) ballistic missile, known in the west as the SS-9 SCARP, was a a twostage, tandem, storable liquid-propellant intercontinental ballistic missile. The missileuses an all-inertial guidance system and according to Western estimates had a CEP of 0.4 to 0.5 nm. The R-36 missile was derived from the experience gained during the development of the R-16 missile, and the first stage of the two missiles are very similar. The propulsion system of the first stage R-36 consisted of three open-cycle rocket engines with two combustion chambers and a four-chambered control engine. The second stage comprised a single engine with two combustion chambers. The oxidizer and fuel tanks of the second stage was the first Soviet ICBM to incorporated a common bulkhead, all propellant tanks were synchronously drained. Asymmetrical dimethylhydrazine and nitrogen tetroxide were used as propellants, and during flight gaseous combustion products were used to pressurize the fuel tanks. In order to increase accuracy the guidance system was originally planned to encompass a combination of an autonomous inertial system and radio-control. However, the deployed missile only disposed of an autonomous, inertial guidance/control system that provided the required accuracy. The SS-9's combination of high accuracy and yield constituted a convincing threat for the American ICBMs for the first time. The SS-9 was viewed in the United States as specifically designed to attack American Minuteman ICBM Launch Control Centers (LCCs), which initially were the "Achilles heel" of the Minuteman system, as 100 LCCs controlled all 1,000 Minuteman missiles. However, by 1969, as a result of redundant internetting of Minuteman silos and a backup airborne launch control system, the LCCs no longer were the "achilles heel" of Minuteman, so building one SS-9 for each Minuteman silo required MIRVed systems. Four payload variants were tested and deployed. 

The Mod 1 featured a single reentry vehicle with a warhead with a yield estimated by Western intelligence at 12 to 18 MT [this light version carried a warhead with a yield of 5 MT according to Russian sources]. This variant was assesed by Western intelligence as being capable of capable of delivering a payload of 12,500 lb to a range of 5500 nm.  The Mod 2 featured a single reentry vehicle with a warhead with a yield estimated by Western intelligence at 18 to 25 MT, although this heavy version carried a warhead with a yield of 10MT according to Russian sources. This variant was assesed by Western intelligence as being capable of capable of delivering a 13,500 lb reentry vehicle a maximum operational range of 5300 nm. The large yield, single warhead Mod 2 variant was the most extensively deployed.  The Mod 3 was a fractional-orbit, depressed-ICBM variant which combines the SS-9 first and second stages with an upper stage.



The Mod 4 variant was a three-warhead MRV which probably began as an attempt to achieve a true MIRV capability. The large throw-weight of the 8K67 missiles (up to 5.8 tons) made them suitable for carrying multiple warheads. The design for the R-36P missile carrying three warheads (8K67P) were conducted by the KB Yuzhnoye (OKB-586) in November 1967. The flight-design tests were started in August 1968. American intelligence remained divided over whether these warheads were independently targetable [MIRV], or merely flying parallel trajectories [MRV], and the issue assumed considerable importance in the context of the debate over the deployment of the American anti-missile program.

The development of the R-36 missile in its heavy, light and orbital version began after its approval by the Soviet government on 16 April 1962. The leading developer was KB Yuzhnoye (OKB-586). The flight-design tests of the ballistic missiles (8K67) began on 28 September 1963, though the first Mod 1 flight test was not detected by Western intelligence until 03 December 1963. The flight-design tests of the R-36 missile were conducted at the Baikonur cosmodrome. The tests of the 8K67 ballistic missiles lasted from 28 September 1963 though May 1966. The missile was placed in a silo of 41.5 meters deep with a shaft diameter of 8.3 meters and a door-diameter of 4.64 meters. Unlike the silo of the R-16U missile, the launch platform was not rotary, and the missile was directed to its trajectory (azimuthal guidance) through an onboard command structure after it left the silo. The SS-9 was deployed in individual, dispersed silos hardened to withstand 500-psi overpressure from a 1-MT weapon. The reaction time in the normal readiness condition is three to five minutes, with an unlimited hold time in that condition. According to Western estimates, the initial operational capability for the SS-9 system, with both the Mod 1 and Mod 2 single reentry vehicle variants was reached in early 1966. According to Russian sources, the first regiment equipped with R-36 missiles was placed on alert on 05 November 1966, deployment of the 8K67 ballistic missiles began on 21 July 1967, and on 26 October 1970 deployment of the multiple-warhead variant began. Between 1965 and 1973 a total of 268 launchers for the R-36 missiles were constructed. Their replacement by the MIRVed R-36P began in 1975. The R-36 ballistic missile was phased out in 1978. The missile was ready for launch during its whole period of service that was originally fixed at five years but subsequently extended to 7.5 years.

Specifications Mod-1

Mod-2

Mod-3

Mod-4

DIA

SS-9

SS-9

SS-9

SS-9

NATO

Scarp

Scarp

Scarp/ FOBS

Scarp/ MRV

Bilateral

Service

R-36

R-36

R-36O

R-36P

OKB/Industry

8K67

8K67

8K69

8K67P

Design Bureau

OKB-586 OKB-586 OKB-586 OKB-586 (Acad. M. (Acad. M. K. (Acad. M. (Acad. M. K. K. Yangel) Yangel) K. Yangel) Yangel)

Approved

4/16/1962

4/16/1962

Years of R&D

1/12/1965 19621966

1967- 1968

Engineering and Testing

1963-1966 1963-1966

19651969

1968-1970

First Flight Test

9/23/1963

12/16/65

8/23/1968

IOC

11/05/1966 1966

08/25/66

1970

Deployment Date

7/21/1967 &

7/21/1967

11/19/68

10/26/1970

Type of Warhead

Single

Single

Orbital

Multiple

Warheads

1

1

1

3

Yield (Mt) (Russian Sources)

5

10

5

2.0-3.5

Yield (Mt) (Western Sources)

12-18

18-25

1-3

Payload (t)

5.825

3.95

1.7

6

Total length (m)

32.2

31.7

32.6-34.5

32.2

Missile Diameter (m)

3.0

3.0

3.0

3.0

Launch Weight (t)

183.9

179 -183.89 180

183.9

Fuel Weight (t)

166.9170.2

166.2

166.2

166.2

Range(km)

10,200

15,20015,500

40,000

10,20012,000

CEP (m) (Russian Sources)

1,3001,900

1,300-1,900 1,100

1,340-1,970

CEP (m) (Western Sources)

900-920

920

1,850

10/10/1964

Total length w/o warhead (m)

1,8005,500

Number of Stages

2

Canister length (m) Canister length w/o front meters (m) Canister diameter (m) Booster guidance system

Inertial, autonomous 1st stage

2nd stage

Length (m)

18.9

9.4

Body diameter (m)

3

3

Fueled weight (t)

121.7 -122.3 (118.7)

48.5 - 49.3

Dry weight (t)

6.4

3.7 Total =17.737

Engine Designation

RD-251 (8D723)

RD-252

Design Bureau

Acad. V. P.Glushko (OKB-456)

Acad. V. P. Glushko (OKB-456)

Configuration

Cluster of three main engines, 6 chambers

One engine 2 chambers

Configuration

Yuzhnoy

Yuzhnoy

RD-68M / RD-855

RD-854

One engine 4 chambers

One engine 4 chambers

Propellants

Liquid Storable

Liquid Storable

Fuel

UDMH

UDMH

Oxidizer

AT =Nitrogen tetroxide

AT=Nitrogen tetroxide = NTO

Main Engines Burning time (sec.)

120,

160

Verniers Burning time (sec.)

127

163

Verniers Thrust Sea Level/Vacuum (Tonnes)

Yuzhnoy RD-68M /

Yuzhnoy RD-69M /

RD-855

RD-856

29.1

5.53

Main engines Thrust Sea Level/Vacuum (Tonnes)

241 / 270.4

96 Vacuum

Total Thrust Sea Level/Vacuum (Tonnes)

270.1 / 303

101.53 B 102.9982

Vernier Engine Specific Impulse Sea Level/Vacuum (sec.)

Vernier Engine

Vernier Engine

254 / 292

280.5 Vacuum

Main Engines

Main Engine

269 -270 /301

317.6 Vacuum

Main Engines Specific Impulse Sea Level/Vacuum (sec.)

Basing Mode

Silo

Hardness Launching Technique

Hot launch

Deployed boosters

0

Test Boosters Warheads Deployed

0

Training Launchers Space Booster Variant

Yes - SL-10 / F-1-r, Mod-3, FOBS SL-11 / F-1-m, Tsyklon - 2 SL-14 / F-2, Tsyklon - 3 Deployment Sites

START

Locale US-Designation

Aleysk

Aleysk

Derzhavinsk

Imeni Gastello

Dombarovskiy

Dombarovskiy

Kartaly

Kartaly

Uzhur

Uzhur

Zhangiz Tobe

Zhangiz Tobe

Historical Review - Western Estimates First flight test, Mod 1 RV

December 3, 1963

First flight test, Mod 2 RV prototype

October 10, 1964

First flight test, Mod 3 RV

1965

Initial operational capability Mod 1 and 2

Early 1966

Mod 4 subsystem design began

Early 1967

First flight test,

Mod 4 RV August 23, 1968

Initial operational capability

Mod 4 RV 1971

Maximum operational launcher inventory achieved 1971

R-36O / SL-X-? FOBS In the early 1960s, the Soviets needed a way to overcome the West's geographic advantages (forward bases in Turkey, Europe, and Asia from which shorter range missiles and bombers could attack the USSR). The Soviet attempt to place missiles in Cuba would have been a partial remedy. When the Cuban venture did not go as planned, they moved to other technological possibilities. The Soviets demonstrated the technology necessary to orbit a space vehicle and then land it in a specific place with the Vostok launches. It was thus logical to assume they could place nuclear weapons in orbit and return them to Earth at any time and place. Khrushchev made this suggestion in 1961, but on 15 March 1962, as part of the rhetoric proceeding the Cuban crisis, he made yet another, more ominous suggestion. We can launch missiles not only over the North Pole, but in the opposite direction, too. . . . Global rockets can fly from the oceans or other directions where warning facilities cannot be installed. Given global missiles, the warning system in general has lost its importance. Global missiles cannot be spotted in time to prepare any measures against them. This statement was the first hint of a new concept called the fractional orbit bombardment system (FOBS). The 1961 Global Rocket 1 (GR-1) requirement chartered a competition for the development of a Fractional Orbital Bombardment System. Yangel offered the R-36O. Korolev proposed the 8K713, which was cancelled in 1964 prior to flight testing due to engine delays. Chelomei proposed the UR-200, which was cancelled following the October 1964 ouster of downfall of Khrushchev, who had been Chelomey's political patron. The R-36O SS-9 Mod 3 SCARP with a modified upper stage was equipped with an orbital nose cone, which contained an instrumentation section, a single-chambered liquid propellant retrorocket motor and a nuclear warhead. The orbital missile carried a one- to three-megaton warhead according to Western estimates [and five megatons according to some published Russian estimates -- about the only instance in which published Russian yield estimates are higher than published Western estimates]. Flying into low-Earth orbit gave the ICBM unlimited range and allowing it to approach the US from any direction, avoiding US northern-looking detection radars and, therefore, giving little or no warning. The reentry vehicle came down in less than one revolution, hence the "fractional" orbit. After the failure of their first two tests in 1966, the Soviets tested their FOBS with nine launches between 25 January and 28 October 1967. All missions followed the same distinct flight profile--launching in the late afternoon into an elliptical, near-polar lowEarth orbit and deorbiting over the Soviet landmass before one complete orbit. This profile allowed the Soviets to monitor the deorbit, reentry, and impact. US planners viewed FOBS as a pathfinder system intended to precede a conventional ICBM attack. The FOBS would circumvent the existing US ballistic missile early warning radars and hit SAC airfields before the bombers could take off. FOBS could destroy ABM radars, disrupt US retaliatory capability, destroy command posts, the White House, and the

command and control network. But, due to its limited accuracy and payload, FOBS was ineffective against hardened targets. Under the 1967 Outer Space Treaty, the Soviets could orbit everything but the nuclear warhead. Some US Senators were concerned with the Soviet FOBS development which followed on ratification of the Outer Space Treaty. The Soviets could, without treaty violation, deploy the weapons system minus the warheads. By 1968 the Soviets' FOBS program settled into a two-flight-per-year pattern which indicated an operational status, although they only deployed FOBS in 18 silos. Little attention was paid to these events in the United States, because they occurred during the national election and at a time when Vietnam had all the headlines. At that time it remained unclear to US intelligence whether the Soviets were developing FOBS, or ballistic missiles with depressed trajectories and deboost capabilities. The orbital missile 8K69 was initially deployed on 19 November 1968, and the first regiment with the R-36 orbital missiles was put on alert on 25 August 1969. The orbital missile was phased out in January 1983 in compliance with the SALT-2 treaty, which prohibited the deployment of these missiles.

Specifications Mod-3 DIA

SS-9

NATO

Scarp/ FOBS

Bilateral

16935

Service

R-36O

OKB/Industry

8K69

Design Bureau

OKB-586 (Acad. M. K. Yangel)

Approved

1/12/1965

Years of R&D

1962-1966

Engineering and Testing

1965-1969

First Flight Test

12/16/65

IOC

08/25/66

Deployment Date

11/19/68

Type of Warhead

Orbital

Warheads

1

Yield (Mt)

5

(Russian Sources)

Yield (Mt)

1-3

(Western Sources) Payload (t)

1.7

Total length (m)

32.6-34.5

Total length w/o warhead (m)

21543

Missile Diameter (m)

3

Launch Weight (t)

180

Fuel Weight (t)

166.2

Range(km)

40,000

CEP (m)

1,100

(Russian Sources) CEP (m)

1,800-5,500

(Western Sources) 1st stage

2nd stage

3rd.Stage FOBS/OR36

Length (m)

18.9

9.4

8.3

Body diameter (m)

3.0

3.0

4.64

Fueled weight (t)

121.7 -122.3 (118.7)

48.5 - 49.3

Dry weight (t)

6.4

3.7 Total =17.737

Engine Designation

RD-251 (8D723)

RD-252

Design Bureau

Acad. V. P.Glushko (OKB-456)

Acad. V. P. Glushko

Cluster of three main engines, 6 chambers

One engine

One engine

2 chambers

1 chamber

Yuzhnoy

Yuzhnoy

Configuration

Configuration

RD-68M / RD-

Yuzhnoy

(OKB-456)

855

RD-854

One engine 4 chambers

One engine 4 chambers

Propellants

Liquid Storable

Liquid Storable

Liquid Storable

Fuel

UDMH

UDMH

UDMH

Oxidizer

AT =Nitrogen tetroxide

AT=Nitrogen tetroxide AT= NTO = NTO

Main Engines Burning time (sec.)

120,

160

Verniers Burning time (sec.)

127

163

Verniers Thrust Yuzhnoy RDSea 68M / Level/Vacuum (Tonnes) RD-855

70 sec.

Yuzhnoy RD-69M / RD-856 5.53

29.1 Main engines Thrust Sea Level/Vacuum (Tonnes)

241 / 270.4

96 Vacuum

Total Thrust Sea Level/Vacuum (Tonnes)

270.1 / 303

101.53 102.9982

Vernier Engine Specific Impulse Sea Level/Vacuum (sec.)

Vernier Engine

Vernier Engine

Main Engines Specific Impulse Sea

Main Engines

Main Engine

269 -270

317.6 Vacuum

280.5 Vacuum 254 / 292

7.7 Vac.

Level/Vacuum (sec.)

/301

R-36M / SS-18 SATAN The R-36m / SS-18 intercontinental ballistic missile is a large, two-stage, tandem, storable liquid-propellant inertial guided missile developed to replace the SS-9 ICBM. Housed in hard silos, the highly accurate fourth generation SS-18 ICBM is larger than the Peacekeeper, the most modern deployed US ICBM. The SS-18 opened a "window of vulnerability" of Minuteman silos (at 300 psi) by 1975, so that some analysts aregued that few Minuteman could be expected to survive a Soviet attack by 1980. The "window of vulnerability" of U.S. land based strategic missiles opened on schedule, and became one of the major issues in U.S. strategic debates in the late 1970s and early 1980s. The R-36M (15A14) was a two-stage missile capable of carrying several different warheads. The basic design is similar to the R-36 missile modified to include advanced technologies and more powerful engines. This missile, using dinitrogen tetroxide (N2O4) and heptyl (a UDMH [unsymmetrical dimethyl hydrazine] compound) has a first stage powered by a 460-ton-thrust motor with four combustion chambers, and the second by a single-chamber 77-ton-thrust motor. The first stage uses four closed-cycle single chambered rocket motors. The second stage was equipped with a closed-cycle single chambered sustainer motor and an open-cycle four chambered control motor. The second stage sustainer is built into the fuel tank's toroidal cavity. The flight control of the first stage was conducted through gimbaled sustainers. The sustainers used asymmetrical dimethylhydrazine and nitrogen tetraoxide. The missile was equipped with an autonomous inertial command structure and an onboard digital computer. The R-36M used a gas-dynamic method for the first and second stages whereby special ports are opened through which the propellant tanks are pressurized. This obviated the need for the use of pressurant gases from tanks and the so-called chemical tanks pressurization (by injecting small amounts of fuel in the oxidizer tank and oxidizer into the fuel tank). The improved design and more effective engines allowed an increase in the total liftoff weight from 183 tons to 209.6 ton and the throw weight from 5.8 tons to 8.8 tons, while maintaining the overall dimensions of its predecessor missile. The SS-18 was deployed in modified SS-9 silos, and employed a cold-launch technique with the missile being ejected from the silo prior to main engine ignition. The rocket was placed in a transport-launch canister made of fiberglass composites. The container was placed into an adapted R-36 silo. The specially hardened silo was 39 meters deep and had a diameter of 5.9 m. Prior to main engine ignition the missile was ejected from the container with the help of a solid-propellant gas generator located in the lower unit of the transport-launch canister. According to Western estimates, the SS-18 was deployed in a silo with a hardness of at least 4,000 psi (281 kg/sq. cm; 287 bar), and possibly as high as 6,000 psi (422 kg/sq. cm; 430 bar). The development of the two stage heavy liquid-propellant ICBM R-36M intended to replace the R-36 SS-9 Scarp was accepted on 02 September 1969. The preliminary design was completed in December 1969 by the design bureau was KB Yuzhnoye. The system

was designed by the M. K. Yangel OKB Yuzhnoye at Dnepropetrovsk (Ukraine) during 1966-1972, with testing beginning in November 1972. It was deployed in January 1975, and integrated with the weapons arsenal in December 1975. There are six variants that have been deployed, while others were tested but not deployed: 

SS-18 Mod 1 - R-36M The SS-18 Mod 1 carried a single large reentry vehicle, with a warhead yield of 18 to 25 MT, a distance of about 6,000 nm. In January 1971 pop-up tests, began during which the mortar launch was perfected. The actual flight tests for the single-RV Mod-1 began on 21 February 1973, though some sources suggest that testing began in October 1972. The testing phase of the R-36M with various different types of warheads was finished in October 1975 and on 30 December 1975 deployment began [though some Western sources suggest that an initial operational capability was reached in early 1975]. A total of 56 were deployed by 1977, though all were replaced by Mod 3 or Mod 4 missiles by 1984. These high-yield weapons were assessed in the West as possibly developed to attack American Minuteman ICBM launch control centers.  SS-18 Mod 2 - R-36M The SS-18 Mod 2 included a post-boost vehicle and up to eight reentry vehicles, each with a warhead yield estimated at between 0.5 to 1.5 MT, with a range capability of about 5,500 nm. The MIRVs were placed in pairs, and a post boost vehicle with a command structure and a propulsion system were contained in the nose cone of the R-36M. The flight tests of the MIRVed Mod-2 began in September 1973 [though some Western sources suggest that the initial flight test of the Mod 2 MIRV version occurred in August 1973], with IOC in 1975. Approximately 132 were deployed by 1978, but the post-boost vehicle design was seriously flawed, and the Mod 2 missiles were all replaced by the Mod 4 variant by 1983.  SS-18 Mod 2x - R-36M Between July 1978 and August 1980 a MIRVed missile with an improved nose cone was tested but not deployed. The fact of the existence of this system is reported by Russian sources, but not attested by unclassified Western literature.  SS-18 Mod 3 - R-36UTTh The SS-18 Mod 3 carried a single large reentry vehicle that was an improved version of the SS-18 Mod-1. On 16 August 1976, a few months after the R-36M entered service, the development of an improved modification of the R-36M (15A14) and MR UR-100 (15A15) was approved. This missile subsequently received the designation R-36M UTTh (15A18) and was developed by KB Yuzhnoye (OKB-586) through December 1976. Its increasing accuracy made it possible to reduce the yield of the warheads. The R36M UTTh was capable of carrying two different nose cones. The version with a divided nose cone [Mod-4] allowed an increase the numbers of warheads from 8 up to 10 and the single-RV version [Mod-3] had a maximum range of up to 16,000 km. The flight-design tests of the R-36M UTTh began on 31 October 1977. On 29 November 1979 deployment of the SS-18 Mod-3 with a single reentry vehicle carrying a warhead with a yield of 24-25 MT began. The P-

36MUTTh was introduced into the inventory on 17 December 1979. A total of 24 were deployed in 1977, and all were replaced by the Mod 4 variant by 1984.  SS-18 Mod 4 - R-36UTTh The SS-18 Mod 4 carries at least 10 MIRVs and was probably designed to attack and destroy ICBMs and other hardened targets in the US. According to some Western estimates, evidence suggested that the Mod 4 may be capable of carrying as many as 14 RVs [this may reflect observation of the deployment of countermeasures intended to overcome a ballistic missile defense, or to confuse American attack characterization systems]. In November 1979 the flight tests of the MIRVed missile were completed. The first three regiments were put on alert on 18 September 1979. During 1980 a total of 120 SS-18 Mod 4 missiles were deployed, replacing the last remaining R-36 missiles. In 1982-1983 the remaining R-36M missiles were also replaced with the new R36M UTTh and the total number of deployed missiles reached a maximum operational launcher reached 308, ceiling established in the SALT-1 treaty. The SS-18 Mod 4 force had the estimated capability to destroy 65 to 80 percent of US ICBM silos using two nuclear warheads against each. Even after this type of attack, it was estimated that more than 1,000 SS-18 warheads would be available for further strikes against targets in the US. After 1988 the SS-18 Mod 4s were partially replaced by the new R-36M2 "Voivode".  SS-18 Mod 5 - R-36M2 "Voivode" The newer, more accurate version (the SS-18 Mod 5) placed in converted silos allowed the SS-18 to remain the bulwark of the SRF's hard-target-kill capability. The Mod 5 carries 10 MIRVs, each having a higher yield than the Mod 4 warheads. The Mod-5 warheads have nearly twice the yield of the Mod-4 (approximately 750 kt to 1 megaton) according to Western estimates, though Russian sources suggest a yield of 550-750 Kt each. The increase in the Mod 5's warhead yield, along with improved accuracy, would, under the START treaty, help allow the Russians to maintain their hard-target-kill wartime requirements even with the 50 percent cut in heavy ICBMs the START agreement required. The technical proposals to build a modernized heavy ICBM were made in June 1979. The missile subsequently received the designation R36M2 "Voivode" and the industrial index number 15A18M. The design of the R36 M2 "Voivode" was completed in June 1982. The R-36M2 disposed of a series of new engineering features. The engine of the second stage is completely built in the fuel tank (earlier this was only used on SLBMs) and the design of the transport-launching canister was altered. Unlike the R-36M, the 10 warheads on the post-boost vehicle are located on a special frame in two circles. The flight tests of the R-36M2 equipped with 10 MIRVs began in March 1986 and were completed in March 1988. The first regiment with these missiles was put on alert on 30 July 1988 and was deployed on 11 August 1988.  SS-18 Mod 6 - R-36M2 "Voivode" The flight tests of a the R-36M2 missile (Mod-6) carrying a single warhead with a yield of 20 MT were completed in September 1989 and deployment began in August 1991. The only deployed versions of the SS-18 are the R-36M UTTh and R-36M2. In 1997 there were 186 deployed launchers for of these missiles in Russia. The dismantling of 104 launchers located in Kazakhstan was completed in September 1996.

The Reagan and Bush administrations respected the SS-18 to such a degree that they made it the main focus of their arms control initiatives. The START II Treaty specifically banned land-based MIRV systems, in part, because of the threat the SS-18 posed to the balance of power. It was seen as a first-strike weapon and a very destabilizing presence in the bilateral relationship. US negotiators allowed the Russian Federation to retain 90 of the SS-18 silos. After complying with the START II silo conversion protocol, the Russian Rocket Forces will be permitted to replace 90 of the SS-18s with a smaller, single-warhead missile. The protocol requires Russia to place a 2.9-meter restrictive ring near the top of the retained SS-18 silos and to fill the bottom five meters of the silos with concrete. These measures make the silos too small to hold an SS-18. The Nunn-Lugar program is assisting in the reduction of the SS-18 missile threat to the United States. The Russian Federation must eliminate 100 SS-18s by December 2001 and an additional 154 SS-18s by January 2003. In recent years, Nunn-Lugar has played a role in SS-18 dismantlement. It provided the equipment necessary to help destroy the missiles. A total of 204 of these missiles were deployed on Russian territory and 104 in Kazakhstan. The elimination base at Surovatikha, near Nijny-Novgorod, destroyed 32 missiles in 1993 with the remaining 44 destroyed in 1994. The SS-18 was manufactured in Ukraine, while Russian enterprises provide maintenance for SS-18s which are currently in inventory. Manufacturing of SS-18s in Russia would be expensive, and could require 5 to 7 years of design work to begin at least tests at a cost of 8-10 billion rubles.

Specifications Mod

Mod-1

Mod-2

Mod-3

Mod-4

Mod-5

Mod-6

DIA

SS-18

SS-18

SS-18

SS-18

SS-18

SS-18

NATO

Satan

Satan

Satan

Satan

Satan

Satan

Bilateral

RS-20A

RS-20A

RS-20A RS-20B

RS-20V RS-20V

Service

R-36M

R-36M

R-36M

R-36MU

R-36M2 R-36M2

UTTkh

UTTkh

15A14

15A18

OKB/Industry 15A14 Design

15A14

15A18M 15A18M

Bureau

OKB-586 OKB-586 OKBOKB-586 OKBAcad. V. 586 586 Acad. V. F. Utkin Acad. V. Acad. F. Utkin Acad. V. F. Utkin V. F. F. Utkin Utkin

OKB586 Acad. V. F. Utkin

Approved

9/2/1969

6/1979

9/2/1969

9/2/1969 8/16/1977 8/9/83

?12/17/ 1980 ? Years of R&D

19691973

19691973

Engineering and Testing

19731974

19731975

19781980

First Flight Test

1 / / 72 1St . failure

9/ /73,

7/ /1978 7/31/1977 3/21/86 1986

IOC

12 /25 / 1974

1975

Deployment Date

12/30/

08/ /73 & another 2/21/1973 derivation success 1 & another 07/ /78 derivation 11-29-79

12/ 76 78

19831988

19791982

19771979

1986-88 19861990

or 10-311977

two failures in the flight test program

1980

9/1979 ? 11-271979?

12/1988 1990

12/30/

11/29/

12/17/

12/1988 9/1991

1975

1975 or 11/20/78

1979

1979, or 1980?

Single

MIRV

Single

MIRV

MIRV

Single

Warheads

1

8

1

10

10

1

Yield (Mt) Russian sources

18-20

0.5-1.3

24-25

0.55

0.550.75

20

Yield (Mt) Western sources

18-25

0.6-1.5

18-25

0.75-1.0

Payload (t)

7.2

7.2 - 8.8

7.2 - 8.8 8.8

8.8

8.8

Total length (m)

33.6

33.6

33.6

34.3

37.25

36.3

Total length 28.5 w/o warhead (m)

28.5

28.5

28.5 29.25

29.25

29.25

Missile

3.0

3.0

3.0

3.0

3.0

Type of Warhead

3.0

Diameter (m) Launch Weight (t)

209.6 210

209.6 210

209.6 210

211.1

211.1

211.1

Fuel Weight (t)

188

188

188

188

188

188

Range (km)

11200

925010200

16.000

16000

11000

16000

11500

15,000

CEP (m)

1000

1000

1000

920

500

500

400-550

400-500

350

220-320

250

?250

Russian Sources CEP (m) Western Sources

Number of Stages

2

Canister length (m)

27.9

Canister diameter (m)

3.5

Booster guidance system

Inertial, autonomous

1st stage

2nd stage

Length (m)

22.3

7.0

Body diameter (m)

3.0

3.0

Fueled weight (t)

Total 161.5

Dry weight (t)

Total 48.1 ? 48.5

Engine Designation

RD-263 x 4 = RD-264 (11D119) for the

RD-0228 = RD-0229 one main engine and RD-0230 four verniers for the R-36M

R-36M Engine Designation

RD-273 / RD-274 for the R-36MU

RD-0230 verniers for the R-36M

Engine Designation

N/A

RD-0255 = RD-0256 one main engine & RD-0257 four verniers for the R-36M2.

Design Bureau

Acad. V. P. Glushko (OKB-456)

Acad. S. A. Kosberg (OKB-154)

Configuration

Four RD-263?s Engines = RD-264

1 Main Engine + 4 Verniers

Years Of R & D

1969-1973 = RD-263 x 4=RD-264

1967-1975 = RD-0228 / RD0229

Years Of R & D

1975-1980 = RD-273

1967-1975 = RD-0230

Years Of R & D

1983-1989 = RD-0255 1983-1987 = RD-0256 1983-1987 = RD-0257

Propellants

Liquid Storable

Liquid Storable

Fuel

UDMH

UDMH

Oxidizer

Nitrogen Tetraoxide

Nitrogen Tetraoxide

424 / 450-461

77

Burn Time (sec.) Main Engines Thrust Sea Level/Vacuum (Tonnes)

Verniers Engine Thrust N/A Sea Level/Vacuum (Tonnes) Main Engines Specific Impulse Sea Level/ Vacuum (sec.)

?

293 / 312-318

MIRV Bus Third Stage Engine Designation for the R-36M2

RD-869

Design Bureau (Bus)

Yuzhnoy SKB

Years Of R & D (Bus)

1983-1985

Propellants (Bus)

Liquid Storable

Fuel (Bus)

UDMH

Oxidizer (Bus)

Nitrogen Tetraoxide

Thrust Vacuum (Tonnes)

2.087- 0.875

Engines Specific Impulse (sec.)

313 ? 302.3

Burn Time (sec.)

700

Basing Mode

Silo

Hardness Launching Technique

Cold and Solid motor

Deployed boosters Test Boosters Warheads Deployed Training Launchers Space Booster Variant

Yes- SL-21?/Dnipr SS-18 derivation Deployment Sites

START

Locale US-Designation

Aleysk in Altai (30)

Aleysk

Derzhavinsk near Akmolinsk (52)

Imeni Gastello

Dombarovsky-3 near Orenbourg (64)

Dombarovskiy

Kartaly-6 near Chelyabinsk (46)

Kartaly

Uzhur-4 near Krasnoyarsk (64)

Uzhur

Zhangiz-Tobe near Seminpalatinsk (52)

Zhangiz Tobe

SS-18/RS-20 in Launch Canister

SS-18/RS-20 Emplacement Equipment

SS-18/RS-20, Stage 1

SS-18/RS-20 Missile

R-46 On 09 August 1961, Premier Nikita Khrushchev openly threatened the West with a new and terrifying weapon, the orbital H-bomb. "You do not have 50- or 100-megaton bombs, we have bombs more powerful than 100 megatons. We placed Gagarin and Titov in space, and we can replace them with other loads that can be directed to any place on Earth." Although the US had hypothesized orbital bombs, this was the first public indication that the Soviets were actively pursuing this course of action. Within a few months, however, American analysis of the threat diminished its proportions.

Specifications SHB2

SHB3

Mod-1 = 2 Stages

Mod-2 = 3 Stages

DIA

SS-LX-? " City Buster" ICBM

SS-LX-? FOBS

NATO

N/A

N/A

Bilateral

N/A

N/A

OKB/Industry

(8K68)

(8K68)

Design Bureau

OKB-586, (Acad. M. K. Yangel )

OKB-586, (Acad. M. K. Yangel )

Approved

4/16/1962

4/16/1962

Years of R&D

19621964

1962-1964

Engineering and Testing

Model Dynamic Testing Only

Model Dynamic Testing Only

First Flight Test

N/A Canceled 6/19/1964

N/A Canceled 6/19/1964

IOC

N/A

N/A

Deployment Date

N/A

N/A

Service

Type of Warhead

1

1

Warheads

Single

Single

Yield (Mt)

50 – 100 – 150

30 – 50

Payload (t)

9,535 – 12,264

Orbital 10,960 – 11,220

Total length (m)

~56

~65

Total length

~49.87

~59.87

Missile Diameter (m)

3.9

3.9

Launch Weight (t)

383,096 390,400 + 12,764

383,735.8350 - 392,270 + 12,764 or 9,535

Range (km)

12,000 – 16,000

12,000 – 16,000

CEP (m) (Russian Sources)

N/A

N/A

CEP (m) (Western Sources)

N/A

N/A

Basing Mode

Hardened launch complex

Hardened launch complex

Number of Stages

2

Canister length w/o front meters (m)

N/A

Canister diameter (m)

N/A

w/o warhead (m)

Fuel Weight (t)

3

Booster guidance system Inertial autonomous 1st stage 2nd stage Length (m) 24 or (32.94 - 39.46) 10 – 10.41 Body diameter (m) 4.0 - 3.9 4.0 - 3.9 Fueled weight (t) 200,334 +77,052 = 62,477 277,386 +24,039 = 86,516 Dry weight (t) 13,869 4,325

~10 ~4.0 - 3.9 1,639 + 0.603 = 1639.603 0.232

Engine Designation Configuration Design Bureau

RD-253 (11D48)(11D43) Cluster of Four Engines OKB-456, Acad. V. P. Glushko

RD-254

KTDU-5A

One Engine

One Engine

OKB-456, Acad. V. P. Glushko 1962-1964 Liquid UDMH

OKB-2, Acad. A. M. Isayev

Years of R&D Propellants Fuel

1961-1965 Liquid UDMH

Oxidizer

Nitrogen Tetroxide

Nitrogen Tetroxide

Burning time (sec.)

130

159.7

Verniers Thrust Sea Level/Vacuum (Tonnes) Main engines Thrust Sea Level/Vacuum (Tonnes) Total Thrust Sea Level/Vacuum (Tonnes) Specific Impulse Sea Level/Vacuum (sec.) Hardness Launching Technique Deployed boosters Test Boosters Warheads Deployed Training Launchers Space Booster Variant

1961 – 1965 Liquid TG-02 = A Amine based fuel AK-27I = 73% HNO3 + 27%N204 = Nitrogen Tetroxide concentrated in Nitric Acid 100.3 +11.6+22.5=

N/A

?

134.4 total ?

148.8884 - 150.25 / 166.7347

174.7

4.638

4 x 150.25 = 601.0

174.7

4.638

284.9/310.0

329.89

277.78

N/A Hot launch N/A N/A N/A N/A SL-LX-? SHB-2 & SHB-3 not developed

Deployment Sites START N/A

Locale US-Designation N/A

UR-100 / SS-11 SEGO The development of the massively deployed UR-100/SS-11 liquid propellant light ICBM was the centerpiece of a major Soviet effort to reach numerical strategic parity with the USA. The SS-ll was the Soviet counterpart of the US Minuteman system in quantity, size and purpose. Initially deployed with a single warhead [with a yield of 1.1 MT according to Russian sources, or 0.6 to 1.2 MT according to Western reports] and a low accuracy [a CEP of 1.4 km according to Russian sources], the missile could be used only against soft targets. The UR-100 intercontinental ballistic missile is a two-stage, tandem, storable liquidpropellant missile. It is about 64 feet long and 8 feet in diameter. In both stages the oxidizer and fuel tanks had a common bottom which reduced overall dimensions and launch weight of the missile. The bottom of the oxidizer tank of the first stage was placed inside the tank like an inverted truncated cone. The nozzle of the sustainer of the second stage was included in the formed upper volume. The first stage used a new set of four closed-cycle single-chambered rocket motors, while the second stage incorporated a single-chambered sustainer and a four-chambered control motor. Asymmetrical dimethylhidrazine and nitrogen tetraoxide were used as propellants. The missile uses an inertial guidance system consisting of an autonomous guidance/control system with a gyro-stabilized platform of floating gyros. The command structure also provided an automatic checkout of all systems during flight and automatic preparation of launch. The development of the UR-100 was approved by the government on 30 March 1963. The developer was NPO Mashinostroyenia (OKB-52). The missile was deployed in at least four variants, and was probably tested in several additional configurations. There is some confusion among these variants between recent published Russian sources, which focus on the physical configuration of the rocket, and contemporaneous Western sources, which were limited to intelligence derived from observing flight tests. In the middle of the 1970's the UR-100 was replaced by two modernized versions that received the designations UR-100K (15A20) and UR-100U (15A20U). 

SS-11 Mod-1 UR-100 The flight-design tests were conducted at the Baikonur cosmodrome between 19 April 1965 and 27 October 1966. The first silo-launch was conducted on 17 July 1965. The Mod 1 reentry vehicle had a ballistic coefficient of 310 lb per sq ft and a CEP assessed by Western intelligence at 1.0 nm. Western intelligence assessed that an initial operational capability was reached in early 1966. According to Russian sources the first three regiments with UR-100 missiles were put on alert on 24 November 1966, and operational employment began on 21 July 1967. According to Russian sources, initially the missile was equipped with two different types of warheads: a light one for intercontinental targets in North America, and a heavier one for medium range targets in Eurasia.  SS-11 Mod-1 UR-100UTTh Upgrades to the UR-100 missile provided a different nose cone that allowed improved flight characteristics and a modified command

structure that reduced the time for pre-launch operations. The modified version received the designation UR-100UTTh (8K84UTTh). It differed from former missiles by improved warhead technology, improved launching equipment, and an autonomous power supply system, ensuring extended storage in fueled conditions. The flight-design tests of the UR-100UTTh missile were conducted between 23 July 1969 and 15 March 1971.  SS-11 Mod-2 UR-100K The development of the UR-100K (15A20) missile [known in the West as the SS-11 Mod-2] began in the middle of the 1960s. The main design changes concerned lengthening of the first stage to increase the amount of propellant and modifications to the propulsion systems of both stages. These measures allowed an increase of launching weight of 8 tons and a 60 percent increase of throw weight. The maximum range of the UR-100K was increased up to 12,000 km, and through the use of improved sensors the accuracy was increased by a factor of 1.5 to a CEP of 1 Km. The Mod 2 reentry vehicle had a ballistic coefficient of 900 lb per sq ft and a CEP assessed by Western intelligence at 0.6 nm. The missile also dispensed decoys at the end of the boost phase of the trajectory before the separation of the reentry vehicle. The reentry vehicle itself had radio-reflecting properties. The sophisticated control system allowed an increase of combat readiness of a missile through the use of boosted spin-ups of gyros. The silo had its own system of power supply allowing remote changes of its mission and launch. The flight-design tests of the UR-100K missile were conducted from 02 February 1971 through 24 November 1971. According to Russian sources the missile was initially deployed on 28 December 1971. Western intelligence assessed that an initial operational capability was reached in 1973.  SS-11 Mod-3 UR-100U The UR-100U (15A20U) missile differed from the UR100K missile by the number of warheads. Instead of a single warhead it carried three warheads, though with a reduced maximum range. The tests of the UP-100U were conducted from July 1971 through January 1973, and its deployment started on 26 September 1974 according to Russian sources. According to Western sources, the first Mod 3 flight test was on 12 September 1969, and Western intelligence assessed that an initial operational capability was reached in 1973. During development of this missile efforts centered on increasing its survivability. The silos were hardened and the shock-absorption of the transport-launch canister was improved. The silo consists of a monolithic ferro-concrete trunk with a steel hardware compartment, rigidly attached to it. The trunk was covered with an accident protection device in the form of a sliding roof.  SS-11 Mod-4 The Mod-4 missile differed from the Mod-3 missile by the number of warheads -- instead of three warheads it carried six. This variant was tested but not deployed. The missile was deployed in a silo launcher, with a design that was substantially simplified in comparison with earlier complexes. The silo could be closed for protection with the help of a pneumatic driven sliding roof. This was the first Soviet ICBM to be deployed with a pressurized transport launch canister in which the missile was delivered to the launch complex and from which it was fired. During the storage of the missile the

engines were isolated from the propellant components by membrane-valves that provided their safety during extended times of being in a fueled condition. The SS-11 deployment was assessed by Western intelligence to be similar in concept to the US Minuteman, where a large force was deployed in hardened silos requiring a minimum of support facilities. Silo and launch control center hardness was estimated at 700 and 400 psi overpressure, respectively, from a 1-MT weapon. The sites were deployed in groups of ten unmanned silos with a single launch control center for each group. Reaction time in the normal readiness condition was assessed by the West as 0.5 to 3.0 min. with an unlimited hold time in this alert condition. The UR-100 missile was the most extensively deployed ICBM within the Strategic Rocket Forces. Between 1966 and 1972 a total of 990 of these missiles were deployed. Between 1973 and 1977 some 420 launchers of the UR-100K/UR-100U missiles were deployed while the UR-100 missiles were phased out. As of 1991 some 326 remained in service, while by the end of 1994 all but 10 of the UR-100 and UR-100U missiles had been removed from combat duty in compliance with the START-1 treaty. By the end of 1996 all SS-11 missiles had been dismantled.

Specifications Mod-1

Mod-2

Mod-3

Mod-4

DIA

SS-11

SS-11

SS-11

SS-11

NATO

Sego

Sego

Sego

Sego

Bilateral

RS-10

RS-10

RS-10M

RS-10M

Service

UR-100/ UR-100M

UR-100K UR-100U

OKB/Industry

8K84 8K84K 8K84UTTkh

Design Bureau

OKB-52 Chelomey

Approved

3/30/1963

Years of R&D

1951-66

Engineering and Testing

8K84UTTkh 8K84M 15A20U

OKB-52 OKB-52 Chelomey Chelomey

OKB-52 Chelomey

1962-66

19691971

1971-1973

First Flight Test

4/19/65

7/23/1969 2/2/71 & 9/2/69

6/16/71

IOC

11/24/966

3/1/1970

[not deployed]

1971-1973

1973 - 74

Deployment Date

7/21/1967

12/28/72

9/26/1974

[not deployed]

Type of Warhead

Single

Single

MRV

MRV

Warheads

1

1

3

6

Yield per Warhead 0.5 or (Mt) 1.0 -1.1 (Russian Sources)

1.2

0.35

0.35-1.3

Yield per Warhead 0.6 to 1.2 (Mt) (Western Sources)

0.6 to 1.2 0.2 to 0.8

Payload (t)

0.76 - .08

0.9-1.2

1.208

1.2

Total length (m)

16.925

18.9 19.0

18.9

19.1 - 19.8

Total length w/o Warhead (m)

16.4516.69

16.5

17

17

Missile Diameter (m)

2

2.

2

2

Launch Weight (t)

39.4 - 42.3

50.1

50.09 - 50.1 50.1 51.24

Fuel Weight (t)

40.4?

45.3

45.3

45.3

Range (km)

11,00012,000 or 5,000

11,00013,000

10,60012,000

10,60012,000

CEP (m) 1,400 (Russian Sources)

1,400

900-1,350

900-1,350

CEP (m) 1,400(Western Sources) 1,500

1,1001,400

1,0001,100

Number of Stages

2

Canister length (m)

19.5

Canister length w/o Front meters (m) Canister diameter (m)

2.9

Booster guidance system

Inertial, autonomous

1st stage (8S816)

2nd stage (8S817)

Mod1

Mod-2

Mod-3/4

Mod-1

Mod-2

Mod-3/4

Length (m)

12.5

13.3

13.4

2.9

3.2

3.8

Body diameter (m)

2

Fueled weight (t)

34

2 38-40

40

Dry weight (t) Engine

RD-0216 / RD-0217 (15D2)

RD-0235 / RD-0236 (8D13, 8D419, 15D14)

Design Bureau

OKB-154, Acad. S. A. Kosberg

OKB-117, Acad. V. Klimov

Configuration

Cluster of four engines

One engine

Years of R & D

1963-1966

Propellants

Liquid

Liquid

Fuel

UDMH

UDMH

Oxidizer

Nitrogen Tetroxide

Nitrogen Tetroxide

Burning time (sec)

103?

164?

Verniers Thrust Sea Level/Vacuum (Tonnes)

N/A

1.565 ?1.6

Main Engines Thrust Sea Level/Vacuum (Tonnes)

79.95/86.275 - 89.33

13.665 - 15.195 - 24.5 Vacuum

Total Thrust Sea Level/Vacuum (Tonnes)

319.8/357.6

20.0651 - 22.3 - 30.9 Vacuum

Main engine Specific Impulse Sea Level/Vacuum (sec.)

262/313 Vacuum

320 Vacuum

Verniers Specific Impulse Sera

N/A

293 Vacuum

Designation

Level/Vacuum (sec.) Basing Mode

Silo

Hardness

Silo at 700-750 psi LCC at 360-400 psi

Launching Technique

Hot

Deployed boosters Test Boosters Deployment Sites Training Launchers Space Booster Variant

No Deployment Sites

START

Locale US-Designation

Bershet?

Perm

Drovyanaya

Drovyanaya Itatka

Kostroma

Kostroma

Kozelsk

Kozelsk

Krasnoyarsk

Gladkaya

Pervomaysk

Pervomaysk Shadrinsk

Svobodny

Svobodny

Teykovo

Teykovo Tyumen

Yasnaya

Olovyannaya

Historical Review - Western Estimates

First flight test Mod 1

April 19, 1965

Mod 2

July 23, 1969

Mod 3

September 12, 1969

Operational system production probably began Mod 1

1965

Mod 2

?

Mod 3

1971

First penaids flight testing

September 20, 1967

Short-range flight testing . began

July 1968

First launch from operational site

November 11, 1970

Maximum operational launcher deployment

1971

SS-11/RS-10 in Launch Canister

SS-11/RS-10 Outside Launch Cannister

SS-11/RS-10 Stage 1

SS-11/RS-10 Emplacement Equipment

SS-11/RS-10 Emplacement Equipment 2

UR-100MR / SS-17 SPANKER The UR-100MR / SS-17 intercontinental ballistic missile is a two-stage, tandem, storable liquid-propellant missile intended to replace the light UR-100 SS-11 missile. It was a competing design with the SS-19 Stiletto, though in fact both were deployed. It was the first Soviet ICBM to have a Multiple Independently targetable Reentry Vehicle (MIRV) and the first to use a cold launch system. The UR-100MR / SS-17 intercontinental ballistic missile was assessed as being capable of delivering a throw-weight of 6,000 lb to a range of 5,500 nm. The throw-weight consists of a post-boost vehicle and either one or four reentry vehicles. The overall dimensions of the SS-17 were determined by the characteristics of the SS-11 UR-100 silos in which the UR-100MR missile was planned for deployment. The diameter of both stages was increased in relative to that of the UR-100, and is 2.25 m for the first and 2.1m for the second stage. The UR-100MR uses asymmetrical dimethylhydrazine and nitrogen tetraoxide propellants. The first stage uses a closed-cycle single-chambered sustainer engine and a four-chambered open-cycle control motor. The second stage is equipped with a single-chamber open-cycle sustainer, placed inside the lower part of the fuel tank. The flight control during the first stage uses deflecting the control motor chambers, while the second stage uses gas injected into the diverging part of the nozzles. Solid propellant retrorockets are used to separate the stages. The rocket MR UR-100 was placed in previously hardened SS-11 UR-100 silos. The missiles in their transport-launch canister were inserted into the silo with the use of two shock-absorption belts. The SS-17 uses a sabot cold launch or pop-up launch system that facilitated modifying existing SS-11 facilities. 

SS-17 Mod-1 - This initial version of the SS-17 carried 4 MIRV warhead with a yield of 0.3-0.75 Mt each, an instrument module with a command structure and solid-propellant rocket motor comprise the post-boost vehicle. According to Western estimates each RV weighed about 900 lbs. The missile had an inertial guidance system with an estimated CEP of 0.34 nm for 1975 and a potential CEP of 0.28 nm in 1980. Its development was approved in September 1970 and conducted by KB Yuzhnoye (OKB-586) which was headed by V. F. Utkin. Popup tests which improved the mortar launch technique began in May 1971. The full scale flight-design tests of Mod1 and 2 were conducted at the Baikonur cosmodrome test site from 26 December 1971 and 17 December1974. Flight testing was first detected by the West on 15 September 1972. The first regiment with MR UR-100 missiles was put on alert on 06 May 1975 and its deployment began on 30 December 1975.  SS-17 Mod-2 - The Mod-2 missile carries only a single warhead with a yield of 46 MT.  SS-17 Mod-3 - On 16 August 1976 a governmental order to improve the UR100MR performance characteristics was issued. The preliminary design of this MR UR-100UTTh missile known as SS-17 Mod3 was completed by KB

Yuzhnoye (OKB-586) in December 1976, receivingthe industrial index number 15A16. Like the SS-17 Mod-1 it carries four MIRV warheads, but it incorporated enhanced survivability and was equipped with an improved commando system and a modernized nose cone. The flight-design tests began on 25 October 1977 and were finished on 15 December 1979. The Mod-3 reached its IOC in 1978 and its deployment started on 17 December 1980 (simultaneously with the R36MUTTh). In 1979 130 missiles were deployed in two missile fields near Yedrovo and Kostroma. From 1979 till 1980 all single warheaded missiles were replace by MIRVed missiles. In the years 1982-1983 all MR UR-100 missiles as well as 20 UR-100 missiles were replaced by the MR UR-100UTTh missiles which reached their maximum operational inventory of 150 in 1983. When the START-1 treaty was signed in 1991 the Soviet Union had 47 launchers for the MR UR-100UTTh which were all subject to dismantling.

Specifications Mod-1

Mod-2

Mod-3

DIA

SS-17

SS-17

SS-17

NATO

Spanker

Spanker

Spanker

Bilateral

RS-16A

RS-16A

RS-16B

Service

MR-UR-100

MR-UR-100

MR-UR-100 UTTKh or MRUR-100U

OKB/Industry

15A15

15A15

15A16

Design Bureau

OKB-586 Acad. V. F. Utkin

OKB-586 Acad. V. F. Utkin

OKB-586 Acad. V. F. Utkin

Approved

9/1970

9/1969

8/16/1976

Years of R&D

1964-70

1964-70

Engineering and Testing

1971-74

1970-75

1977-79

First Flight Test

09/15/1972 failure 12/26/71 success

12/26/1971

10/25/1977

IOC

05/06/1975

1975

10/17/1978

Deployment Date

12/30/1975

12/30/1975

12/17/1980

Type of Warhead

MIRV

Single

MIRV

Warheads

4

1

4

Yield (Mt)

0.350-0.750

3.5-6.0

0.550 - 0.750

Payload (t)

2.550

2.550

2.550

Total length (m)

22.52

21.6 ? 22.52

23.9

Total length w/o

20.9

20.9

20.9

Missile Diameter (m)

2.25

2.25

2.25

Launch Weight (t)

71.1

71.1

71.1 - 72

Fuel Weight (t)

63.2

63.2

63.2

Range (km)

10,200 10,320

10,100 10,320

10,200 -11,000

CEP (m) 1,080 (Russian Sources)

1,080

920

CEP (m) 440-500 (Western Sources)

420-450

220-400

Warhead (m)

Number of Stages

2

Canister length (m)

21.6

Canister length w/o Front meters (m) Canister diameter (m)

2.5

Booster guidance system

Inertial, autonomous

1st stage

2nd stage

Length (m)

14.3, 14.9

3.2

Body diameter (m)

2.25

2.15

Fueled weight (t)

59.0

Dry weight (t) Engine Designation

RD-268 Main Engine

RD-262 (15D169)

Engine Designation

RD-263 Vernier Engine

N/A

Design Bureau

Acad. V. P. Glushko

Yuzhnoye

(OKB-456)

(OKB- 586)

Configuration

One Main Engine, One One Chamber Four Chamber Verniers Engine

Year of R & D main engines

1969-1973

1969-1972

Year of R & D Vernier engine

1970-1973

N/A

Propellants

Liquid

Liquid

Fuel

UDMH

UDMH

Oxidizer

Nitrogen Tetroxide

Nitrogen Tetroxide

Burning time (sec.)

130

195

Main Engine Thrust Sea Level/Vacuum (Tonnes)

117/126

14.5 44 Vacuum

Verniers Thrust Sea Level/Vacuum (Tonnes)

28.230 /?

N/A

Main Engine Specific Impulse Sea Level/Vacuum (sec.)

?/319

331 Vacuum

Vernier engine Specific Impulse Sea Level/Vacuum (sec.)

259/301

N/A

Basing Mode

Silo

Hardness Launching Technique

Mortar Launch

Deployed boosters Test Boosters Warheads Deployed Training Launchers Space Booster Variant

No

Deployment Sites START

Locale US-Designation

Kostroma

Kostroma

Vypolzovo

Yedrovo

SS-17/RS-16 in Launch Canister

SS-17/RS-16 Missile

SS-17/RS-16 and SS-19/RS-18 Emplacement Equipment

SS-17/RS-16 Stage 1

UR-100N / SS-19 STILLETO Once regarded by some as the "backbone" of the Soviet ICBM force, the fourth generation UR-100N / SS-19 intercontinental ballistic missile is a two-stage, tandem, storable liquid-propellant missile. The SS-19 is approxiamately 80 feet long and 8 1/2 feet in diameter. It was a competing design with the SS-17 Spanker, though in fact both were deployed to partially replace the SS-11 force. The UR-100N is similar to the UR-100, but with an increased diameter and longer propellant tanks its launch weight was more than doubled and the throw-weight was increased over three-fold. The UR-100N uses asymmetrical dimethylhidrazine and nitrogen tetraoxide propellants. The first stage consists of four autonomous closed-cycle single-chambered rocket motors. The second stage has a closed-cycle single chambered sustainer and a four chambered open cycle control motor with four rotating nozzles. The guidance and control system of the SS-19 is identical to that of the SS-18, and permits remote monitoring of missile status while on alert, as well as automatic pre-launch preparation, remote missile targeting before launch and in-flight control of the missile via a flexible pitch control program. The UR-100N silos were constructed at the same sites as the UR-100U silos but were completely dismantled and rebuilt to increase the survivability of the new missiles. The UR-100N was launched in the hot mode through the thrust of the first stage sustainer engine. The SS-19 has been deployed in three configurations. 

SS-19 Mod-1 - Through the increase of throw-weight and reduction of the size of the warheads relative to the UR-100 the UR-100N carries six MIRV warheads with a yield of 550 KT each according to Russian sources [Western estimates suggested a yield of one- to two-megatons]. According to Western estimates the booster alone was limited to a range of 4900 nm but the total system, booster plus PBV, was assessed as being capable of delivering all six RVs to a maximum range of 5200 nm. Development was approved on 19 August 1970 and developed by V. N. Chelomey. The flight tests of the UR-100N were conducted at the Baikonur cosmodrome from 09 April 1973 through October 1975. The missile was initially deployed on 30 December 1975, though according to Western estimates it achieved an initial operational capability in 1974. The first regiment with UR-100N missiles was put on alert on 26 April 1975 and by the end of 1975 a total of 60 launchers were deployed. The missile employed an inertial guidance system that was is estimated by some Western sources to have an operational CEP of 0.3 nm in 1975 with a potential CEP of 0.25 nm by 1980. However, due to the hasty deployment of the UR-100N a major design flaw was overlooked. Training launches that took place after its deployment revealed a significant reduction of accuracy due to resonant oscillations of the missile. Subsequently all deployed missiles were modified to eliminate the problems.  SS-19 Mod-2 - Otherwise similar to the Mod-1, this variant carries a single warhead with a yield reported by Russian sources of between 2.5 and 5 MT.

Between 1976 and 1978 the UR-100N reached its maximum operational inventory of 180 missiles, of which 60 carried a single warhead. Both of these SS19 Mods were attributed "hard target kill" capabilities by the West.  SS-19 Mod-3 -The development of an improved version was authorized on 16 August 1976. The upgrades to the missile involved the development of improved engines and modification of the command system. The extent of protection from a nuclear strike at their silos was considerably improved. The flight-design tests of the improved version that received the designation UR-100NUTTH were conducted between 26 June 1979 and 26 October 1979. Its deployment began on 05 November 1979. The first regiment with the UR-100NUTTH was put on alert on 06 November 1979. Between 1980-1982 UR-100N missiles with a single warhead (SS-19 Mod 2) were replaced by the UR-100NUTTH (SS-19 Mod 3). The replacement of all UR-100N missiles was completed in 1983. In 1984 the UR-100NUTTH reached its maximum operational inventory of 360 missiles. From 1987 on they were gradually replaced by new missiles. The silo-based version of the SS-24 replaced some SS-19s. When the START-1 treaty was signed in 1991 the Soviet Union had a total of 300 UR100NUTTH missile stationed in Russia and Ukraine. After the dissolution of the Soviet Union Ukraine claimed ownersip of the missiles located on its territory. In compliance with the START treaty provisions Ukraine is in charge of the dismantling the launchers for the SS-19 missiles. However, all nuclear warheads that were deployed in Ukraine were dismantled by Russia. Some 170 launchers remain in Russian territory, of which 10 were deactivated but not dismantled. In December 1995 Strategic Rocket Forces Commander Colonel General Igor Sergeyev announced a policy under which the service life of the SS-19 would be extended from 10 years to 25 years. The missiles will remain on alert at least through 2005, and the missiles that were deployed in the early 1980s will serve beoynd this. Following the ratification of the START-II treaty by the Duma, Russia is obliged to dismantle all ground-based ICBMs with multiple warheads. Under the treaty provisions a total of 105 of the UR-100NUTTH missiles can be retained provided they are downloaded to carry only one warhead instead of six.

Specifications Mod-1

Mod-2

Mod-3

DIA

SS-19

SS-19

SS-19

NATO

Stiletto

Stiletto

Stiletto

Bilateral

RS-18A

RS-18A UTTKh

RS-18B

Service

UR-100N

UR-100N

UR-100NU

OKB/Industry

15A30

15A30

15A35

Design Bureau

OKB-52, OKB-52, KB KB Salyut, Salyut,

OKB-52, KB Salyut,

Acad. V. N. Chelomey

Acad. V. N. Chelomey

Acad. V. N. Chelomey

Approved

8/19/1970

8/19/1970

8/16/1976

Years of R&D

1964-73

1964-1973

Engineering and

1973-75

1973-75

1977-79

Testing First Flight Test

9/15/1972 4/9/1973 failure & 12/28/1973 success

10/26/1977

IOC

4/26/1975

1979

Deployment Date

12/301975 12/30/1975

11/5/1979

Type of Warhead

MIRV

Single

MIRV

Warheads

6

1

6

Yield per Warhead (Mt)

0.5 0.55 0.750

2.5 - 5.0

0.5-0.75

Payload (t)

4.350

4.350

4.350

Total length (m)

24.0

24.0

24.3

Total length w/o

21.1

21.1

21.1

Missile Diameter (m)

2.50

2.50

2.50

Launch Weight (t)

103 105.6

105.6

103.4 - 105.6

Fuel Weight (t)

93.1

93.1

93.1

Range (km)

9,650

10,000

10,000

CEP (m)

?

?

920

1975

Warhead (m)

(Russian Sources)

CEP (m)

350-550

250-400

220-380

(Western Sources) Number of Stages

2

Canister length (m)

19.4

Canister length w/o front meters (m) Canister diameter (m)

2.9

Booster guidance system

Inertial 1st stage

2nd stage

3rd. Stage

Length (m)

17.2

2.8

Body diameter (m)

2.5

2.5

Fueled weight (t)

86.3

86.3

Engine Designation

RD-0233 / RD-0234

RD-0235 (14/15D113)

N/A

Vernier Engine Designation

N/A

RD-0236 (15D114)

N/A

Bus Engine Designation Third Stage

N/A

N/A

RD-0237

Design Bureau Main Engines

OKB-154, Acad. S. A. Kosberg

OKB-154, Acad. S. A. Kosberg

N/A

Design Bureau Vernier Engine

N/A

OKB-154, Acad. S. A. Kosberg

N/A

Design Bureau Bus Engine Third Stage

N/A

N/A

OKB-154, Acad. S. A. Kosberg

Configuration

Cluster of four engines

One engine

N/A

2.5

Dry weight (t)

Configuration Vernier Engine

N/A

Four vernier chambers

N/A

Configuration Bus engine Third Stage

N/A

N/A

Four chambers

Years of R & D

1969 1974

1969 - 1974

N/A

Years of R & D Vernier Engine

N/A

1969 - 1974

N/A

Years of R & D Bus Engine Third Stage

N/A

N/A

1969 - 1974

Propellants

Liquid

Liquid

Liquid

Fuel

UHMH

UDMH

UDMH

Oxidizer

Nitrogen Tetroxide

Nitrogen Tetroxide

Nitrogen Tetroxide

Burning time (sec.) Main Engine Thrust Sea Level/Vacuum (Tonnes)

46.961/52.958 - 53.1 24.5 Vacuum

N/A

Verniers Thrust Sea Level/Vacuum (Tonnes)

N/A

1.6 Vacuum

N/A

Third Stage Bus Engine Thrust Vacuum (Tonnes)

N/A

N/A

0.5 Vacuum

Total Thrust Sea Level/Vacuum (Tonnes)

187.8442/207.8319

30.9 Vacuum

2.0 Vacuum

Main Engine Specific Impulse Sea Level/ Vacuum (sec.)

291 / 310

320 Vacuum

N/A

Vernier Engine Specific Impulse Sea Level/Vacuum (sec.)

N/A

293 Vacuum

N/A

Bus Third Stage Engine Specific

N/A

N/A

?

Impulse Vacuum (sec.) Basing Mode

Silo

Hardness Launching Technique

Hot

Deployed boosters Test Boosters Warheads Deployed Training Launchers Space Booster Variant

Yes SL-X- ? , Rockot Deployment Sites

START

Locale US-Designation

Khmel?Nitskiy

Derazhnaya

Kozel?sk

Kozelsk

Pervomaysk

Permovaysk

Tatishchevo

Tatishchevo

SS-19/RS-18 in Launch Canister

SS-19/RS-18 Missile

SS-19/RS-18 Stage 1

SS-17/RS-16 and SS-19/RS-18 Emplacement Equipment

UR-200 / SS-X-10 SCRAG The 1961 Global Rocket 1 (GR-1) requirement chartered a competition for the development of a Fractional Orbital Bombardment System. Yangel offered the R-36. Korolev proposed the 8K713, which was cancelled in 1964 prior to flight testing due to engine delays. Chelomei proposed the UR-200, which was cancelled following the October 1964 ouster of downfall of Khrushchev, who had been Chelomey's political patron. The UR-200 intercontinental ballistic missile was a two-stage, tandem, cryogenic liquidpropellant missile with a nominal payload of approximately 7000 lb. With approximately the same launching weight as the R-16 missile (138.0 T), the UR-200 was designed to carry a very large payload (3.3 T or 2.7 T depending on the nose cone]. The UR-200 was unique in that it was the first and only Soviet ICBM for which attitude control during first-stage flight was provided by hinged/gimbaled engines. The missile was to be surface and silo launched from former R-16U silos. Development of the UR-200 was approved on 16 March 1961, to serve simultaneously as an ICBM and as a space launch vehicle. The UR-200 missile was the first missile to be developed by the NPO Mashinostroyeniya (OKB-52) under designer V. N. Chelomey. In November 1963 flight-design tests began at the Baikonur cosmodrome, and a total of nine launches were conducted, after which the program was terminated. The last flight test on 20 October 1964, was the only one to the 6,500 nm Pacific test range, and was apparently successful. The UR-200 was not deployed operationally. The UR-200 was initiated as a technologically conservative alternative to the SS-9 SCARP, and used cryogenic liquid fuel (Liquid Oxygen and Kerosene). The successful development of the storable hypergolic propellants on the SS-9 rendered this approach obsolete, and in 1965 the development of the UR-200 missile was cancelled. The exact reasons for terminating the SS-10 weapon system program are unknown, but are believed to be related to the probable use of a cryogenic propellant combination and the success of the SS-9 weapon system. The UR-200 flight tests were associated with the designation SS-X-10, although Western intelligence mistakenly associated these flights with the GR-1 missile that was displayed in parades in Red Square. Although the GR-1 missile had not been flight tested, it was paraded in Red Square and did receive the US-designation SS-X-10 SCRAG. The GR-1 missile was correctly identified as being a FOBS configuration, although open sources at the time evidently assumed that the FOBS parading in Red Square and the FOBS undergoing flight tests were the same system. In fact, the initial FOBS flight tests were conducted by the competing UR-200 missile. It is unclear when US intelligence understood that the parade missile and the test missile were two different systems.

Specifications DIA

SS-X-10

NATO

N/A

Bilateral

N/A

Service

UR-200/UR-200B

OKB/Industry

8K81/8K83

Design Bureau

OKB-52 , KB Salyut, Acad V. N. Chelomey

Approved

3/16/1961 & 8/1/1961

Years of R&D

1961-1964

Engineering and Testing

1963-1964

First Flight Test

11/4/1963

IOC

Not operational

Deployment Date

Not deployed, terminated 1964/1965

Type of Warhead

1

Warheads

Single

Yield (Mt)

5 & 15

Payload (t)

2.690 - 3.9 - 4.0

Total length

34.65

Total length w/o warhead

30 – 32

Missile Diameter

3

Diameter of Stabilizers

4.2

Launch Weight (t)

136 -138

Fuel Weight (t) Range (km)

12000 & 14000

CEP (m) (Russian Sources) CEP (m) (Western Sources)

1800-5500

Number of Stages

2

Canister length (m)

Canister length w/o Front meters (m) Canister diameter (m) Booster guidance system

Length (m) Body diameter (m) Fueled weight (t) Dry weight (t) Engine Designation Main Engines Vernier Engine Designation Design Bureau Configuration Years Of R & D Propellants Fuel Oxidizer Burning time (sec.) Main Engine Thrust Sea Level/Vacuum (Tonnes) Vernier Engine Thrust Sea Level/Vacuum (Tonnes) Total Thrust Sea Level/Vacuum (Tonnes) Specific Impulse Main Engines (sec.) Specific Impulse Vernier engine (sec.) Basing Mode Hardness

Inertial autonomous with radio correction

1st stage 16.9 – 19.4 3

2nd stage 12.9 2.2

RD-0203/RD-0204

RD-0206/RD-0207 (8D46)

(8D44/8D45) N/A

Four Verniers

OKB-154, Acad. S, A, Kosberg Cluster of Four Engine 1961-1964

OKB-154, Acad. S, A, Kosberg

Liquid UDMH (AT) Nitrogen Tetroxide

Liquid UDMH (AT) Nitrogen Tetroxide

50.0/57.0

58.7 Vacuum

N/A

3.1 Vacuum

200

62.5 - 71.1 Vacuum

278/311

297

N/A

322 - 326

One Main Engine and Four Verniers 1961-1964

Soft Site Land Based N/.A

Launching Technique Deployed boosters Test Boosters Warheads Deployed Deployment Sites Training Launchers Space Booster Variant

Hot N/A

N/A N/A No

UR-500 / [PROTON] On 09 August 1961, Premier Nikita Khrushchev openly threatened the West with a new and terrifying weapon, the orbital H-bomb. "You do not have 50- or 100-megaton bombs, we have bombs more powerful than 100 megatons. We placed Gagarin and Titov in space, and we can replace them with other loads that can be directed to any place on Earth." Although the US had hypothesized orbital bombs, this was the first public indication that the Soviets were actively pursuing this course of action. Within a few months, however, American analysis of the threat diminished its proportions.

Specifications Mod-1 = 2 Stages

Mod-2 = 3 Stages

DIA

SS-LX-? " City Buster" ICBM

SS-LX-? FOBS

NATO

N/A

N/A

Bilateral

N/A

N/A

Service

UR-500

UR-500, UR500K

OKB/Industry

(8K82)

(8K82)/(8K82K)

Design Bureau

OKB-52 Acad. V.N. Chelomey

OKB-52 Acad. V.N. Chelomey

Approved

4/2429/1962

4/24- 29/1962

Cancellation

ICBM 5/15/1964

ICBM 5/15/1964

Years of R&D

1961-1965

1961-1967

Engineering and Testing

1962-1965

1962-1970

First Flight Test

7/16/1965

11/22/67

IOC

N/A

N/A

Deployment Date

N/A

N/A

Type of Warhead

1

1

Warheads

Single

Single

Yield (Mt)

50 – 100 – 150

30 – 50 (45 –55)

(35-45) Payload (t)

12.2 - 14

14.0 –17.0

Total length (m)

37 – 46.28

Total length

30.68

44.3

Missile Diameter (m)

7.4 with 1.6 strap-on tanks, 4.1 core tank

7.4 with 1.6 strapon tanks, 4.1 core tank

Launch Weight (t)

600

620 - 621.9

Range (km)

10,000

12,000

CEP (m) (Russian Sources)

N/A

N/A

CEP (m) (Western Sources)

N/A

N/A

Basing Mode

Hardened launch complex

Hardened launch complex

w/o warhead (m)

Fuel Weight (t)

Number of Stages Canister length w/o front meters (m)

2 N/A

3 N/A

Canister diameter (m)

N/A N.A

N/A N/A

Booster guidance system

Length (m)

Inertial Inertial autonomous autonomous st 1 stage 2nd stage 3rd. Stage 21.07 – 21.18 Strap-on 14.56 6.857 Tanks 19.9

Body diameter (m)

7.4 With 1.6 Strap-on Tanks, 4.1 Core Tank 449.8 32.5 – 34.5 RD-253 (11D48)(11D43)

4.1

4.1 46.562 4.185 RD-0210/RD0211 or RD0213/RD-0214

Vernier Engine Designation

N/A

172.1 12.1 RD-0208/RD0209 or (three)RD0210/(one)RD0211 N/A

Configuration Design Bureau

Cluster of Six Engines OKB-456, Acad. V. P. Glushko

Years of R&D Propellants Fuel Oxidizer

1961-1965 Liquid UDMH N204 = Nitrogen Tetroxide

Burning time (sec.) Verniers Thrust Sea Level/Vacuum (Tonnes) Main engines Thrust Sea Level/Vacuum (Tonnes) Total Thrust Sea Level/Vacuum (Tonnes)

127 - 130 N/A

RD-0214 Four Chamber Vernier Engine Four Engine One Engine OKB- 154 OKB-154, Acad. S. A. Acad. S. A. Kosberg Kosberg 1961-1964 1961 – 1967 Liquid Liquid UDMH UDMH N204 = N204 = Nitrogen Nitrogen Tetroxide Tetroxide 210-230 240 ? 3.21 x 4 = 12.8493 Vacuum 233.6 Vacuum 58.4 Vacuum

Main Engines Specific Impulse Sea Level/Vacuum (sec.) Vernier Engine Specific Impulse Sea Level/Vacuum (sec.) Hardness Launching Technique Deployed boosters Test Boosters Warheads Deployed

284.9/310.0

4 x 58.4 – 59.4 58.4 – 59.4 + = 233.6 12.8493 = Vacuum 71.2493 Vacuum 326.5 326.5

N/A

N/A

Fueled weight (t) Dry weight (t) Main Engine Designation

147 – 148.8884 – 150.25 / 166.7347 6 x 147 - 150.25 = 901.5

N/A Hot launch N/A N/A N/A

?

Training Launchers Space Booster Variant

N/A SL-LX-?, SL-9/Proton/D, Proton 1-3B SL-12/Proton K, Zond, (UR-500L1), Lunar, Venera, Mars,

START N/A

SL-13/Proton K, Proton-4, Salyut, Mir, Proton-K Locale US-Designation N/A

RT-1 ICBM Specifications DIA NATO Bilateral Service

RT-1

RT-1-63

OKB/Industry

(8k95-63)

(8K95-1963)

Design Bureau

OKB-1, Acad. S. P. Korolev

OKB-1, Acad. S. P. Korolev

Approved

11-20-59

11-20-59

Years of R&D

1958/59 -1962

1962,1963/1964

Engineering and Testing

1960 –1963

1962 -1963

First Flight Test

04/28/1962 failure 3/18/1963 success cancelled

9-11/ /1965, 2 failures one success cancelled

IOC

N/A

N/A

Deployment Date

N/A

N/A

Type of Warhead

Single

Single

Warheads

1

1

Yield (Mt)

0.5 -1.0

0.6 -1.0

Payload (t)

0.5 - 0.8

0.8

Total length (m)

18.0

18.3

Missile Diameter (m)

2.0

2.0

Launch Weight (t)

35.5-36.0 (34)

34 –35.5

1,850-2,000

2,400-2,500

Total length w/o warhead (m)

Fuel Weight (t) Range (km) CEP (m) (Russian Sources)

CEP (m) Western Sources) Number of Stages Canister length (m) Canister length w/o front meters (m) Canister diameter (m) Booster guidance system

3

Inertial st

Length (m) Body diameter (m) Fueled weight (t) Dry weight (t) Engine Designation configuration Design Bureau Years of R & D Propellants

Inertial 2 stage 3rd Stage 3.9-4.0 2.8 1.5 x 4 1.4 nd

1 stage 4.6-4.8 1.6 x 4

Solid Propellant

Fuel

Solid Propellant

Oxidizer

Solid Propellant

Burning time (sec.)

Thrust Sea Level/Vacuum 100 (Tonnes) Specific Impulse Sea 204 Level/Vacuum (sec.) Basing Mode Hardness Launching Technique Deployed boosters Test Boosters Warheads Deployed Deployment Sites Training Launchers Space Booster Variant

3

Solid Solid Propellant Propellant Solid Solid Propellant Propellant Solid Solid Propellant Propellant 30 17.5 -30 30 - 42 32 51 25 223

N/A Hot Launch 0 0 0 0 N/A

RT-2 - SS-13 SAVAGE The RT-2 is a three-stage missile with sequentially arranged stages and a single reentry vehicle. According to Western estimates, the missile was capable of delivering a 1200 lb reentry vehicle to a maximum operational range of 5500 nm with a CEP in the range of 0.7 to 1.0 nm. The three sustainer stages, using solid-propellant motors, were connected by trellised trusses. Four trellised aerodynamic stabilizers were used to stabilize the missile during the active trajectory leg. The flight control was implemented with the help of four split nozzles. With a nose cone of 500 kg it had a maximum range of 10,00012,000 km, which was reduced to 4,000-5,000 km when employing a heavier nose cone of 1,400 kg. The guidance/control system incorporated a gyro-stabilized platform with floating gyros and pendulous accelerometers. Three variants of the SS-13 reentry vehicle have been identified. The Mod 1 variant had a ballistic coefficient of approximately 300 lb per sq ft and a CEP assessed in the West of about 1.0 nm. The Mod 2 has a ballistic coefficient of approximately 730 lb per sq ft and a CEP assessed at about 0.7 nm. Both had a yield in the range 0.6 to 1.5 MT, according to Western sources. The system was deployed in hardened and dispersed unmanned silos. Silo and launch control hardness was estimated by Western sources at 1300 psi overpressure. Because of the heavy weight of the missile it was transported in parts. The first stage was separated from the second and third stage. The assembly of a missile was directly carried out in the silo. The silo door was sealed and the ensuing special climate conditions in the silo guaranteed an extended storage of the solid-propellant. The missile launch was effected through a new technique that was essentially the breadboard of a subsequently used method called "mortar launch". Water was poured into the bottom of the launch canister, while in the tail unit of the missile a shroud provided for isolation. During the ignition of the first sustainer stage the steam that formed underneath the missile popped the missile out of the silo. The readiness for missile firing was 3-5 minutes. A railway based version of the RT-2 missile was also studied, but the project never advanced beyond the preliminary design phase. The task of developing a solid-fuel missiles with a range of 10-12 thousand kilometers was approved by the ministerial Council on 20 November 1959, with Korolev's OKB-1 in charge of carrying out the design. The development of this ICBM was scheduled to be conducted in two separate phases. The first phase provided for the development of a missile designated as RT-1 with a range of 2500-3000 kms using solid fuel. The RT-1 missile was developed and underwent flight test but was not deployed. With a launch weight of 35.5 T and a payload of 800 kg it had a limited range of only 2,000 km, the same as the R-12.

The preliminary design of the RT-2 missile was finished in 1963. The flight tests were conducted in two phases from February 1966 through November 1968. It was first detected by Western intelligence during a 1,050 nm short-range flight test on 26 February 1966. During the first phase of tests, from February through July 1966, seven successful launches from the test site in Kapustin Yar were carried out. The missiles were launched from adapted silos and the nose cones were successfully deployed. During the second test phase between 03 October 1966 and 04 November 4, a total of 16 successful missile firings out of a total of 25 launches took place on the test site in Plesetsk. A total of 21 of the 25 missiles were tested on an intermediate range basis with the nose cone falling on a training site on Kamchatka and four were tested on maximum range with the nose cone falling into the Pacific Ocean. On 18 December 1968 deployment of the RT-2 missile began. According to Western estimates, the initial operational capability was probably achieved in 1969. Maximum deployment was reached in 1972. The missile deployment areas of missiles RT-2 were organized in area of Yoshkar Ola. Despite the hardness of the silos and the relative simplicity of operation, the operational capabilities of the RT-2 were limited due to a small throw-weight and the short operational lifetime of the solid-propellant motors. These characteristics limited the deployment to only 60 RT-2 missiles. In 1968 the development of a modernized version with a sophisticated control system and countermeasures for overcoming an ABM system was undertaken by KB Arsenal. The missile received the designation RT-2P. The flight tests RT-2P were conducted from December 1969 tthrough January 1972, and on 28 December 1972 the first missiles were deployed. In 1974 the RT-2M variant was deployed. This system was developed by Nadiradize, which finally took over the program in 1973. The expected service time of the RT-2 and RT-2Ps were estimated to be 10 years. Periodic static tests of motors on firing stands which were carried out after extended storage allowed an extension of the time the missiles could remain in service. The missiles remained in service for more than twenty years, and were phased out by the middle of 1996. Some have been replaced by the "Topol" missile.

Specifications Mod-1

Mod-2

Mod-3

DIA

SS-13

SS-13

SS-13

NATO

Savage

Savage

Savage

Bilateral

RS-12

RS-12

RS-12

Service

RT-2

RT-2P

RT-2M

OKB/Industry

8K98

8K98P

8K98M

Design Bureau

OKB-1, Acad. S. P. Korolev

OKB-1 Acad. S. P. Korolev & TsKB-7, Arsenal, Acad. A. D. Nadiradize which finally took over in 1973

TsKB-7, Arsenal, Acad. A. D. Nadiradize which finally took over in 1973

Approved

04/04/1961

12/18/1968

Years of R&D

1958-68

1969-72

Engineering and Testing

1966-68

1969-72

First Flight Test

2/26/1966 IRBM & 11/4/1966 ICBM

01/16/1970

IOC

7-1-1969

1972

Deployment Date

12/18/1968

12/28/1972

1974

Type of Warhead

Single

Single

Single

Warheads

1

1

1

Yield (Mt) Russian Sources

0.75-1.0

0.75-1.65

.466-.467

Yield (Mt) Western Sources

0.6-1.5

0.6-1.5

Payload (t)

0.545

0.6-1.4

0.5- 1.0

Total length (m)

21.27

21.265

21.13

Total length w/o warhead (m)

19.7

19.66 ? 19.7

19.8

Missile Diameter (m)

1.95

1.95,

2.0

Diameter of Stabilizers (m)

3.618

3.618

3.618

Launch Weight (t)

46.1 ? 51

51.6 ? 51.9

50

Fuel Weight (t)

43.9

43.9

Range (km)

9,400 ? 9,500

10,000-10,200 10,000

CEP (m) (Russian Sources)

1,800 - 2,000

1,300 ?1,500

1,500 - 1,800

CEP (m) (Western Sources)

1,850 - 2,000

1,500 ?1800

Number of Stages

3

Canister length (m)

N/A

Canister length w/o front meters (m)

N/A

Canister diameter (m)

N/A

Booster guidance system

Inertial, autonomous

1st stage

2nd stage

3rd stage

Mod1

Mod2

Mod3 Mod1

Mod2

Mod3 Mod1

Mod2

Mod3

8.7

9.2

9.29.5

4.74

5.08

4.8

3.827

5.45

4.5-4.7

Body diameter (m) 1.84

1.84

1.9

1.49

1.49

1.5

0.981.06

0.981.06

1.0

Fueled weight (t)

34.55

34.55

35

9.6

11.28

3,5

4.64

?

Dry weight (t)

30.6730.8

30.8

3.6

?

Solid Motor Designation

15D23 15D23P

Propellants- Solid Propellants

Solid

Solid

Burning time

75.37

Length (m)

9.78 15D24 15D24P1 Solid

Solid

Solid

75.37

59

Solid Motor Thrust 91 Sea Level/Vacuum (Tonnes)

100

44

Specific Impulse (sec)

237 / 263

15D25 15D94 15D31/94 Solid

Solid

Solid

60.6

45-46

49

44.6 44.77

22

18

269.5

Basing Mode

Silo

Hardness

1290 psi/LCC at 1430 psi

Launching Mode

Hot

Deployed boosters

40

Test Boosters

8

271

Solid

Warheads Deployed

40

Training Launchers

2

Space Booster Variant

No Deployment Sites

START

Locale US-Designation

Yoshkar Ola

Yoshkar Ola

SS-13/RS-12 Emplacement Equipment

SS-13/RS-12, Stage 1

SS-13/RS-12, Stages 2 and 3 as a Unit

RT-20P / SS-15 SCROOGE The RT-20P missile was the first Soviet mobile ICBM, although Western sources generally viewed the SS-X-15 as a theater-range ballistic missile. Western intelligence correctly determined that the missile had a storable liquid-propellant second stage, but uncertainty remained as to whether the first stage used either a liquid or solid propellants. Western sources were also puzzled as to whether the missile was a two- or three-stage system. The RT-20P was a two-stage missile which was unique in using dis-similar solid and liquid propellants in the first and second stages -- the first stage used solid propellant while the second stage used liquid propellants. The engine of the first stage featured four rotating nozzles to conduct flight control. The second stage had a single chambered sustainer using asymmetrical dimethylhydrazine and nitrogen tetraoxide. The flight control of the missile was attained by injecting spent turbine gas into the diverging part of the four sustainer nozzle. With a launch weight of 30.2 tons, according to Russian sources the missile could either carry a payload of 545 kg delivering a single warhead with a yield of 550 Kt up to 11,000 km, or a payload of 1410 kg and a 1.5 Mt warhead up to 8,000 km. Western sources believed that the missile was capable of delivering a 1000-lb reentry vehicle to a range of 5,300 nm with a CEP of 1.0 to 1.5 nm. During the development of the RT-20P three different basing modes were considered: road-mobile, railway and silo, but only the road-mobile basing mode was actually developed realized. The missile was placed in a transport-launch canister and fired from a automotive launcher created on the basis of a heavy T-YUM tank. The launch from the container was conducted using the mortar launch technique. A new command structure substantially increased the time the missile could be maintained in an operational mode. The missile had an inertial guidance system, and the application of new high-precision gyroscopic devices allowed improved accuracy. Additionally, an improved capability for remote input of mission data implemented. The missile was designed by KB Yuzhnoye (OKB-586) which finished the design in December 1964. On 24 August 1965 its development was officially approved. Although the missile was first displayed in the Moscow parade of November 1965, the flight test program did not begin until October 1967. Apparently the first test associated by Western intelligence with this program was detected on 12 February 1968. This test was a failure. A total of nine test launches were conducted from the Plesetsk test site. After a total of eight detected flight tests, the program apparently was abandoned following a successful flight on 07 August 1967. The development of the RT-20P missile was officially halted in October 1969, and the SS-X-15 was not deployed operationally.

Specifications DIA

SS-X-15 (SS-XZ-15)

NATO

Scrooge

Bilateral Service

RT-20P RT-20PII - silo version

OKB/Industry

8K99 (15II696)

Years of R&D

1965-1969

Design Bureau

OKB-586 (Acad. M. K. Yangel)

Approved

8/24/1965

Engineering and Testing

1963-1967/69

First Flight Test

10/1967

IOC

1969

Deployment Date

Not deployed 10/__/1969

Type of Warhead

Single

Warheads

1

Yield (Mt)

0.5 or 1.5

Payload (t)

0.545 or 1.410

Total length (m)

17.48-17.8

Total length w/o warhead (m)

16.2

Missile Diameter (m)

1.8

Launch Weight (t)

30-30.2

Fuel Weight (t)

25.4

Range (km)

11000 or 7000-8000

CEP (m) (Russian Sources)

2000-4000

CEP (m) (Western 600-1800 Sources) Number of Stages Canister length (m) Canister length w/o front meters (m) Canister diameter (m)

2 18.90 NA 2

Booster guidance system 1st stage Length (m) 6.12 Body diameter (m) 1.8 Fueled weight (t) 16.7 Dry weight (t) Liquid Engine N/A Designation Solid Motor RDTT 15D15 Designation Design Bureau Years of R&D Propellants Solid Fuel N/A Oxidizer N/A Burning time (sec.) Thrust Sea Level /

2nd stage 8.4 1.8 8.9 RD-857 (15D12) (8K94) N/A Acad. M. K. Yangel 1963-1967 terminated Liquid Storable UDMH AT=AK-27P, N204, Nitrogen Tetrioxide

210 + 5 60

Vacuum (Tonnes) Specific Impulse Sea ? Level/Vacuum (sec.) Basing Mode Hardness Launching Technique Deployed boosters Test Boosters Warheads Deployed Deployment Sites Training Launchers Space Booster Variant

114-115

329.5 vacuum Ground mobile & silo concept (SLBM?) Cold 0 0

NA

RT-21 / SS-16 SINNER The "Temp-2S" missile was the first attempt to develop a mobile ICBM. that received the western designations SS-X-16 Sinner, According to Western assessments, the SS-16 probably was intended originally for both silo and mobile deployment, using equipment and a basing arrangement comparable to that used with the SS-20. The RT-21/SS-16 intercontinental ballistic missile is a three-stage, tandem, solid-propellant missile with a post-boost vehicle (PBV) operating after third-stage burnout. The SS-16 is 65 feet long and 6 1/2 feet in diameter. Although equipped with the same bus system as the SS-20 mobile missile, the SS-16 was never tested in a MIRV configuration. The Temp-2S was a three-stage solid-propellant missile with an autonomous inertial guidance/control system. It was started from a transport launch canister. The container was installed on the mobile launcher on a wheel landing gear. With a launching weight of 44 tons the rocket could deliver a payload of 940 kg to a maximum range of 9,000 km according to Russian sources. It carried a single warhead with a yield of 0.65-1.5 Mt and a CEP of 450 m to 1640 m according to Russian sources. The missile was assessed by Western intelligence to be capable of delivering a throw-weight of about 2,100 lb to a range of 5,000 nm, with the PBV providing the capability for an additional range increment of about 500 nm for the 1,000-lb class reentry vehicle known to have been tested. The missile used an inertial guidance system providing a CEP assessed by Western intelligence to be about 0.4 nm. The development of the missile began with a decree of the Ministerial Council on 10 July 1969. The main developer was the Moscow Institute of Thermal Technology under its chief designer A. D. Nadiradzye. The flight tests of the "Temp- 2S" began on 14 March 1972, which was detected by Western intelligence. Through the end of1974 a total of 26 missile launches were conducted on the training site in Plesetsk. The last missile firing that took place in April 1976 ended in failure. According to Russian sources the SS-16 Temp-2S was not introduced into the operational inventory, although Russian sources affirm that the first two rocket regiments equipped with the "Temp-2S" were put on alert on 21 February 1976. According to Western estimates, the SS-16 was deployed beginning in 1978. According to Western sources, at the time of the signing of the SALT II Treaty in June 1979 as many as 200 missiles had been built, of which as many as 60 were stored on the test training site in Plesetsk. According to Western data by the middle of 1978 as many as 50 missiles could have been deployed in Plesetsk. As of 1983 the American assessment was that available information did not allow a conclusive judgment on whether the Soviets deployed the SS-16, but did indicate probable deployment. The Soviet Union agreed in SALT II not to produce, test, or deploy ICBMs of the SS-16 type and, in particular, not to produce the SS-16 third stage, the RV or the appropriate device for targeting the RV of that missile. The missile appeared to share a number of components with the Soviet SS-20, an intermediate range ballistic missile (IRBM). As

the Parties had agreed that land-based launchers of ballistic missiles which are not ICBMs should not be converted into launchers of ICBMs, the United States sought this ban on the SS-16 in order to prevent verification problems which might have arisen if the SS-16 program had gone forward, since in that case distinguishing between SS-16 and SS-20 deployments would have been very difficult. In 1985 the US government determined that somewhat ambiguous evidence indicated that the SS-16 activities at Plesetsk were a probable violation of SALT II, which banned SS-16 deployment. By 1985 all supporting equipment had been removed from the training sites and the INFTreaty finally ruled out the deployment of the SS-X-16.

Specifications DIA

SS-16

NATO

Sinner

Bilateral

RS-14

Service

RS-14/Temp-2S

OKB/Industry

15Zh42

Design Bureau

(MIT) Moscow Institute of Thermal Technology, NII-1, Acad. A. D. Nadiradze

Approved

3/6/1966 - 3/ 4/1966 IRBM, 7/10/1969 officially

Years of R&D

1964-73

Engineering and Testing

1972-74

First Flight Test

3/14/1972

IOC

2/21/1976, Halted in 1977

Deployment Date

3/11/1976 Late 1975 - US Estimate

Type of Warhead

Single

Warheads

1

Yield (Mt)

0.65-1.500

Payload (t)

0.940

Total length (m)

18.50

Total length w/o warhead (m)

16.9

Missile Diameter (m)

1.79

Launch Weight (t)

41.5 - 44.2

Fuel Weight (t) Range (km)

9,200-10,500

CEP (m) (Russian Sources)

450-1,640

CEP (m) (Western Sources)

360-480

Number of Stages

3

Canister length (m)

20.01

Canister length w/o front meters (m) Canister diameter (m)

3.22

Booster guidance system

Inertial, autonomous

1st stage

2nd stage

3rd stage

Length (m)

8.58

4.4

3.9

Body diameter (m)

1.79

1.47

1.3

Fueled weight (t)

26.63

8.7

8.7

Solid Propellant

Solid Propellant

Solid Propellant

Specific Impulse Sea Level/Vacuum (Sec.)

Vacuum

Vacuum

Basing Mode

Ground mobile

Dry weight (t) Solid Motor Designation Propellants Burning time (sec.) Solid Motor Thrust Sea Level/Vacuum (Tonnes)

Hardness

Bus Stage

Launching Technique

Mortar Cold Launch

Deployed boosters Test Boosters Warheads Deployed Deployment Sites Training Launchers Space Booster Variant

No

RT-2PM - SS-25 SICKLE Approximately the size of the U.S. Minuteman ICBM, the SS-25 carries a single-warhead atop a three stage system. The SS-25 is road mobile, making the missile inherently survivable and capable of reload/refire operations. It can fire from field deployment sites or through the sliding roof garage it occupies at its base. The SS-25 joined operational Soviet SRF regiments in 1985. A total area of approximately 190,000 square kilometers could be required to deploy a force consisting of 500 road-mobile SS-25 ICBMs. A much higher number of personnel for the maintenance of the mobile versions than for the fixed missiles, and the maintenance and operation of mobile ICBMs are significantly more expensive. The three stage solid propellant RT-2PM Topol became the first Soviet mobile ICBM. It was deployed after almost two decades of unsuccessful attempts undertaken by different design bureaus. It emerged from the line of development of mobile missiles such as the SS-X-16 Temp-2S and the 'SS-20 Pioneer, and was deployed as a replacement for the widely deployed SS-11 SEGO. All three stages are made of composite materials. During the first stage operation the flight control is implemented through four aerodynamic and four jet vanes. Four similar trellised aerodynamic surfaces serve for stabilization. During the second and third stage of flight gas is injected into the diverging part of the nozzle.With a throw-weight of 1000 kg the "Topol" carries a single warhead with a yield of 550 Kt and an accuracy (CEP) of 900m according to Russian sources [or 300m according to Western sources]. The missile is deployed in a transport-launch canister stationed on a mobile launch vehicle. The Transporter Erector Launcher is mounted on cross-country 7-axle chassis which incorprates jacks, gas and hydraulic drives and cylinders, with a power of several hundred tons, for jacking and leveling of the launcher, speeded up (combat) and slowed down (maintenance) elevation of the container with the missile to the vertical position. The TEL is accompanied by a Mobile command post, which carries support facilities mounted on cross-country 4-axle chassis with unified vans. The complex is equipped with an onboard inertial navigation system which provides a capability to conduct the launch independently from its field deployment sites. This topo-geodesic support and navigation subsystem, created by the “Signal” Research Institute, provides a quick and highly precise tie-in of the launcher in a field position and enables its crew to carry out missile launches from any combat patrol route point. The launch can also be carried out at regimental bases from the garrison garage, which has a sliding roof. The order to begin the development of this missile was approved on July 19, 1977 and carried out by the Moscow Institute of Thermal Technology headed by A. D. Nadiradzye. The flight tests were conducted on the Plesetsk test site from 08 February through 23 December 1985. During this period the battle management system constituted the main problem that had to be resolved. After the first test series was successfully conducted in April 1985, the first regiment with Topol missiles was put on 23 July 1985. Through this

time work on improving the battle management system continued. The first regiment with "Topol"-missiles employing a modernized mobile command center (in area the of Irkutsk) were put on alert on 27 May 1988. The test missile firings were finally completed on 23 December 1987. At the time of the signing of the Start-1 treaty in 1991 the Soviet Union had deployed some 288 Topol missiles. Deployment continued, and at the end of 1996 a total of 360 Topol missiles were deployed. The Topol missile was deployed at previously developed deployment sites. After the INF-Treaty was signed in 1987 several SS-20 Pioneer deployment sites were adapted for the SS-25 Topol missiles. The United States expressed specific concerns during the INF treaty negotiations. When the SS-25 missile system was deployed in the field, with its missile inside the canister and mounted on the launcher, the US contended that the canister might conceal an SS-20 missile. The one distinguishing characteristic between the two systems, US treaty negotiators argued, was that the SS-25 had a single nuclear warhead, while the SS-20 had three warheads. After considerable discussion, the Soviet Union agreed to a provision in the treaty allowing the inspecting party the right to use radiation detection equipment to measure the fast neutron intensity flux emanating from the launch canister. A launch canister with a missile inside containing a single warhead (SS-25) emitted a different pattern of fast neutrons than did one with a missile having three warheads (SS-20). In the Memorandum of Agreement of 21 December 1989, the USSR and the U.S. agreed on procedures on how measurements would be taken during an on-site inspection. As the provisions of the SALT-2 agreement prohibited the deployment of more than one new missile (which became RT-23UTTh), it was officially declared by the Soviet Union that the SS-25 Topol was developed to upgrade the silo based SS-13 RT-2P. The US government disputed this view, contending that the missile was clearly more than 5% larger and had twice the throw-weight as the SS-13. An SS-25 with two MIRVs may have been tested in 1991, and the missile was tested at least once with four MIRV warheads, but no further development of a mutiple warhead version was carried out. This became an issue during the conclusion of the 1991 START negotiations, at which time the US pressed for a definition of "downloading" (removing warheads from missiles) that would complicate any Soviet attempt suddenly to deploy multiple warheads on the SS-25. Russia plans to to reequip approximately 400 silos in which obsolete SS-11, SS-13 and SS-17 missiles are located. Under the START-II Treaty Russia is permitted to place 90 single- warhead solid fuel missiles in reequipped SS-18 ICBM silos. On-site inspection of SS-18 heavy ICBM silo conversions, to guard against a break-out scenario involving speedy reconversion of SS-18 silos, is one particularly important aspect of START II verification in accordance with the Protocol on Procedures Governing Elimination of Heavy ICBMs and on Procedures Governing Conversion of Silo Launchers of Heavy ICBMs. US inspectors could either physically witness the pouring of the five meters of

concrete in the bottom of the silo or measure silo depth before and after the concrete was poured. Although the Treaty prohibits emplacement in such converted silos of a missile with a launch canister greater than 2.5 meters in diameter, and the Russians have undertaken a political commitment to deploy in these converted launchers only a singlewarhead ICBMs of the SS-25 type, the possibility exists that Russia could further modify the converted SS-18 silos to enable them to launch a different missile than the one declared. The breakup of the Soviet Union had a significant impact on the Topol program. The Minsk Wheeled Truck-Tractor Manufacturing Plant [MAZ] in Belarus manufactured the missiles' transporter launchers, and some 90% of the components of the guidance system were manufactured in Ukraine. In Belarus, as of December 1995, 63 SS-25 ICBMs originally deployed there had been returned to Russia. As of December 1995, Belarus had two operational SS-25 mobile ICBM regiments remaining on its territory, with a total of 18 nuclear warheads. In July 1992, Belarus signed an agreement with Russia placing the regiments under exclusive Russian control. In September 1993, Moscow and Minsk signed an agreement requiring the return of these nuclear missiles and all related missile support equipment to Russia by the end of 1996. A total of 81 SS-25 ICBMs and associated warheads were returned to Russia from Belarus. By the late 1990s the lack of resources and qualified personnel forced the Russian Navy to cut back operations considerably, with no more than one or two regiments of the mobile SS-25 missiles dispersed in the field. The remaining 40 or so regiments, each with nine single-warhead missiles, remain in garrison.

Specifications DIA

PL-5 & SS-25

NATO

Sickle

Bilateral

RS-12M

Service

RT-2PM/Topol

OKB/Industry

15Zh58

Design Bureau

(MIT) Moscow Institute of Thermal Technology, Acad. A. D. Nadiradze

Approved

7/19/1977

Years of R&D

1974-80

Engineering and Testing

1980-85

First Flight test

10/27/1982 failure, 2/8/1983 success

IOC

7/23/1985 authorized, 8/2/1985

operational Deployment Date

12/1/1988

Type of Warhead

Single

Warheads

1

Yield (Mt)

0.550

Payload (kg)

1,000 ? 1,200

Total length (m)

20.5 - 21.5

Total length w/o warhead (m)

18.5

Missile Diameter (m)

1.80

Launch Weight (t)

45.1

Fuel Weight (t) Range (km)

10,500

CEP (m) (Russian Sources)

900

CEP (m) (Western Sources)

150-250

Number of Stages

3

Canister length (m)

22.3

Canister length w/o front

20.0

Meters (m) Canister diameter (m)

2.0

Booster guidance system

Inertial, autonomous

1st stage

2nd stage

3rd stage

4th.

Length (m)

8.1

4.6

3.9

2.1

Body diameter (m)

1.86

1.55

1.34

0.8

Fueled weight (t)

27.8

Solid Propellant

Solid

Dry weight (t) Solid Motor Designation Propellants

Solid

Stage Bus

Propellant Burning time (sec.) Solid Motor Thrust Sea Level/Vacuum (Tonnes) Specific Impulse Sea Level/Vacuum (sec.)

Basing Mode

Road-Mobile/Silo

Launch Technique

Mortor/Cold

Deployed boosters

288

Test Boosters

5

Warheads Deployed

288

Training Launchers Space Booster Variant

START-1 Deployment Sites

START

Locale US-Designation

Irkutsk Kansk Krasnoyarsk

Gladkaya

Lida Mozyr? Nizhniy Tagil

Verknyaya Salda

Teykovo

Teykovo

Yoshkar Ola

Yoshkar Ola

Yur?ya

Yurya

SS-25/RS-12M in Launch Canister

SS-25/RS-12M Road-Mobile Launcher Version B

LaunchAssociated Support Vehicle

SS-25/RS-12M Road-Mobile Launcher Version A

SS-25/RS-12M Road-Mobile Launcher Version A with Missile

SS-25/RS-12M Road-Mobile Launcher Version B with Missile

SS-25/RS-12M, Stage 1

Fixed Structure for Road-Mobile Launchers

Driver Training Vehicle 1.0

Driver Training Vehicle 1.1

RT-2UTTH - Topol-M SS-27 The single-warhead RT-2UTTH Topol-M is an advanced version of the silo-based and mobile Topol intercontinental ballistic missile. The SS-25 Topol is generally similar to the American Minuteman-2, while the more sophisticated SS-27 Topol-M is comparable to the American Minuteman-3. The Topol-M is 22.7 meters (75 feet) long and has a diameter of 1.95 meters (6 feet 3 inches). The missile weighs 47.2 metric tons and has a range of 11,000 kilometers (6,900 miles). The solid-propellant three-stage Topol-M missile complex, with a standardized (silo and mobile) missile, is to become the foundation of the Russian strategic nuclear forces in the 21st century. It is planned to accommodate Topol-M both on selfpropelled launchers as well as in silos. High survivability of the mobile complex is achieved by the capability of offroad movement, of a continuous change in location and of a missile launch from any point along the movement route. The Moscow Institute of Heat Engineering (MIT) State Enterprise is the only plant in Russia building such missiles today. The modernized 45-ton Topol-M is the first strategic missile to be built by Russia without the participation of Ukraine and CIS countries. The first test firing of a Topol-M took place on December 20, 1994. The flight and design testing of the Topol-M was successfully completed in 1995, and joint flight-testing is continuing, leading to a decision to commence series production. All the launches have been a success, but largescale serial production has not started due to a shortage of funds. On 08 July 1997 the fourth launch of a Topol-M ICBM was successfully made from the Strategic Missile Forces' Plesetsk State Test Site within the framework of joint flight-testing. The eighth test of the Topol-M missile was conducted on 03 September 1999. The missile was launched from Plesetsk, north of Moscow, and landed at the Kura testing site on Kamchatka. On 10 February 2000 Russia successfully completed the tenth test flight of the Topol-M. The missile was launched from the Plesetsk cosmodrome to a target at the military base in Kura, on the Kamchatka peninsula in the Russian far east, 8,000 kilometers away. On 27 September 2000 Russia test-fired another Topol-M, sending the SS-27 on a 4,000-mile flight from the Arctic base of Plesetsk in northern Russia to its intended target in the Russian Far East. In this 12th test, the missile was fired from a mobile launcher, rather than from a silo. It was the second SS-27 missile test in two days.

Topol-M silo lid Work on the new Topol-M ICBM is lagging seriously behind the initial timetable. Defense state order financing for the next decade provides that by 2003 there will be on the order of 250-300 Topol-M missiles in service. A total of 1.5 trillion [old] rubles were included in the 1997 budget for the development of the Topol-M missile complex. The Russian Missile Troops are permitted to have 300 Topol RS-12M mobile missiles under the START II Treaty, and the RVSN must acquire two Topol-M regiments annually up to 2001, which will cost 3.7 billion new rubles. The Strategic Missile Force plans to deploy mobile Topol-M missile systems at the end of 2002 or early in 2003. A total of R700 billion would be required to place 450 Topol-M missiles in service by 2005 to maintain parity under START II. But the present 55 percent funding will permit production of at the very most 10-15 missiles at this facility each year year. As a result the Strategic Missile Troops would have a total of approximately 350-400 ICBM warheads, not the 800-900 which are permited within the framework of the START II Treaty. On 15 April 1998 Acting Prime Minister Sergey Kiriyenko approved a schedule of monthly budget appropriations for the Topol-M, which he noted would make up the core of Russia's strategic nuclear forces. In December 1997 after four test launches, the first two Topol-M systems were put on alert for a trial period with the Taman Division at Tatischevo in the Saratov region. As of late July 1998 two more Topol-M launch sites were completed and were awaiting acceptance trials. Russia put a regiment of 10 Topol-M missiles on duty in 1998. By that time the Strategic Rocket Forces had carried out 6 successful test launches. A second regiment of another 10 missiles entered service in December 1999. A third regiment, of 10 Topol-M missiles will be deployed in 2000. The Topol-M missile system is being commissioned in the Russian strategic nuclear forces' grouping regardless of whether heavy missiles are stood down from combat alert duty or not. It is intended that the Topol-M ICBM grouping will comprise an equal number of mobile and silo-launched missiles. Some 90 of the 360 launch silos vacated by the RS-20 ICBM's, which are being stood down from combat alert duty, need to be converted for the latter. Apart from Saratov Oblast the Topol-M systems will be deployed in Valday, the southern Urals, and the Altay. The START II strategic arms reduction treaty, signed with the United States in 1993 but not yet ratified by Russia's parliament, calls for Russia to replace its SS-18 missiles, which have multiple warheads, with single warhead missiles such as the Topol-M. Although deployed with a single warhead, the Topol-M could be converted into a multiple-warhead missile, which was prohibited by the START II treaty. Topol-M could

carry at least three and perhaps as many as six warheads. The Topol-M missiles could be transformed into missiles with multiple reentry vehicles [MIRV's], since their throw weight allows accommodating 3-4 warheads on a missile. The warheads could be taken from some of those ground-based and naval missiles which will be withdrawn from the order of battle in coming years. The Topol-M can carry a maneuverable warhead, which was tested in the summer of 1998. Topol-M also has a shorter engine-burn time, to minimize satellite detection on launch.

Specifications DIA

SS-27, SS-X-29, SS-25B

NATO Bilateral

RS-12M2

Service

RT-2PM2, RT-2PM-OS

OKB/Industry

15Zh??

Design Bureau

(MIT)Moscow Institute of Thermal Technology

Approved

2/ /1993

Years of R&D

1993 - 1997

Engineering and Testing

1994 - 1997

First Flight Test

12/20/94

IOC

1997

Deployment Date

12/27/1997

Type of Warhead

Single

Warheads

1

Yield (Mt) Payload (kg)

1,000 - 1,200

Total length (m)

21.0 - 22.7

Total length w/o warhead (m)

17.9

Missile Diameter (m)

1.86 - 1.95

Launch Weight (t)

47.2 - 47.21

Fuel Weight (t) Range (km) CEP (m) (Russian Sources)

10,000 -10,500

CEP (m) (Western Sources)

350+

Number of Stages

3

Canister length (m)

21,2 - 23.0

Canister length w/o

19.44

front meters (m) Canister diameter (m)

2.0

Booster guidance system

Inertial, autonomous

1st stage

2nd stage

3rd stage

1.61

1.58

MIT, NPO Soyuz

MIT, NPO Soyuz

MIT, NPO Soyuz

Solid Propellant

Solid Propellant

Solid Propellant

Length (m)

8.04?

Body diameter (m)

1.86 - 1.95

Fueled weight (t)

28.6

Dry weight (t) Design Bureau for the Solid Motors Engine Designation Propellants Burning time (s) Solid Motor Thrust Sea Level/Vacuum (Tonnes) Specific Impulse (m/s) Basing Mode Hardness Launching Technique Deployed boosters Test Boosters Warheads Deployed Deployment Sites

Silo/Ground mobile

4th.

BUS

Training Launchers Space Booster Variant

No

RT-23 / SS-24 SCALPEL Comparable in size and concept to the US Peacekeeper, the SS-24 is cold-launched with 10 warheads. The missile is deployed both as rail-mobile and silo-based. The silo-based SS-24 was intended to replace the SS-19 Stilletto in the Russian strategic inventory. The SS-24 rail missile systems is subject to elimination under the provisions of the START-II Treaty. The RT-23UTTh is a solid-propellant missile with three stages within a constant diameter body. The first stage of the silo-based missile uses a rotating nozzle, whereas the railway–based version is equipped with a fixed nozzle partially inserted in the motor combustion chamber. The engines of the second and third stages deploy extendable nozzles during flight to increase the motor's specific impulse without the need to increase of the overall dimensions of the missile. During the first stage flight control is attained through deflection of the sustainer nozzle, and during the second and third stage by deflecting the combat stage and by fairing-mounted aerodynamic vanes. Both silo-based and rail-mobile missiles have an autonomous inertial guidance system using an onboard digital computer. The silo-based system uses a two-package block of control instruments made of radiation-resistant electronic elements. The railway-based missile has only one-package block of control instruments. A total of 10 warheads [each with a yield of 550 KT], a post-boost vehicle with a guidance/control system and a propulsion system are inside the nose cone. The guidance/control system provides a CEP of 500 meters according to unofficial Russian estimates, which gives the missile a hard-target-kill capability. The missile is deployed in a transport-launching canister from which it is launched through the mortar start technique. To conduct a railway launch the sliding roof of the car opens, the container is erected and the missile is launched with the help of a solid propellant gas generator. The missile can be launched from any point of the route. The length of the two versions are the missile were determined by the dimensions of the silo or the railway launcher. The silo-based missile therefore has a nose cone tip flap that is activated when the launch is initiated while the railroad based missile has a folded nose cone that is extended when the launch is conducted. The creation of the RT-23 UTTh was the culmination of a long-term effort to create a solid-propellant ICBM for multiple basing modes which was initiated on 13 January 1969. 

15Zh44 - SS-24 PL-4 The difficulties with which the developing institute KB Yuzhnoye (OKB-586) was confronted during the development of the railwaybased SS-24 led to a redefinition of the task on 23 July 1976. Only a silo-launched version of the RT-23 was considered. The preliminary design was completed in March 1977 but it was considered unsatisfactory, and in December 1979 a second

design with an improved propulsion system and a front end was finished. The new design provided using reentry vehicles that were identical to that of the R-36M / SS-18 missile. The suspended activities to build a railway based RT-23 (15Zh52) missile were resumed, and this design was finished in June 1980. The flightdesign tests of the silo-launched RT-23 (15Zh44) began on 26 October 1982. As a result of several failures during the flight-tests, this version was cancelled on 10 February 1983 by the Soviet Defense Ministry.  15Zh52 - SS-24 Mod-0 On 09 August 1983 a further effort to develop a silo, railway and road-mobile missile designated as RT-23UTTh was approved, but the road-mobile stationing mode was subsequently abandoned. The tests of the railway based RT-23 (15Zh52) were successfully completed in April 1985, and in November 1987 it was experimentally adopted.  15Zh61 - SS-24 Mod-1 The RT-23UTTh tests of the railroad SS-24 Mod-1 version (15Zh61) that is almost identical to the 15Zh52 began on 27 February 1985 and were finished in December 1987 The deployment of these missiles started on 28 November 1989, and the first regiment with railroad-based missiles was put on alert on 20 October 1987. Altogether 36 railway-based RT-23UTTh missiles were initially deployed. They were deployed in three garrison areas: 12 launchers at Kostroma (400 km east of Moscow), 9 launchers at Bershet (1,250 km east of Moscow), and 12 launchers at Krasnoyarsk in Siberia. The Military Railroad Missile Complex (Boyevoy Zheleznyy Raketnyy Kompleks BZhRK) consists of three launch cars [each with a single missile], a command and control car, cars for personnel, and several diesel locomotives. The rail-mobile version could operate on any Soviet rail line that was unobstructed by overhead electrical power lines, a total of 145,000 km of track.  15Zh60 - SS-24 Mod-2 The silo-based version (15Zh60) known as SS-24 Mod-1 was tested from 31 July 1986 through November 1988. The deployment of these missiles in silos formerly occupied by SS-17 Sego ICBMs, started on 28 November 1989, and the first regiment of silo-based missiles was activated on 19 August 1988. Altogether 56 silo-based RT-23UTTh missiles were initially deployed, with 10 at Tatishchevo in Russia and 46 at Pervomaysk in Ukraine. The US Defense Department stated in September 1991 that production had ended with approximately 90 missiles deployed. A total of 46 silo-based RT-23UTTh missiles located in Ukraine were phased out and dismantled in compliance with the provisions of the START-1 treaty. They were denuclearised and their warheads have been transferred to Russia. By 1994 most of the rail-mobile systems remained in garrison due to lack of funding. By April 1997 10 silo-based and 36 railway based RT23-UTTh missiles were still deployed on Russian territory. Following Russian ratifiication of the START-2 treaty in early 2000, all RT-23 UTTh missiles are subject to dismantling. With the breakupof the Soviet Union in 1991, most design and production facilities for the SS-24 belonged to Ukraine. Ukraine had no interest in continuing to produce these ICBMs, and the production line was closed in 1995.

It has been suggested that these rail-mobile land-based missiles, which have been parked in their garrisons, may be placed back on patrol in response to American missile defense and associated arms control initiatives.

Specifications R&D

Mod-

Mod-2

Mod-1

DIA

SS-24 PL-04

SS-24

SS-24V

SS-24

NATO

Scalpel

Scalpel

Scalpel

Scalpel

RS-22B

RS-22A

RS-22V

Bilateral Service

RT-23

RT-23

RT-23 UTTKh RT-23 UTTKh

OKB/Industry

15Zh44

15Zh52

15Zh60

15Zh61

Design Bureau

SKB-586, NPO Yuzhynoy Acad. V. F. Utkin

SKB-586, NPO Yuzhnoye Acad. V. F. Utkin

SKB-586, NPO Yuzhnoye Acad. V. F. Utkin

SKB-586, NPO Yuzhnoye Acad. V. F. Utkin

Approved

7/23/1976 6/1/1979

8/9/1983

8/9/1983

Years of R&D

1/1969 ?3/1977

Engineering and Testing

1985-87

First Flight Test

10/26/82 Failure, 12/1982 Success

11/1982 - 1983 - 1989 1987

1983 - 1989

4/ /1984

7/31/1986

2/27/1985

IOC

canceled 10/20/87

8/19/1988

12/1987

Deployment Date

Canceled 11/ /1987 11/28/1989

11/28/1989

Type of Warhead

MIRV

MIRV

MIRV

MIRV

Warheads

10

10

10

10

Yield (Mt)

0.55

0.35 0.55

0.35 -0.55

0.3 -0.55

Payload (t)

4.05

4.05

4.05

4.05

Total length (m)

23.3

23.4 23.8

18.8 - 23.4

23.3

Total length w/o

18.8, 19

19

19

19

warhead (m) Missile Diameter (m)

2.4

2.4

2.4

2.4

Launch Weight (t)

104.5

104.5

104.5

104.5

Range (km)

10,000

10,000 11,000

10,100 11,000

10,100 10,450

CEP (m) (Russian Sources)

500

500

500

500

CEP (m) (Western Sources)

150-250

150-250

150-250

150-250

Silo

Silo

Railroad

Basing Mode Number of Stages

3

Canister length (m)

21.0 - 22.4

Canister length w/o

19.4

Front meters (m) Canister diameter (m)

2.7

Booster guidance system

Inertial autonomous 1 Stage

2nd Stage

3rd Stage Bus Stage

Length (m) M1

9.7

4.8

3.6

Length (m) M2

9.5

Body diameter (m)

2.4

2.4

2.4

Fueled weight (t) M2

52.5

Fueled weight (t) M1

53.7

Dry weight (t) Design Bureau Solid Motor Designation

15D305

Propellants

Solid Solid Solid Propellant Propellant Propellant

Burning time (sec.)

15D339

2.4

Solid Motor Thrust Sea Level/Vacuum (Tonnes)

?/210

107

21

Specific Impulse (sec.)

Hardness Launching Technique

Cold

Deployed boosters

56

Test Boosters Warheads Deployed

560

Training Launchers Space Booster Variant

Yes, concept only Space Clipper Deployment Sites

START

Locale US-Designation

Kostroma

Kostroma

Pervomaysk

Pervomaysk

Tatishchevo

Tatishchevo

Bershet

Bershet

Krasnoyarsk

Krasnoyarsk

SS-24/RS-22 (silo) in Launch Canister

SS-24/RS-22 (silo), Stage 1

SS-24/RS-22 (rail-mobile) in Launch Canister

S-24/RS-22 (rail-mobile), Stage 1

SS-24/RS-22 Rail-Mobile Launcher

SS-24/RS-22 LaunchAssociated Railcar 1

LaunchAssociated Railcar (1.1)

SS-24/RS-22 LaunchAssociated Railcar 2

SS-24/RS-22 (silo) Emplacement Equipment

SS-24/RS-22 LaunchAssociated Railcar 2.1

Fixed Structure for Rail-Mobile Launchers

RSS-40 Kuryer On 6 October 1991 the USSR rejected development of a new small, mobile ICBM undertaken by the Moscow Institute of Heat Engineering (MIT) State Enterprise. The Kuryer was in no way inferior to its American analog, the small, mobile Midgetman missile complex. This system could have taken the place of Topol-M. The complex was fully prepared for flight tests, but the political leadership yielded to the United States at that time and did not permit them to be conducted. Nevertheless, the basic components of the complex were tested piecemeal. This missile was being developed to include new materials, fuel, a control system and other new design and technological solutions.

Burya La-350 Buran RSS-40 A design for an experimental cruise missile (EKR) with a cruising speed of Mach 3 and a range of 1,300km was developed at the OKB of S. Korolev in 1951-53. It was to consist of a booster with [liquid-fueled rocket engines (derived from the R-11 rocket with storable fuel) and a cruising stage with a supersonic ramjet engine (SPVRD) developed by the OKB of M. Bondaryuk. The technical challenges of intercontinental cruise missiles (MKRs) were not as great as those for ballistic missiles of such long range. A celestial navigation system could provide adequate accuracy for hitting targets. On 20 May 1954 a ministerial decree authorized the development of two parallel projects. The Burya was assigned to the OKB of S. Lavochkin [which had experience in supersonic fighters], and the Buran was the project of the OKB of V. Myasishchev [which was established to develop long-range bombers]. Myasishchev's Buran was designed for a larger warhead than the Burya, and had a large takeoff mass and thrust. The work of the Lavochkin on the Burya OKB moved quickly, and by 1956, when the Myasishchev OKB was finishing the design engineering of the Buran, the first models of Lavochkin's Burya had already been created. The flights of the Burya began in July 1957, at the same time as the flight testing of the R-7 ICBM developed by the Korolev OKB. The Soviet leadership decided soon afterward to curtail the work on the Buran. The final flight of the Burya was conducted on 16 December 1960, following which further work was discontinued. Although the source of the information is uncertain, American publications beginning around 1960 made reference to a "large winged antipodal T-4A bomber under development in the USSR," and even included drawings. However, by the mid-1960s all references in the open literature to such projects vanished, suggesting that such projects were merely Cold War rumors. The fact of the existence of these projects was not confirmed in the open literature until the end of the Cold War, and the provenance of the early reports remains obscure.

Specifications Characteristics

Navaho

Burya

Buran

Launch mass, tonnes

66.2

96

125

Mass of warhead, tonnes

2.25

2.19

3.50

Total length of system, meters

25.1

19.9

24.0

1

2

4

Boosters Quantity

Length, meters

23.1

18.9

19.1

Diameter of body, meters

1.83

1.45

1.20

2 x 68.61

4 x 55

Thrust at launch, tonnes of force 128.45 Fuel Components: oxidizer

liquid oxygen nitric acid

liquid oxygen

combustible

ethyl alcohol amines

kerosene

Length, meters

20.7

18.0

23.3

Diameter of body, meters

1.83

2.20

2.40

Wingspan, meters

8.72

7.75

11.6

Wing area, meters 2

38.9

60

98

Number of SPVRDs

2

1

1

Diameter of SPVRDs, meters

1.22

1.70

2.00

Cruising thrust, tonnes of force

2 x 3.94

7.65

10.6

Maximum range of flight, km

5,400

8,500

8,500

Cruising altitude of flight, km

22-24

18-20

18-20

Cruising speed of flight, Mach

3.25

3.10

3.10

Start of development

1950

1954

1954

Date of start of flight testing

6 Nov 56

1 Jul 57

-

Total number of launches

11

17

-

of which, failed

10

3

Date of end of flight testing

18 Oct 58

16 Dec 60

-

Shutdown of project

July 1957

December 1960

-

Cruising Stage:

R-11FM / SS-1b Scud The first Soviet SLBM, the liquid-propellant missile R-11FM, was a modified version of the R-11 Scud-A. This single-stage missile with a nonseparable warhead was equipped with a single-chamber liquid rocket engine and a pressurized fuel supply system. Flight control was accomplished with control jet motors and four aerodynamic stabilizers. The missile was deployed in a dry tube that penetrated the hulls of the submarine. The launch was conducted from the surface, prior to which the missile was elevated to the edge of the tube and fixed with the help of special racks. Unlike the R-11, the R-11FM featured a hermetically sealed instrumental and propulsion compartment and a command stucture capable of receiving data from the navigation system of the submarine on launch.. The development of the R-11FM was authorized by the government on 26 January 1954. S.P. Korolev who was at that time chief designer of OKB-1 NII-88 was assigned the development of the D-1 launch system and the R-11FM missile. Other institutions working on the project included: NII-885 Minraliopoma (command structure, chief designer N.A. Pilyugin), OKB-2 HII-88 (propulsion systems, chief designer A. M.Irayev), NII-49 (navigation systems, director N.A. Charin), МNII-1 (navigation systems, director E.I. Ellyer), OKB-34 (creation of the dynamic platform, chief designer Ye. G. Rudyak). The development of the R-11FM missile was carried out in three phases. The first two took place at the State Central Taining Site Number 4 at Kapustin Yar, during which the missile was launched from a fixed and then from a dynamic platform. . During September and October 1954 three missiles were launched from a fixed platform similar to the designated submarine launcher. Between 25 May and 30 July 1955 a total of 11 launches were conducted from a dynamic platform. The third phase of tests were carried out on a submarine The first submarine launch was successfully completed on 16 September1955, from the submarine "B-67" of the V-611 (Zulu) class, located in the White Sea close to the Kola peninsula. Seven of the eight tests between 16 September and 13 October 1955 were successful. In August 1955 the R-11FM project was transferred to SKB-385 in Zlatoust. Chief designer V.P. Makyeyev of SKB-385 was responsible for creating the design documentation, conducting modifications and and flight tests, to adjust series production and to deliver the missile. To ensure combat readiness after long periods of on-board storage, service tests of the missile and launch system were conducted in August and October 1956 by the Northern fleet. The first long-range patrol of the "B-67" submarine with R-11FM missiles began on 16 August 1956. Covering a route through the White and Barents seas, the boat sailed surfaced and submerged at various speeds, spending two days on alert and conducting missile fiings afterwards. On 12 September and 03 October 1956 missiles that had been stored onboard the submarine for 37, 47 and 82 days were successfully launched.

After these tests, OKB-1 participated in the improvement of the missile and acted as architectural supervisor whereas SKB-385 assumed responsibility for all further activities. The missile documentation was completed in late 1956 and preparation for serial production was initiated. In 1957 manufacturing of propulsion systems and missiles to be tested from a fixed platform began. After they were completed the missile was testlaunched from a dynamic platform in the autumn of 1957. The last test phase between March and May 1958 consisted of four submarine launches, of which three were successful. Deployment of the R-11FM missile began on 20 February 1959 on the 611AB [ZULU V] and 629 [GOLF I] class submarines. Although the R-11FM missiles were designed to use RDS-4 nuclear explosives, it is reported that during regular patrols they were not equipped with nuclear explosives. The nuclear warheads were stored at the coast, to be transferred to the submarines in times of crisis. Between 1958 and 1967 a total of 77 missile firings were conducted of which 59 were successful. In 1967 the D-1 launch system and the the R-11FM missiles were withdrawn from operational service. Western intelligence in the 1960s was evidently somewhat confused by the relationship between the R-11FM and R-13 programs. Despite the differences in the physical designs of these missiles, the R-11FM was regarded as simply the interim reduced-range version of the longer range R-13 follow-on.

Specifications DIA

SS-1b

NATO

Scud

Bilateral Service

R-11FM

OKB/Industry

8K11/8A61FM

Design Bureau

OKB-1 NII-88/SKB-385

Approved Years of R&D Engineering and Testing First Flight Test IOC Deployment began

2/20/1959

Launch system

D-1/D-2

Submarine

611 AB Zulu V

Type of Warhead

Single, inseparable

Warheads

1

Yield (mt)

0.1/0.5

Payload (t)

975-1000

Total length (m)

10.3

Total length w/o warhead (m) Missile Diameter (m)

0.88

Launch Weight (t)

5.4-5.6

Fuel Weight (t) Range (km)

150/167

CEP (m) (Russian Sources)

1.5 km on range, 0.75 on azimuth

CEP (m) Western Sources) Number of Stages

1

Warheads Deployed Booster guidance system

Inertial autonomous

Engine Designation Propellants

Liquid

Fuel

Kerosene T-11

Oxidizer

20% UDMH 80% Nitrogen Acid

Burning time (s) Verniers Thrust Sea Level/Vacuum (kn) Specific Impulse (s) Launching Technique

Surfaced

R-13 / SS-N-4 SARK The R-13 was a single-stage storable liquid-propellant missile with a separable monoblock reentry vehicle. Equipped with a single combustion chamber rocket engine with turbopumps, it had a four-chamber flight control engine. The R-13 was the first Soviet SLBM to use such vernier engines for flight control instead of gas or aerodynamic control surfaces. Additionally, to stabilize the missile in early flight, four aerodynamic stabilizers were used. These were considerably smaller than the fins used on the R-11FM. The SS-N-4 could deliver a 2800-lb reentry vehicle a maximum operational range of 300 nm. The reentry vehicle had a nuclear warhead with a yield estimated in the west at 1.2 to 2.0 MT, though Russian sources place the yield at 1.0 MT. It had an inertial guidance system and a CEP of 1 to 2 nm according to western intelligence estimates. Western intelligence in the 1960s was evidently somewhat confused by the relationship between the R-11FM and R-13 programs. Despite the significant differences in the physical designs of these missiles, the R-11FM was regarded as simply the interim reduced-range version of the longer range R-13 follow-on. The short range of the R-11FM missiles rendered submarines armed with this missile vulnerable to antisubmarine defense systems, highlighing the need for a longer-range system. On 25 August 1955 the governmental ordered the development of a sea-based ballistic missile with a range of 400-600 km carrying a nuclear warhead. The D-2 launch system with R-13 missiles was authorized on 11 January 1956. In early 1956 OKB-1 NII88 finished the the preliminary design, after which the project was transferred TO SKB385, which conducted all further activities. The design was completed in 1957 and in December 1958 the engine tests of the R-13 missile began. Between June 1959 and March I960 flight tests of the R-13 on fixed and dynamic platforms were conducted on the State Central Training Site in Kapustin Yar. Submarine tests began in November 1959 and were completed in August 1960. Altogether 15 out of 19 launches were successfully carried out at the training site and 11 out 13 on submarines. During the time the R-13 missile was deployed (1960-1972) 225 out of 311 launches were conducted successfully. The D-2 launch system and the R-13 missiles were deployed on 13 October 1961 on 629class Golf and 658-class Hotel submarines. Several improvements were implemented thereafter, with the missiles' combat readiness increased from three to six months, and depot storage time was increased to seven years. The SS-N-4 was believed to have been assigned both a peripheral and an intercontinental mission in the past. Peak operational deployment was reached in 1962, with phase-out from the intercontinental mission beginning in 1964 and phaseout from the peripheral mission beginning in 1967. By 1973 the missile was believed to be assigned only a peripheral mission and was carried only aboard the Golf-I Class diesel-electric submarine, which required surfacing before missile launch. The normal reaction time is 20 to 25 minutes. The reaction time under conditions of peak alert is six to eight minutes, and the allowable hold time under these conditions is about one hour.

Specifications DIA

SS-N-4

NATO

Sark

Bilateral Service

R-13

OKB/Industry

4K50

Design Bureau

SKB-385

Approved Years of R&D Engineering and Testing

1959-1960

First Flight Test

1959

IOC Deployment Date

10/13/1961

Launch system

D-2/D-3

Submarine

Golf & Hotel class

Type of Warhead

Single

Warheads

1

Yield (mt)

1

Payload (t)

1.6

Total length (m)

11.8

Total length w/o warhead (m) Missile Diameter (m)

1.3

Diameter of Stabilizers (m)

1.9

Launch Weight (t)

13.745

Fuel Weight (t) Range (km)

600

CEP (m) (Russian Sources)

4,000

CEP (m) Western Sources)

1,800 - 3,900

Number of Stages

1

Warheads Deployed

Booster guidance system Engine Designation Propellants

Liquid

Fuel

AK-27I

Oxidizer

TG-02

Burning time (s) Verniers Thrust Sea Level/Vacuum (kn) Specific Impulse (s) Launching Technique

Surfaced

Historical Review - Western Estimates Zulu Class submarine modified for two SS-N-4 missiles mounted in sail, for SLBM test program

1955

Missile flight test program began

1956

Initially deployed aboard Zulu Conversion submarine

1957

IOC for early model of reduced range

1958

IOC for full-range model

1960

Peak operational deployment (105 missiles aboard 37 submarines)

1962

Missile production terminated

Mid-1964

Beginning of phase out

1965

Phase out of Golf-I Class submarines and SS-N-4 SLBMs complete

January 1975

R-15 The R-15 missile, which was supposed to have a range of about 1,000 km, was developed by OKB-586 at Dnepropetrovsk. Unlike the D-1 and D-2 launch systems, with the D-3 launch system the R-15 missile would be fired directly out of the missile tube without previous elevation of the missile. In 1955 chief designer V.P. Funikov of SKB-143 [now MBM Malakite] undertook the design of a nuclear powered submarine [designated Project 639] with a displacement of 6000 tons that was intended to carry three R-15 missiles. The development of the D-3 launch system was officially authorized on 20 March 1958. During 1958 OKB-16 developed a design for a diesel-engine electric submarine able to carry one R-15 missile. Because of the large overall dimensions and weight of the missile, these systems had poor technical and tactical characteristics. Consequently, the development of the R-15 missile, the D-3 launch system and the submarines was canceled in December 1958 while they were still on the drawing board.

R-21 / SS-N-5 SERB The R-21 / SS-N-5 submarine-launched ballistic missile is a single-stage, storable liquidpropellant missile. The D-4 launch system used the "wet launch" technique, under which the missile tube had to be filled with water before launch. The missiles could be fired underwater and were intended to replace the D-2 launch system on board the Golf submarines. According to Western intelligence estimates, the missile could deliver a 2800-lb reentry vehicle having a 2.0-3.5 MT warhead a maximum operational range of 700 nm. It had an inertial guidance system, and a CEP estimated by western intelligence of 1 to 2 nautical miles. The SS-N-5 was carried aboard both the Golf-II Class diesel-electric submarine, which was believed to be assigned a peripheral mission, and the Hotel-II Class nuclear submarine, which were assigned a strategic mission. Both submarines can launch missiles while fully submerged and underway at about five knots. The normal reaction time is 15 to 20 minutes, and their action time under conditions of peak alert is one to two minutes. The allowable hold time under peak alert conditions is about one hour. Initial operational capability was reached in 1963. The project to construct an underwater launched missile started as early as 1955 and concentrated on the R-11FM missile. On 03 February 1955, E.V. Charnko, the chief designer of OKB-10 NII-88, was assigned responsibility of developing the missile, and the chief designer of SKB-626, N.A. Ryemihatov, was responsible for developing the submarine infrastructure. The development program conducted in three phases. First, R-11FM dummies were fired from a fixed underwater tube, then dummies were launched from tubes located on the outside of the submarine and finally full scale test firing from a sailing submarine. For pop-up tests, two R-11FM dummies were designed: the С4.1 and the C4.5. The first missile launch from an underwater platform was conducted on 23 December 1956. The specially modified "S-229" Whiskey submarine, re-designated B-613, conducted tests with a dummy missile while the submarine was submerged at a depth of 15-20 meters and sailing at a speed of 3-4 knots. Three С4.1. dummy launches were conducted in the Black sea in June 1957. The development of the new D-4 launch system with R-21 missiles was authorized on 20 March 1958. Originally, OKB-586 and its chief designer M.K. Yangel was charged with the project but on 17 March 1959 the program was transferred to SKB-385. After the development of the R-21 missile was authorized in 1958, the R-11FM missile continued in use for further tests. The modified R-11FM, designated C4.7, was used in the third series tests, of launches from submerged submarines, that began in July 1959. Prior to the conclusion of the second phase of tests, the Ministerial Council had directed the conversion of the "B-67" V-611 submarine to carry out the third test phase. The first С4.7 missile firing in August 1959 from the "B-67" submarine was a failure, delaying

further tests by a year. The second test flight on 16 August1960 also ended in failure when the tube filled with water and the missile fell from the launch pad and crushed its nose cone. The third submarine launch on 10 September 1960 was successful. The K1.1 missile, a less powerful experimental version of the R-21 SS-N-5 SERB missile, was tested in parallel to the C4.7 test program. Pop-up tests of the K1.1 missile were conducted in the Black Sea from a 40-50 m deep fixed floating platform and the "S229" submarine. Six launches from a platform and three from a submarine were carried out between May 1960 and October 1961. The K1.1 missile was publicly displayed in parades in Red Square, and incorrectly identified in the West as the SS-N-5 SERB. In fact, it was a prototype missile tested in association with the development of the operational SS-N-5. The 629B Golf II submarine was built for testing the D-4 launch system, Joint testing began in February 1962 and the first underwater launch took place on 24 February 1962. A total of 27 missile launches were conducted during these tests. On 15 May 1963 deployment of the D-4 launch system on Golf and Hotel submarines began. The R-21 remained in operational service from 1963 to 1989, during which time 193 out of a total of 228 launches were successful. Over this period the service life of the fueled missile was increased from six months to two years.

Historical Review - Western Estimates Estimated start of Golf Class submarine conversion

January 1960

Beginning of preliminary flight testing

1961

Estimated start of underwater ejection tests

1961

Beginning of integrated system tests

Late 1961

First launch detected

March 10, 1962

Estimated start of Hotel Class conversion

Mid-1963

IOC of Golf-II Class submarines

Late 1963

IOC of Hotel-II Class submarines

1964

Peak operational inventory (57 missiles aboard 19 submarines) 1971

Specifications DIA

SS-N-5

NATO

Sark

Bilateral

Service OKB/Industry

4K55

Design Bureau

OKB-586/SKB-385

Approved Years of R&D Engineering and Testing First Flight Test

2/24/1962

IOC Deployment Date

15/5/1963

Launch system

D-4 with 3 missiles

Submarine

Golf-II / Hotel II

Warheads

1

Yield

0.8-1.0 MT - Russian sources 2.0-3.5 MT - Western sources

Payload (kg)

1,200

Total length (m)

12.9-14.3

Total length w/o warhead (m) Missile Diameter (m)

1.3-1.4

Diameter of Stabilizers (m) Launch Weight (t)

16.6-19.7

Fuel Weight (t) Range (km)

1400

CEP (m) (Russian Sources)

2,800

CEP (m) Western Sources)

1,800 - 3,900

Number of Stages

1

Warheads deployed Booster guidance system

Inertial

Engine Designation Propellants Fuel Oxidizer

Liquid

Burning time (s) Verniers Thrust Sea Level/Vacuum (kn) Specific Impulse (s) Launching Technique

Underwater

Firing conditions:

Sea state - Up to 5 Submarine Speed, kn - 4 (at 40 to 50m depth)

R-27 / SS-N-6 SERB The R-27 / SS-N-6 submarine-launched ballistic missile is a single-stage, storable liquidpropellant missile. Three variants were deployed using an inertial guidance system, while a fourth variant [the SS-NX-13] used radio command guidance. One of the inertiallyguided variants carried multiple re-entry vehicles [MRV] that were not independently targetted. The missile was first seen publicly in a Moscow parade in 1967. By the mid-1970s Western intelligence believed that the SS-N-6 Mod 1 delivered a 1500-1b reentry vehicle to a maximum operational range of 1300 nm with a CEP of about 0.6 nm. The SS-N-6 Mod 2 was believed to deliver a 1,500-lb reentry vehicle to a maximum operational range of 1,600 nm. The SS-N-6 Mod 3 was assessed as having MRV payload consisting of two 600-lb RVs or three 400-lb RVs. Both the Mod 2 and Mod 3 were thought to have a CEP of about 0.7 nm. The yield of the single RV Mod 1 and Mod 2 was believed to be 0.6 to 1.2 MT. The yield of each warhead in the 2-MRV variant of the Mod 3 was estimated at 0.4 to 0.8 MT, and the yield of each warhead in the 3-MRV variant at 0.1 to 0.4 MT. The existence of a 2-MRV variant of the Mod 3 is not reported by Russian sources. Sixteen of the SS-N-6 missiles were carried aboard the Yankee class nuclear submarine. Missiles could be launched while the submarine was submerged and underway. According to Western estimates, normal reaction time, while the submarine was submerged on patrol, was about 15 minutes. Reaction time under conditions of peak alert is one minute. The allowable hold time under conditions of peak alert was one hour. The Yankee submarine demonstrated a patrol capability of 75 days, and patrols of longer duration (90 days) were believed possible, consistent with crew provisioning and morale. The D-5 launch system with R-27 missiles originated with studies by SKB-385 in the early 1960s to develop a ballistic missile capable of attacking sea-based targets. Development work resulted from a proposal by SKB-385 in late 1961 for the development of a launch system with a light single-stage missile for strikes against strategic land targets. The Yankee I submarnes were the designated carrier. On 24 April 1962 the project was officially authorized. One distinctive innovation in this design was the placement of the rocket engines within the fuel tank in order to reduce the external dimensions of the vehicle. The missile body was made of aluminium alloys, and the fuel and oxidizer tanks had common bottoms. The command and control avionics systems were was placed in a hermetically sealed container in the lower interior of the oxidizer tank, eliminating the need for a separate instrument module. Another design innovation was the placement of the command system's sensors on a gyro-stabilized platform. These design features characterize all subsequent liquid-propellant SLBMs developed by SKB-385. The propulsion system has a single-chamber sustainer and a dual-chamber control engine. The thrust chambers of the attitude control engine were oriented at an angle of 45 degrees

from the stabilization axis of the missile (instead of the usual scheme in which the four thrust chambers are aligned along the stabilization axis). Due to an increased thrust ratio the R-26 missile had four times the range of the R-13 missile (2400 km against 600 km) despite its similar launching weight (14.2 versus 13.7 tons). The missile was loaded in the launching tube with the use of several metallized rubber shock absorbers. Together with the lack of aerodynamic stabilizers, this allowed a significant reduction in the overall dimensions of the launch tube. The missile was fired from a flooded tube. A gas bubble generated by the missile's docking adapter dampened the hydraulic shock caused by engine ignition in the tube. Testing of the D-5 launch system took place in three phases. During the first phase 12 pop-up tests were conducted from a flooded platform and a converted 613 submarine. Data from these tests was used to perfect underwater launch, rocket engine and launch tube designs. The second phase from June 1966 through April 1967 consisted of 12 successful launches (out of 17) from a ground platform. The test phases concluded with 6 missile firings from 667Аsubmarines of the Northern fleet. Deployment began on 13 March 1968. On 10 June 1971 it was decided to upgrade the D-5 launch system and the R-27 missiles. The modernized missile, with a more powerful engine and improved guidance system, was designated as R-27U and the launching system received the designation D-5U. The R-27U was designed to carry both single and multiple warheads. The upgraded missile was supposed to have the same maximum range as the original R-27, though equipped with three multiple reentry vehicles. The range and accuracy of the single warhead version of the R-27U was supposed to increase in 20 and 15 percent respectively. Between September 1972 and August 1973 a total of 16 R-27U missiles were successfully launched from a submarine. On 04 January 1971 deployment of the D-5U launch system began. Yankee II and upgraded Yankee I submarines were outfitted with the new system and missiles. The R-27U missile and D-5U launch system remained in service through 1990. Over the life of the program the service life of the missile was increased from five years to thirteen years. The R-27K (SS-NX-13) modification featured a nose cone with a terminal guidance system. This missile, designated 4K18, was designed to attack both coastal radiocontrol installations and moving targets at sea. The R-27K missile was tested in 1974 on board the converted "K-102" 629 Golf submarine. Between 1968 and 1988 the D-5 launch system conducted 492 missile firings, of which 429 were successful. The D-5 launch system conducted more launches than any other Soviet launch system: a peak of 58 launches in 1971 and an average of 23.4 launches per year. During the service life of the D-5U launch system 150 out of 161 missile firings

were successful. Missile firings for military purposes were completed in 1988. Subsequently experimental launches were conducted for microgravity research purposes.

Specifications Mod1

Mod2

Mod3

DIA

SS-N-6

SS-N-6

SS-N-6

NATO

Serb

Serb

Serb

Bilateral

RSM-25

RSM-25

RSM-25

Service

R-27

R-27U

R-27U

OKB/Industry

4K10

Design Bureau

SKB-385

SKB-385

SKB-385

Approved Years of R&D Engineering and Testing First Flight Test

1965

Deployment Date

early 1969

1973

1975

Launch system

D-5

D-5U

D-5U

Submarine

Yankee I

Yankee II

Yankee II

Type of Warhead

Single

Single

MRV

Warheads

1

1

3

Yield (Russian Sources)

1.0 MT

1.0 MT

0.2

Yield (Western Sources)

0.6-1.2 MT

0.6-1.2 MT

0.1-0.8 MT

Payload (t)

0.65

0.65

0.65

Total length (m)

9.65

9.65

9.65

Total length w/o warhead (m)

7.1

7.1

7.1

Missile Diameter (m)

1.5

1.5

1.5

14.2

14.2

14.2

Diameter of Stabilizers (m) Launch Weight (t)

Fuel Weight (t) Range (km)

2400

3200

3200

CEP (km) (Russian Sources)

1.9

1.3-1.8

1.3-1.8

CEP (km) Western Sources)

1.1

1.3

1.3

Number of Stages

1

Warheads Deployed Booster guidance system

Inertial

Engine Designation Propellants

Liquid

Fuel Oxidizer Burning time (s) Verniers Thrust Sea Level/Vacuum (kn) Specific Impulse (s) Launching Technique

Underwater "wet start"

Firing conditions:

Sea state - Up to 5 Submarine Speed, kn - 4 (at 40 to 50m depth)

D-6 Two versions of the D-6 launch system for solid-fuel missiles studied by OKB-7 (KB Arsenal) in Leningrad between 1958 and 1960. One used missile with a single large diameter motor using propellants that were already in production for use in unguided tactical rockets. The second version focused on a new missile incorporating new solid propellants using a crystal oxidizer and fuel, with the first and second stages consisting of clusters of four separate rocket motors. The overall dimensions of either missile would have been too large for a launching tube inside the pressure hull, so the D-6 launcher design called for two tubes on each side of the outside of the hull. To fire the missiles the submarine would surface and the tubes would be turned into a vertical position. The preliminary design of the launch system was completed in 1960. The beginning of detailed design development of the D-6 complex was directed on 18 June 1960, but on 04 June 1961 the program was cancelled.

Specifications DIA NATO Bilateral Service OKB/Industry Design Bureau

OKB-7 (KB Arsenal)

Approved Years of R&D Engineering and Testing First Flight Test

none

IOC Deployment Date

Not deployed

Launch system

D-6

Submarine Type of Warhead

Single

Warheads

1

Yield (mt) Payload (t)

Total length (m) Total length w/o warhead (m) Missile Diameter (m) Launch Weight (t) Fuel Weight (t) Range (km) CEP (m) (Russian Sources) CEP (m) Western Sources) Number of Stages

2

Booster guidance system

Inertial autonomous 1st stage

2nd stage

Length (m) Body diameter (m) Fueled weight (t) Dry weight (t) Engine Designation Propellants

Solid

Fuel Oxidizer Burning time (s) Verniers Thrust Sea Level/Vacuum (kn) Specific Impulse (s) Launching Technique

Surface launch

Firing condition

Sea state Submarine speed, kn

Solid

RT-15M The solid-propellant RT-15M missile was the sea-based counterpart of the RT-15 landbased missile, known in the West as the SS-14 SCAMP. Both consisted of the second and third stage of the RT-2, a prototype solid-fueled ICBM eventually deployed as the SS-13 SAVAGE. The 667 Yankee submarine, originally designed to carry the liquid-fueled R21 missiles with the D-4 launch system, was to carry the RT-15M using the D-7 launch systems. An order of the ministerial council on 04 April 1961 authorized the development of the system by SKB-385, under the industrial designation 4K22. However, SKB-385 was not particularly enthusiastic with the RT-15M missile, regarding liquid-propellant missiles as more promising The solid-propellant RT-15M missile, with a range of 2400 km, weighed three times more than the liquid propellant R-27 missile which had similar range capabilities. Testing lagged substantially behind the initial schedule. Initially the missile underwent pop-up tests, with 5 launches conducted on "613" submarines. Beginning in late 1963 a series of 20 flight tests were conducted of the missile from Golf I submarines. The demonstration of underwater launch from a flooded platform was not completed until the middle of 1964. However, in July 1963 the initiation of integrated testing was postponed, pending successful results with tests of the solid-fuel RT-2 ICBM. Subsequently, development of the RT-15M missile and the D-7 launch system was halted due to the limited range and large weight and overall dimensions of the missile.

Specifications DIA NATO Bilateral Service

RT-15M

OKB/Industry Design Bureau

SKB-385

Approved Years of R&D Engineering and Testing First Flight Test IOC

1964

Deployment Date

Not deployed

Launch system

D-7

Submarine

667 Delta

Type of Warhead

Single

Warheads

1

Yield (mt)

1

Payload (t) Total length (m)

10.5

Total length w/o warhead (m) Missile Diameter (m)

1.5

Launch Weight (t)

50

Fuel Weight (t) Range (km)

2400

CEP (m) (Russian Sources) CEP (m) Western Sources) Number of Stages

2

Booster guidance system

Inertial autonomous 1st stage

2nd stage

Length (m) Body diameter (m) Fueled weight (t) Dry weight (t) Engine Designation Propellants Fuel Oxidizer Burning time (s) Verniers Thrust Sea Level/Vacuum (kn)

Solid

Solid

Specific Impulse (s) Launching Technique

Underwater start

Firing condition

Sea state - Any weather Submarine speed, kn

R-29 / SS-N-8 SAWFLY The R-29 SS-N-8 was the first Soviet sea-based ICBM. Deployed on the Delta-class submarines beginning in 1973, the missile's long range allowed submarine alert patrols in the marginal ice seas of the Soviet arctic littoral, including the Norwegian and Barents seas. Consequently, Soviet submarines no longer needed to pass through Western SOSUS sonar barriers to come within range their targets. And deployed close to home, they could be protected in "bastions" by the rest of the Soviet Navy. The R-29 is a two-stage missile storable liquid-propellant, without an interstage section, carrying a single warhead. The missile had an aluminium magnesium alloy body with integrated fuel tanks. The first stage sustainer and the second stage propulsion system are located inside the fuel tanks, thus reducing the external dimensions of the missile. The conical blunt shaped re-entry vehicle was also located in the second stage fuel tank, oriented opposite to the flight direction. The guidance section is located in the conical area of the compartment where the warhead is usually placed. The propulsion systems of both stages consists of a single-chamber main rocket engine, and dual-chamber control engines with moveable chambers. The R-29 was the first Soviet SLBM to use a digital computer and an azimuthal stellar monitoring system for improved high accuracy and inflight course correction. With a launching weight of 33.3 tons the R-29 missile was capable of delivering a 1,100 kg reentry vehicle to a maximum range of 7800 km, three times greater than the R-27 missile. Thus its patrolling zones were substantially enlarged. According to Western estimates in the 1970s, the SS-N-8 was capable of delivering a 1400-lb reentry vehicle with a 0.6-1.5 MT warhead a distance of 4200 nm with a CEP of approximately 0.5 nm. The R-29 was equipped with ballistic missile defense countermeasures. Decoys were carried in a cylindrical container in the fuel tank of the second stage, and released during nose cone separation. Preliminary design work was conducted by SKB-385 in 1963, which was also in charge of carrying out the entire project after the Soviet Defense Ministry discarded the competing proposals made by OKB-52 and its chief designer V.N. Chyelomyey. The development of the D9 launch system with R-29 missiles was approved on 28 September 1964. The initial tests of the R-29 missile and the D-9 launch system took place with the Black Sea fleet. They consisted of launching full-scale missile dummies with a first stage propulsion system and a simplified command system. Further testing was conducted from March 1969 until December 1971 at the State Central Marine Test Site in Nenoksa. A total of 20 flight demonstration launches were conducted from a ground platform. The final test phase consisted of a series of submarine launches from Delta I submarines. The first submarine launch was on 15 December 1971 in the White Sea. Further tests took

place from August through November 1972, during which 18 out of 19 launches were successfully conducted. The R-29 missiles and the D-9 launch system were made operational on March 12, 1974 and they are deployed on 18 Delta I submarines. The Delta Class nuclear submarine can launch missiles at approximately 7-second intervals while fully submerged. Normal reaction time is 15 minutes; reaction time under conditions of peak alert is about one minute. The allowable hold time under peak alert conditions is one hour. The missiles could either be fired underwater or while the submarine was moored at their bases. Further improvements lead to an increase in range up to 9100 km. The modernized launch system designated as D-9D was made operational in 1978. It was initially deployed on four Delta II submarines, which carry 16 R-29D missiles instead of 12 R-29 missiles. Subseqeuntly, the Delta I submarines were also outfitted with R-29D missiles.

Historical Review - Western Estimates First land-based launch from Nenoksa Naval Missile Test Center detected

June 21, 1969

Hotel III submarine used as test bed for SS-N-8 SLBM

1970

First sea launch

December 25, 1971

Estimated start of integrated system test

Mid-1972

First detection of 12-missile tube Delta Class SSBN

August 1972

Two SS-N-8 missiles launched simultaneously

November 28, 1972

Four SS-N-8 missiles launched within a 30-second interval

December 14, 1972

Initial operational capability reached

Mid-1973

Specifications Mod1

Mod2

DIA

SS-N-8

SS-N-8

NATO

Sawfly

Sawfly

Bilateral

RSM-40

RSM-40

Service

R-29

R-29

OKB/Industry

4K75

Design Bureau

SKB-385

SKB-385

Deployment Date

3/12/1974

1978

Launch system

D-9 with 12 missiles

D-9D with 16 missiles

Submarine

Delta I

Delta I & Delta II

Approved Years of R&D Engineering and Testing First Flight Test IOC

Type of Warhead Warheads

Single

Yield (Russian sources) Yield (Western sources)

0.6-1.5 MT

0.6-1.5 MT

Payload (t)

1.1

1.1

Total length (m)

13

Total length w/o warhead (m) Missile Diameter (m)

1.8

Diameter of Stabilizers (m) Launch Weight (t)

33.3

Fuel Weight (t) Range (km)

7,800

9,100

CEP (m) (Russian Sources)

1,500

900

CEP (m) Western Sources)

900

900

Number of Stages

2

Warheads Deployed Booster guidance system

Astroinertial

1st stage

2nd stage

Length (m) Body diameter (m) Fueled weight (t) Dry weight (t) Engine Designation Propellants

Liquid

Fuel Oxidizer Burning time (s) Verniers Thrust Sea Level/Vacuum (kn) Specific Impulse (s) Launching Technique

Underwater "wet start"/surfaced

Firing conditions:

Sea state - Any conditionUp to 5 Submarine Speed, kn --

Liquid

R-29R/R-2S / SS-N-18 STINGRAY The R-29R missile is the first sea-based Soviet ballistic missile carrying 3 to 7 multiple independently targetable reentry vehicles (MIRVs), with a range of 6,500 to 8000 km, depending on the number of reentry vehicles. It is carried on the 667BDR Delta III ballistic missile submarine, which is equipped with the D-9R launch system and 16 R29R missiles. The Delta III is the first submarine that can fire any number of missiles in a single salvo. The R-29R, the R-29RL and the R-29RK were based on the R-29 single-warhead SLBM. The missiles incorporated the first two stages of the R-29 missile largely unchanged. However, instead of the single reentry vehicle and instrument module on the R-29, the R29R features a post-boost vehicle with either a single warhead or three or seven multiple independently targetable reentry vehicles. The single warhead missile has a maximum range of 8000 km, whereas the MIRVed missiles have a range 6500 km. The post-boost vehicle includes an instrument-assembly module, a guidance system and a propulsion system. The propulsion system of the post-boost vehicle consists of a fourchamber liquid-propellant rocket engine providing for independent warhead targeting. The combustion chambers of the engine are placed on an external conical support structure. The blunt shaped warheads, oriented at an angle of the centerline of the missile, are positioned opposite of the flight direction. They are positioned in a conical shaped internal cavity at the bottom of the forward second stage fuel tank. The bus also dispenses ballistic missile defense countermeasures. Based on the D-9 launch system, the D-9R launch system was developed in the mid1970s to provide a capability for launching MIRVed missiles. The flight tests of the R29R missiles took place from November 1976 throughl October 1978 in the White and Barents Seas on board of the "K-441" Delta III submarine. Of the 22 missiles that were tested, 4 carried a single warhead, 8 carried three MIRVs and 12 were tested with seven MIRVs. Fourteen 667 BDR Delta III submarines were outfitted with the D-9R launch system and R-29R missiles. The SS-N-18 missile carrying seven MIRVs was not deployed. In compliance with the START-1 treaty all missiles are considered to carry four MIRVs.

Specifications Mod1 DIA NATO

SS-N-18 Stingray

Mod2 SS-N-18 Stingray

Mod3 SS-N-18 Stingray

Bilateral

RSM-50

RSM-50

RSM-50

Service

R-29R

R-29R

R-29R

OKB/Industry

3M40

Design Bureau

NII NII Mashinostroyeniy Mashinostroyeniya a

NII Mashinostroyeniya

1973-

1973-

1973-

Approved Years of R&D Engineering and Testing First Flight Test IOC Deployment Date

1979

Launch system

D-9R

D-9R

D-9R

Submarine

Delta III

Delta III

Delta III

Type of Warhead

Single

MIRVed

MIRVed

Warheads

1

3

7

Yield (mt)

0.450

0.2

0.1

Payload (t)

1.6

1.6

1.6

14.1

14.1

1.8

1.8

1.8

35.3

35.3

35.3

Range (km)

8000

6500

6500

CEP (m) (Russian Sources)

900

900

900

Total length (m) 14.1 Total length w/o warhead (m) Missile Diameter (m) Diameter of Stabilizers (m) Launch Weight (t) Fuel Weight (t)

CEP (m) Western Sources) Number of Stages

2 plus post boost vehicle

Warheads deployed Booster guidance system

Astroinertial

1st stage Length (m) Body diameter (m) Fueled weight (t) Dry weight (t) Engine Designation Propellants Fuel Oxidizer Burning time (s) Verniers Thrust Sea Level/Vacuum (kn) Specific Impulse (s) Launching Technique Firing conditions:  

Sea state Submarin e Speed,

Liquid

2nd stage

kn Deployed boosters Test Boosters Warheads Deployed Training Launchers

R-29RM / SS-N-23 SKIF The R-29RM is a three-stage liquid-propellant missile carrying four or ten MIRV. Compared to the R-29R the missile has a larger launch weight (40.3 to 35.5 Tons) providing a heavier payload (2800 kg to 1650 kg) to a greater maximum range (8300 to 8000 km). The R-29M incorporates a number of significant design changes relative to the predecessor R-29R Relative to the R-29R, the diameter of the R-29RM was increased from 1.8 meters to 1.9 meters, which allowed an increase in propellant loading. The new missile's length was increased only slightly, from 14.1 meters to 14.8 meters, allowing the overall dimensions of the launching tube to remained constant. The D-9RM launch system for the R-29RM missiles is based on the D-9R system. Unlike the R-29 and R-29R, the propulsion system of the first stage has four control chambers. The engines of all three stages are located in the tanks. The third stage propulsion system and the post-boost vehicle propulsion system use the same fuel tanks. The warheads are placed in an internal cavity of the concave conical bottom of the upper tank of the second stage at the periphery of the sustainer of the third stage. NII Mashinostroyeniya began work on the development of the D-9RM launch system and the R29-RM in 1979. A series of vehicle development launches from a floating platform was conducted initially, followed by 16 flight tests from a ground platform and submarine tests. Deployment of the D-9RM launch system began in 1986. Seven Deltra IV submarines were equipped with the D-9RM launch system. They carry 16 R-29RM missiles containing four warheads each. The R-29RM missiles carrying ten warheads were not deployed. In 1988 the launch system was modernized providing improved accuracy, and for firing the missiles on depressed trajectories. At that time the missile was also equipped with improved warheads. In late 1999 Russia announced plans to resume production of the SS-N-23. he state missile center Design Agency named after V. P. Makeev received a state order from the Russian government to resume the manufacture of naval missiles, including the most advanced RSM-54 system developed by the Agency when Victor Makeev was its general designer. While deployed with four warheads for the START I treaty, it was originally tested with 10 warheads and might be deployed with that number in the absence of such arms control agreements. It has been suggested that some of these liquid-fuel missiles could be deployed on land in the absence of the START agreements. T

Specifications

DIA

SS-N-23

NATO

Skiff

Bilateral

RSM-54

Service

R-29RM

OKB/Industry

3M37

Design Bureau

NII Mashinostroyeniya

Approved Years of R&D Engineering and Testing First Flight Test

June 1983

IOC Deployment Date

1986

Launch system

D-9RM with 16 missiles

Submarine Type of Warhead

MIRV

Warheads

4 (tested with 10)

Yield (mt) Payload (t)

2800

Total length (m)

14.8

Total length w/o warhead (m) Missile Diameter (m)

1.9

Diameter of Stabilizers (m) Launch Weight (t)

40.3

Fuel Weight (t) Range (km)

8300

CEP (m) (Russian Sources)

500

CEP (m) Western Sources) Number of Stages

2

Warheads Deployed Booster guidance system

astroinertial 1st stage

2nd stage

Length (m) Body diameter (m) Fueled weight (t) Dry weight (t) Engine Designation Propellants

Liquid

Fuel

Nitrogen Tetraoxid

Nitrogen Tetraoxid

Oxidizer

UDMH

UDMH

Burning time (s) Verniers Thrust Sea Level/Vacuum (kn) Specific Impulse (s) Launching Technique

Underwater wet start/ surface

Firing conditions

Sea State Submarine speed, kn

R-31 / RSM-45 SS-N-17 SNIPE The R-31 missile, the first deployed Soviet sea-based solid-fuel missile, was a two-stage missile with a single warhead. Compared to the liquid-propellant R-27 missile the R-31 was easier to handle and had an increased range. However, despite a similar launch weight, the R-31 had a lower accuracy and half the range of the liquid-propellant R-29 missile which was developed at the same time. In the early 1970s the Soviet Navy ordered the development of new missiles and a new launch system intended to replace the D-5 launch system on Yankee I submarines that were to be overhauled and upgraded. Two different proposals were submitted by NII Mashinostroyeniya (chief designer V. P. Makyeyev) and KB Arsenal (chief designer P.A. Tyurin), and the project was awarded to KB Arsenal. Unlike the liquid-propellant missiles R-21, R-27 and R-29, the underwater firing of the R-31 did not require filling the launch tube with water. The missile was ejected from the hermetically sealed tube by a gas generator. The missile emerged in a gas bubble, which was maintained with the help of a special hydrodynamic device located on the nose cone. The sustainer motor of the first stage was started after the missile emerged from the water. The dry start allowed to reduce pre-launch preparation time substantially and decreased the noise during launch preparation. Flight tests of the R-31 missile from a ground platform took place in 1973. The first underwater launch was held on December 26, 1976 in the White Sea. Flight tests were completed in 1979 and in 1980 the Yankee II submarine "K-140" was outfitted with R-31 missiles. Deployment was limited to a single Yankee II submarine "K-140". In 1989 the R-31 missiles were withdrawn from service.

Specifications DIA

SS-N-17

NATO

Snipe

Bilateral

RSM-45

Service

R-31

OKB/Industry

3M17

Design Bureau

KB Arsenal

Approved Years of R&D Engineering and Testing

First Flight Test

1973

IOC Deployment Date

September 1980

Launch system

D-11 with 12 missiles

Submarine

Yankee II

Type of Warhead

Single

Warheads

1

Yield (mt)

0.5

Payload (t)

0.45

Total length (m)

11

Total length w/o warhead (m)

10.6

Missile Diameter (m)

1.54

Diameter of Stabilizers (m) Launch Weight (t)

26.9

Fuel Weight (t) Range (km) CEP (m) (Russian Sources) CEP (m) Western Sources) Number of Stages

2

Warheads Deployed Booster guidance system 1st stage

2nd stage

Length (m) Body diameter (m) Fueled weight (t) Dry weight (t) Engine Designation Propellants

Solid

Solid

Fuel Oxidizer Burning time (s) Verniers Thrust Sea Level/Vacuum (kn) Specific Impulse (s) Launching Technique Firing condition

Underwater dry start 

Sea state - Any weather  Submarine speed, kn

R-39 / SS-N-20 STURGEON The R-39 solid-propellant intercontinental missile is a three-stage missile with multiple re-entry vehicles. The post-boost vehicle has a guidance system, a liquid fuel propulsion system and 10 blunt shaped MIRVed warheads that are smaller than warheads carried on previous missiles. The warheads are located on the rear unit of a post-boost vehicle, around the nozzle of the third stage engine. The missile is suspended in the launch tube from a special control mounted in the nose cone, with a reference ring at the top of the tube functioning as the launch support. The dry launch from the tube is accomplished with a gas generator located on the bottom of the tube in a cavity of the first stage engine nozzle. During lift-off special solid-propellant charges create a gas bubble around the missile considerably reducing hydrodynamic resistance. Ignition of the first stage engine occurs after leaving the tube. Flight control during the active leg of the first stage is attained by injecting gases from the combustion chamber of the sustainer into the nozzle through 8 symmetrically located injection valves. The engines of the second and third stage have gimbaled nozzles. Work on the R-39 missile and the D-19 launch system began in 1971 by NII Mashinostroyeniya (chief designer V. P. Makyeyev). Development was officially authorized in September 1973. Flight testing was conducted in several phases. Initially two series of dry launches were carried out, nine from a floating platform and seven from a specially adapted submarine. Due to first and second stage engine problems more than half of the 17 flight tests at the Central Naval Test Training Site at Nenoksa were unsuccessful.. After resolution of the engine problems 11 out of 13 launches from the "TK-208" Typhoon submarine were carried out successfully. After intensive testing on board the "TK-208" submarine, deployment began in 1984. The large Typhoon submarines were outfitted with 20 R-39 missiles each. Soon after deployment work began on an advanced version with greater accuracy and greater warhead coverage. Deployment of the modernized missile began in 1989. At the end of the 1980s work on an improved version of the R-39 missile began. This was intended to be deployed on Typhoon submarines and new "Yurin Dolgorukiy" SSBNs. Work on the new missile lagged seriously behind the initial timetable. Flight testing began in 1996 and the first launches terminated in failures.

Specifications DIA

SS-N-20

NATO

Sturgeon

Bilateral

RSM-52

Service

R-39

OKB/Industry Design Bureau

NII Mashinostroyeniya

Approved Years of R&D

1973-`979

Engineering and Testing First Flight Test

1979

IOC Deployment Date

May 1983

Launch system

D-19 with 20 missiles

Submarine

Typhoon

Type of Warhead

MIRVed

Warheads

10

Yield (mt)

0.1 each

Payload (kg)

2550

Total length (m)

16.0

Total length w/o warhead (m)

8.4

Missile Diameter (m)

2.4

Diameter of Stabilizers (m) Launch Weight (t)

90

Fuel Weight (t) Range (km) CEP (m) (Russian Sources)

500

CEP (m) Western Sources) Number of Stages

3

Warheads Deployed Booster guidance

Astroinertail

system 1st stage

2nd stage

3rd stage

Length (m) Body diameter (m) Fueled weight (t) Dry weight (t) Engine Designation Propellants

Solid

Solid

Fuel Oxidizer Burning time (s) Verniers Thrust Sea Level/Vacuum (kn) Specific Impulse (s) Launching Technique

Underwater dry start

Firing condition

Sea state - Any weather Submarine speed, kn

Solid

R-39M / Grom [Bark] / RSM-52V / SS-N28 Russia regards as top priority the maintenance of its strategic nuclear capacity, which represents the base of its policy of deterrence. From this point of view, and in advance of the need for replacing the obsolete hardware or not in conformity with the START-II agreements (which authorize singlewarhead land-based missiles, while permitting multiplewarhead sea-based missiles) a process of modernization of hardware has been authorized. This envisages the development of missile SS-27, successor of the SS-25, and the development of the new SS-N-28 embarked on submarines, and the construction of a fourth generation of strategic missile submarines. Russia still maintains a large force of nuclear-powered ballistic missile submarines equipped with intercontinental range missiles. Although the number of Russian SSBNs is expected to drop considerably over the next few years, Russia planned to modernize its force with the addition of the new SS-NX-28 and new Borei Class ballistic missile submarines. The new Grom SS-N-28 was designed to provide improved accuracy compared to the previous SS-N-20, but is otherwise apparently a straightforward development of this system. The SS-NX-28, unlike previous Russian SLBMs, is the first to be totally developed and manufactured within Russia's borders by the Makeyev Machine-Building Design Bureau. The test launch of a prototype SS-NX-28 (RSM-52V) SLBM on 19 November 1998 resulted in a catastrophic failure of the SLBM's booster. The missile exploded roughly 200 meters after take-off from its ground based launch station. Having had failed its first three test firings, and the SS-N-28 project was abandoned. As of early 1999 it appeared that construction had ceased on the first unit of the Boreiclass, pending a redesign of the ship to accomodate a different missile from the originally intended SS-N-28. The Typhoon submarines were initially intended to be retrofitted with the SS-N-28. The lead unit of this class, the TK-208, had been in overhaul since 1992 with the intent of receiving these modifications, but it now appears that it will not return to service. The Typhoon class submarines are slated to be withdrawn from service within a few years, and it is unlikely that other units of the class would be modified to accomodate new missiles. In January 2000 Rear-Admiral Vladimir Makeev, the head of the Northern Fleet's rocket test site at Nenoksa, Arkhangelsk County, stated that Typhoon submarines would be used

to test the new Bark-class strategic missiles. Makeev also stated that Bark-class missiles were to be installed on the forth generation Borey-class submarines. The creation of D-19UTH missile complex designed for the new nuclear strategic submarines of the Borei-class has been undertaken at GRTs KB named after V. P. Makeev. The D-19UTH launch complex is to replace the D-9 launch complex with RSM52 ballistic missiles. The new complex will be equipped with a solid-fuel ballistic missile of greater reliability and longer range, capable of being fired from the surface and underwater positions.

Specifications Primary function: Contractor:

Makeyev Machine-Building

Power Plant: Length: Weight: Diameter: Range:

5,000+ miles

Speed: Guidance system: Warheads: Date Deployed: Unit Cost: Inventory:

10 or fewer

611 AB ZULU V The development of the first Soviet ballistic missile submarine started with a governmental order for the adaptation of a diesel-powered submarine of the 611 Zulu class to be equipped with the D-1 launching system and two R-11FM missiles. This new submarine designated as B-611 was developed by OKB-16. The technical design of the submarine was completed by the end of 1954. Unlike its predecessors the B-611 submarine had an additional missile compartment with two firing tubes which passed through the strong hull. To accommodate the new launching complex the structure of armament was changed. The spare torpedos, mines and artillery armament were removed and at the expense of removing one of four groups of storage compartments additional launching devices for missile firings were installed. To fire the missile the submarine had to submerge, the cover of the launching tube was opened and the missile was raised to the edge of the tube. The missile was fastened with the help of two racks, which were removed at liftoff. The pre-launch preparation were conducted underwater and lasted two hours. When submerged it took five minutes to launch the first missile and another five minutes to launch the second one. The launch could be carried out at a speed of up to 12 knots. The B-611 submarine was assembled in Severodvinsk and some parts of the submarine were delivered from Leningrad. The construction of the first Soviet ballistic missile submarine was completed in September 1955 and received the tactical designation "B62". The B-62 was Project 611A [ZULU IV] with a single R-11FM (Scud) missile. Some sources quote B-67 as the original Project 611A, however only B-62 fits the known construction dates. The other submarines were Project 611AB ZULU V with two such missiles. In September 1955 the first ballistic missile was launched from the first B-611 submarine "B-62". Between 1956 and 1958 further testing of the D-1 launch system was carried out and in 1959 the "B-62" submarine was converted to carry out the first underwater missile firing. From 1956 on the B-611 submarines were equipped with five new diesel-powered engines and received the new designation AV-611. The first AV-611 submarines served in the Northern fleet. The four submarines that were re-equipped in Severodvinsk were commissioned in 1957 and served in the 40th brigade of the Northern Fleet while the AV-611 re-equipped at Komsomolsk-na-Amur served in the Pacific Fleet. After an improved launch system was developed, the original launch systems D-1 was removed from operational status in 1967. In the second half of the 1960s the AV-611 submarines were equipped with hydroacoustic devices and improved navigation and communication systems. They remained in service until the end of the 1980s.

Specifications Soviet Designation

V-611

AV-611

US-Designation

Zulu IV

Zulu V

Development began

January 1954

Design Bureau

UKB-16

Chief designer

N.N. Isanin

Builders

Nr. 402 Severodvinsk

Nr. 402 Severodvinsk Nr. 199 Komsomol Na Amur

Construction and Outfit

1953-1956

1954-1958

Service time

1956-1964

1957-1968

Number of ships

1

5

Armament

D-1 launch system with R-11FM missiles 10-533mm torpedo tubes

Power Plant

Diesel and electrical engines

Length

90.5 meters

Beam

7.5 meters

Draft

5.14 meters

5.15 meters

Displacement

1875 m3 Surfaced

1890 m3 Surfaced

2387 m3 Submerged

2415 m3 Submerged

98.9 meters

Operating depth

170 meters (design) 200 meters (maximum depth)

Speed

16.5 knots Surface 13 knots Submerged

12.5 knots Submerged

Crew

72 men

83 men

Endurance

58 days

Class Listing Boat # number Name

Chronology

Shipyard Laid

Launched Comm.

Notes Stricken

Down 1 B-62

402 Sevmash

Dec.31/53 1970

2 B-67

402 Sevmash

Jun.30/56 1970

3 B-73

402 Sevmash

Nov.30/57 1971

4 B-78

402 Sevmash

Nov.30/57 1990

5 B-79

402 Sevmash

Dec.4/57

6 B-89

199 Komsomolsk

Dec.13/57 1990

1971

Sonar trials ship 1966

629 GOLF Along with initiating development of the first experimental ballistic missile submarine under Project V-611, the governmental order of 26 January 1954 provided for the development of a diesel-powered ballistic missile submarine. On May 1954 the headquarters of the Navy assigned OKB-16 the task of developing the Golf submarines. The development of the Golf I submarine and its corresponding launch system D-2 was authorized on 11 January 1956. In March 1956 the complete technical design of the submarine was submitted to the Navy shipbuilding headquarters. Originally the new submarine was designed to carry the R-11FM missiles, which had a range of 250 km, and only 150 km when carrying a nuclear warhead. American antisubmarine defense precluded using such a short-range missile to carry out effective strikes against targets at any meaningful distance from the coastline. As the development of the submarine encountered significant delays, it was nevertheless decided to equip the first three submarines with R-11FM missiles. The basic design of the Golf submarine is based on the 641 Foxtrot, and the electromechanical installation for a surface and underwater navigation, the hydroacoustic system, the radar facilities and the radio communication systems were incorporated without change. The 629 Golf has a cylindrical pressure hull divided into eight compartments, with three missile tubes located in the fourth compartment. The large fin of the submarine contains the missiles that are stored in vertical containers directly behind the sail. The missiles are fired by raising the launch platform to the edge of the tube. Launches are conducted on the surface at a speed of up to 15 knots. The battle management system records the current flight coordinates automatically, considerably reducing the time necessary for pre-launch preparation. The pre-launch procedures are conducted underwater and take approximately one hour. Another four minutes was needed after the submarine surfaced, and a total of 12 minutes elapsed until all three missiles were fired. In comparison with the AV-611 submarine the 629 had several advantages. It was outfitted with an additional missile and their range was four times greater. By employing stronger steel for the pressure hull, the maximum navigable depth was increased. The range of sailing was increased both for the surface and the underwater mode and special five-bladed fixed-pitch propellers were developed to reduce the noise. In January 1959 the USSR decided to sell the construction and design plans of the 629 SSBN to the People's Republic of China. After the relations between the USSR and China deteriorated, Soviet specialists were mostly withdrawn in August 1960, though the documentation and equipment for the project remained in China. The construction of submarines of the project 629 was begun in 1957 at Severodvinsk and Komsomol Na Amur. Less than one year later the submarines were launched and at

the end of 1958 trial runs were carried out and the vessels were moored. By 1960 seven 629 submarines had been launched, five of which were incorporated into the Northern fleet and two into the Pacific fleet. In 1961 another five submarines entered the Northern fleet and one entered the Pacific fleet. In 1962 the last two boats arrived at the Pacific fleet. A total of 23 submarines were built: 16 in Severodvinsk and 7 in Komsomol Na Amur. In March or April 1968 the "K-129" submarine sank in the northern Pacific Ocean (1390 kms northwest of Oahu harbor). According to the official version of the Soviet Navy, the submarine exceeded its maximum depth and came to rest on the ocean bottom at a depth of over 5 km. The collapse of the hull was detected by the American SOSUS acoustic system, and in July 1974 parts of the submarine were recovered. The 629 SSBNs of the Northern fleet were organized in the 16th Division that was based in the Olyenya port. This division formed part of the 12th Squadron, which was headquartered in Yagyelnoy. In May 1962 the Soviet government approved a plan for the deployment of a Group of Soviet Forces to Cuba, which in October 1962 precipitated the Cuban Missile Crisis]. Initially the plan called for the deployment of a squadron of submarines, comprising the 18th Division of missile submarines of the Project 629 class [NATO Golf or G-class], consisting of 7 submarines each with 3 R-13 [SS-N-4] missiles with range of 540 km. This element of the plan was in fact not implemented. In September 1968 two 629A submarines were transferred from the Northern to the Pacific fleet and another four from October 1971 till November 1974. At the end of the 1970s the 16th Division, consisting of six 629A submarines, was transferred from the Northern to the Baltic fleet. The 629 submarines that served in the 29th submarine division of the Pacific Fleet were first based on Kamchatka and later on in the Pavlovsk bay. In the middle of the 1970s seven 629A submarines were still in service in the Pacific Fleet. In 1989 four 629A submarines still served in the Baltic and two in the Pacific Fleet. In 1990 however, all submarines were decommissioned.

Variants 

Golf III - Between 1969-1974 the "K-118" was outfitted with 6 launchers to carry out tests of the R-29 (SS-N-8) ballistic missiles. Its' displacement was increased to 4000 tons and the updated submarine received the designation 601.  Golf IV - Between 1969 and 1973 the "K-102" submarine was converted under the Project 605 in order to conduct tests of the R-27K (SS-NX-13) ballistic missiles. It was lengthened in 18,3 meters and outfitted with four launchers.  Golf V - In 1976 one submarine ("K-153") was outfitted with a launcher to carry out tests of the R-39 missile. The submarine received the new designation Project 619.



Golf SSQ - Between 1973 and 1979 the submarines "K-61", "B-42" and "K-107" were converted in Vladivostok under the Project 629R into a command post, with the missile and torpedo tubes removed.

Specifications Soviet Designation

629

629A

US-Designation

Golf I

Golf II

Development began

January 1956

March 1958

Design Bureau

UKB-16

Chief designer

N.N. Isanin

Builders

Nr. 402 Severodvinsk Nr. 199 Komsomol Na Amur

Construction and Outfit

1958-1962

1966-1972

Service time

Since 1959

1967-1990

Number of ships

22

14 (converted from Golf I)

Armament

D-1 launch system with 3 R-11FM missiles D-2 launch system with 3 R-13 missiles

D-4 launch system with 3 R-21 missiles

6-533mm torpedo tubes Power Plant

Diesel and electrical engines

Length

98.4 meters

Beam

8.2 meters

Draft

7.85 meters

8.5 meters

Displacement

2,794 tons Surfaced

2,300-2,820 tons Surfaced

3,553 tons Submerged

2,700-3,553 tons Submerged

98.9 meters

Operating depth

260 meters (design) 300 meters (maximum depth)

Speed

15 knots Surface

15-17 knots Surface

12.5 knots Submerged

12-14 knots Submerged

80 men

83 men

Crew

Endurance

70 days

Class Listing Boat # Num Na ber me

Chronology Shipyard

Laid Launc Commisi Stricke Dow hed oned n n

Notes

1 B-92

402 Sevmash

------ ------------

01/20/19 1991 60

redesignated K-96 (or K-61) 12/1976 project 629R converted to SSQ,redesignated BS167

2 B-40

402 Sevmash

------ ------------

1959-62

1991

redesignated K-72 project 629A converted (Golf II) 1974 redesignated K372

3 B-41

402 Sevmash

------ ------------

1959-62

1991

redesignated K-79 project 629A converted(Golf II)

4 B-42

402 Sevmash

------ ------------

1959-62

1991

redesignated K-83 1978 project 629R converted to SSQ,redesignated BS83

5 B121

402 Sevmash

------ ------------

1959-62

--------- redesignated K-102 1973 project 605 converted(Golf IV)

6 B125

402 Sevmash

------ ------------

1959-62

--------- redesignated K-167 -

7 B-45

402 Sevmash

------ ------------

1959-62

--------- redesignated K-88 12/28/1966 first project 629A converted(Golf II)

8 B-61

402 Sevmash

------ ------------

1959-62

1991

redesignated K-93 project 629A converted(Golf II)

9 B-15

402

------ -------

1959-62

1974

redesignated to K-113

Sevmash

----

---

1 K0 118

402 Sevmash

------ ------------

1959-62

1 K-36 1

402 Sevmash

------ ------------

1959-62

1980

1 K-91 2

402 Sevmash

------ ------------

1959-62

1980

1 K3 107

402 Sevmash

------ ------------

1959-62

1991

1 K4 110

402 Sevmash

------ ------------

1959-62

--------- project 629A converted(Golf II)

1 K5 153

402 Sevmash

------ ------------

1959-62

1992

projext 629A converted(Golf II) 1978 project 619 converted(Golf V) 1991 redesignated BS153

1 K6 142

402 Sevmash

------ ------------

1959-62

1991

1967 project 629A converted

1 B-93 7

199 ------ ------Komsomol -----sk

1959-62

--------- redesignated K-126 project 629A converted(Golf II)

1 B8 103

199 ------ ------Komsomol -----sk

1959-62

08/30/ 1968

1 B9 109

199 ------ ------Komsomol -----sk

1959-62

--------- redesignated K-136 project 629A converted(Golf II)

2 B0 113

199 ------ ------Komsomol -----sk

1959-62

--------- redesignated K-139 project 629A converted(Golf II)

2 K-75 1

199 ------ ------Komsomol -----sk

1959-62

--------- redesignated B-575 project 629A converted(Golf II)

2 K-99

199

1959-62

--------- project 629A

------ -------

project 629E converted(minelayer) 12/1976 project 601 converted(Golf III) redesignated K-106

1977 project 629R converted to SSQ,redesignated BS107

redesignated K-129, lost 03/08/1968

2

Komsomol ---sk

---

2 K3 163

199 ------ ------Komsomol -----sk

1959-62

converted(Golf II)

--------- project 629A converted(Golf II)

629A GOLF II In March 1958 the development of a new missile launch system D-4 with R-21 missiles was approved. It was planned to replace the D-2 launch system and allowed underwater missile firings. The R-21 missiles could be fired from a depth of 40-50 m at a speed of up to 4 knots at intervals of 5 minutes. The time for prelaunch preparation was approximately 45 minutes. After the launch system reached its IOC in May 1963 the reequipment of the 629 submarines began. The submarines equipped with the new D-4 launching system were designated as 629A (Golf II). In early 1967 the upgrading of the first submarines under the project 629A was completed. In total 8 submarines from the Northern and Pacific fleet were outfitted with the D-4 launch system. The improved twenty third submarine of the Golf class (629A) incorporated two improved R-21 missiles.

Specifications Soviet Designation

629

629A

US-Designation

Golf I

Golf II

Development began

January 1956

March 1958

Design Bureau

UKB-16

Chief designer

N.N. Isanin

Builders

Nr. 402 Severodvinsk Nr. 199 Komsomol Na Amur

Construction and Outfit

1958-1962

1966-1972

Service time

Since 1959

1967-1990

Number of ships

22

14 (converted from Golf I)

Armament

D-1 launch system with 3 R-11FM missiles D-2 launch system with 3 R-13 missiles

D-4 launch system with 3 R-21 missiles

6-533mm torpedo tubes Power Plant

Diesel and electrical engines

Length

98.4 meters

Beam

8.2 meters

98.9 meters

Draft

7.85 meters

8.5 meters

Displacement

2,794 tons Surfaced

2,300-2,820 tons Surfaced

3,553 tons Submerged

2,700-3,553 tons Submerged

Operating depth

260 meters (design) 300 meters (maximum depth)

Speed

15 knots Surface

15-17 knots Surface

12.5 knots Submerged

12-14 knots Submerged

Crew

80 men

83 men

Endurance

70 days

658 HOTEL I/II/III Development of the 658 Hotel Class nuclear powered ballistic missile submarine, to be equipped with the D-2 launch system and R-13 missiles, was approved on 26 August 1956. Work on the design documentation began in September 1956, and the technical project was completed in the first quarter of 1957. However this preliminary design was not developed because it would have taken too long to complete. The duties of the chief designer of the project 658 were originally assigned to the chief engineer of OKB-18 P. Z. Golosovskogo. In February 1958 the project management was transferred to I.V. Mihaylov, who in October 1958 had replaced S.N. Kovalev. The deputy of the chief designer was from outset I.D. Spasskiy. The Hotel I submarine was a modification of the first Soviet atomic submarine of the 627 November class. Unlike the November it was equipped with a missile compartment that had previously been used on the Golf submarines. Additionally, small horizontal hydroplanes were added to provide better maneuverability. For high-speed underwater operations with reduced noise, more reliable electrohydraulic-command control surfaces were implemented using main ballast low pressure air. The Hotel I carried three R-13 missiles and the D-2 launch system placed in vertical containers directly behind the sail. All three missiles could be fired within 12 minutes after the submarine surface. The first Hotel submarine -- "K-19" -- was laid down on 17 October 1958. The construction of the boats was completed on 12 November 1960 when the last of eight Hotel submarines was launched. All of them were built at the shipyard in Severodvinsk. In March 1958 it was decided to modify the Hotel I design to accommodate the D-4 launch system which could conduct submerged missile launches. This modified SSBN received the designation 658M Hotel II, and the chief designer of the Hotel II was S.N. Kovalev. The installation of the D-4 launching system required some structural changes of the submarine. Before launch water filled the gap between the launch tube and the missile. To fire the missiles the submarine had to come to a depth of 16m. The upgrading of an advanced submarine under the project 658M was completed on December 30, 1963. Between 1963 and 1967 all Hotel I submarines but one ("K-145") were re-equipped with the D-4 launch system. From 1969 to 1970 the "K-145" submarine was re-equipped to test the R-29 missiles converted. It received the designation 701 (Hotel III). Its length increased up to 130 m and the displacement increased to 5500 Tons surfaced and 6400 Tons submerged. The maximum speed was reduced up to 18 knots on the surface and 22 knots submerged. Four launching racks for R-29 missiles were placed in a compartment. In 1976 the "K-145" Hotel III was introduced into the Navy.

The two Hotel I submarines that were launched in 1960 were sent to the Western Theater and formed a brigade together with 627A submarines. From this brigade in January 1961 a flotilla consisting of two divisions was organized which included all the Project 658 missile-submarines . In March 1964 the division was transferred to Gadzhiyevo base as part of the 12th squadron, which subsequently became the Northern Fleet 3rd Flotilla. By the late 1960s the division began to fill with new 667A Yankee I submarines, and in late 1970 one Hotel II submarine was transferred to the 18th division at Gremihu. The Hotel submarines of the Northern fleet were removed from operational status during 19861991. Two 658 Hotel I submarines ("K-178" and "K-55") were transferred to the Pacific Fleet in September 1963 and 1968 and served in the 45-th division of atomic submarines on Kamchatka. Both submarines were subsequently converted into the Hotel II class. They were decommissioned in 1988 and 1990. A series of serious emergencies occurred on board Hotel I "K-19". In February 1961 a depressurization in the first containment of the reactor occurred. The next accident happened in the summer of 1961 while the "K-19" was on its first patrol mission during a naval exercise in the Atlantic Ocean close to Southern Greenland. On 04 July 1961 the patrolling submarine's port side pumps ensuring circulation of heat-exchanger gave out. The crew managed to restore the integrity of the air-tight cooling jacket.. As a result of the radiation 22 men were killed. Subsequently from 1962-1964 the reactor compartment of the "K-19" was completely removed and replaced. On 15 November 1969 the "K-19" crashed with the American submarine "Gato" (SSN-615), which had pursued the Soviet submarine in the Barens Sea. As a result of the impact the acoustic systems located in the bow were completely destroyed and the covers of the torpedo tubes were deformed. On 24 February 1972 a fire broke out onboard "K-19" while the submarine was returning from patrol and was at a depth of 120 meters some 1300 km northeast of Newfoundland. The rescue operation of the submarine lasted more than 40 days and was severely hampered by storms. More than 30 ships of Navy participated in the recovery operation and by early April the boat was towed back to the base of the Northern fleet. However, as a result of the emergency 28 crew members lost their lives.

Specifications Soviet Designation

658

658M

US-Designation

Hotel I

Hotel II

Development began

August 1956

March 1958

Design Bureau

OKB 18

Chief designer

C.H. Kovalev

Builders

Nr. 402 Severodvinsk

Construction and Outfit

October 1958 December 1962

1963-1967

Service time

January 1961-1967

1964-1991

Number of constructed 8 ships

7 (converted 658 submarines)

Armament

D-4 launch system with 3 R-21 missiles

D-2 launch system with 3 R-13 missiles

4-533mm torpedo tubes, 4- 400mm torpedo tubes Power Plant

2 pressurized water reactors, 190 MW each 2 steam turbines, 17.500 hp each

Length

114 meters

Beam

9.2 meters

Deposit

7.31 meters

Displacement

4080 m3 Surfaced 5000 m3 Submerged

Operating depth

240 meters (design) 300 meters (maximum)

Speed

18 knots - Surface 26 knots - Submerged

Crew

104 men

Endurance

50 days

Class Listing Boat

Chronology

# numb Name er

Shipyard Laid Down

1 K-19

402 Sevmash

Launche Comm. d

Strick en

10/17/19 08/08/19 11/12/19 1991 58 59 60

Notes

07/04/1961 reactor accident 1962-64 refit 1963-67 project 658M converted(Hot el II) 11/15/1969

collided with USS SSN-615 02/24/1972 fire and nuclear torpedo accident converted to SSQN 06/04 reactor accident nicknamed "Hiroshima" in storage in Polyarny 2 K-33

402 Sevmash

---------

---------

07/05/19 1988- 1963-67 61 90 project 658M converted(Hot el II)

3 K-55

402 Sevmash

---------

---------

08/12/19 ------- 1963-67 62 --project 658M converted(Hot el II) project 658T converted to SSN in reserve in Pavlovsk

4 K178

402 Sevmash

---------

---------

12/**/19 ------- commission 62 --possibly 06/30/1964 1963-67 project 658M converted(Hot el II) project 658T converted to SSN in reserve in Pavlovsk

5 K-40

402 Sevmash

---------

---------

12/28/19 1988- 1963-67 62 90 project 658M converted(Hot

el II) 1977 became SSQN,redesig nated KS-40 6 K-16

402 Sevmash

---------

---------

06/15/19 1988- 1963-67 63 90 project 658M converted(Hot el II)

7 K145

402 Sevmash

---------

---------

12/19/19 ------- 1963-65 63 --project 658M converted(Hot el II) 1966 project 701 converted(Hot el III) in storage in Sevmorput naval shipyard

8 K149

Ukrainsk 402 y Sevmash Komsoml ets

---------

---------

02/12/19 1988- 1963-67 64 90 project 658M converted (Hotel II) 1969 named

667A YANKEE I In 1958 OKB-18 started the development of a new ballistic missile submarine. Initially work was undertaken on two versions, of which only one was authorized. A.S. Kassatsiyer, the author of both versions was designated as chief designer. The development of the submarine faced significant problems regarding the launch system. During elimination of the problems the project underwent fundamental changes and as a result the completely new submarine design received the new designation 667A. The new chief designer was S. I. Kovalev. The revised 667A submarine was both developed and authorized in 1962. The external contours of the submarine were designed to achieve minimal resistance when operating under water. Unlike previous submarines, the horizontal hydroplanes were arranged on the sail. The cylinder-shaped pressure hull is divided into 10 compartments and has an exterior diameter of 9.4m. The SSBN 667A is equipped with the D-5 launch system and 16 R-27 missiles with a range of about 2400 km. They are arranged in two rows in the fourth and fifth compartments. The missiles can be launched from a depth of 40-50 meters below the surface, while the submarine is moving at a speed of up to 3-4 knots. The missiles are fired in four salvos each comprising four missiles. The time needed for pre-launch preparation is 8 minutes, and within a salvo the missiles are fired at intervals of 8 seconds. After each salvo the submarine needs three minutes return to the launching depth and between the second and third salvo it takes 20-35 minutes to pump water from the tanks into the launching tubes. The primary propulsion machinery includes two self-contained units [port and starboard], each of which consists of a pressurized water reactor reactor, and an independent turbogear assembly. The maximum speed when submerged is 27 knots. The auxiliary propulsion motors can be used for torpedo firing, to maintain electric power during emergency and provide for stand-by capability of the boat while on the surface. To reduce the noise of the submarine special propellers were created, the pressure hull was covered with sound-absorbing rubber and the external hull was covered with a antihydroacoustic coating. The footings under the main and auxiliary propulsion systems are also isolated by a layer of rubber. The 667A SSBNs were equipped with the "Cloud" battle management system which could receive signals up to a depth of 50 meters with the help of the towed antenna "Paravan." The first four 667A Yankee submarines employed the "Sigma" navigation system whereas the follow-on ships were equipped with the "Tobol" -- the first Soviet navigational system that used a satellite navigation system. This system provided reliable navigation in the Arctic Region and in the Pacific Ocean and also sustained the operational capability of the missiles at high latitudes down to 85 degrees.

The first 667A Yankee submarine, with the tactical designation K-137, was launched in 1964 at the Northern machine-building enterprise in Severodvinsk. In July 1967 the submarine "K-137" completed sea trials and at the end of 1967 it was introduced into the Northern fleet. Between 1967 and 1974 a total of 34 strategic submarines of the 667A class were build. 24 submarines were launched in Severodvinsk and 10 in Komsomolsk na Amure. In 1972-1983 the Yankee submarines along with older submarines were re-equipped with the D-5U launch system and R-27U missiles. The R-27U missile had a greater range -- up to 3000 km -- and carried multiple reentry vehicles. The upgraded submarine was designated as 667AU. In 1967 the first 667A ballistic submarines to form part of the Northern fleet were incorporated into the 31st division of strategic submarines, which was based in the port of Sayda. At the end of the 60s the 19th division of strategic submarines was also equipped with 667A submarines. Both divisions formed part of a structure consisting of 12 squadrons, which in December 1969 was transformed into the 3rd flotilla of submarines. Two divisions of 667A submarines of the Pacific fleet — 8th and 25th- - were based at Kamchatka. In the middle of the 1970s a unit of 667A SSBNs was transferred to Pavlovsk. In May, 1974 near the Navy base in Petropavlovsk a ballistic missile submarine of the 667A class collided with the American attack submarine "Pintado" (SSN-672) in a depth of about 65m. The Soviet submarine was only lightly damaged. On 03 October 1986 on board of the ballistic missile submarine "K-219" of the 667AU class an explosion took place that sparked off a fire. The cause was a depressurization of the reactor pit. The submarine was located 970 km east of the Bermuda Islands. The crew of a boat managed to surface the submarine and muffle the reactors. As a result of the accident four people were killed. The submarine was towed but on 06 October it had to be scuttled into a depth of 5,500 meters. The United States Navy normally does not comment on submarine operations. But the US Navy issued a statement regarding the release of the book "Hostile Waters" and an HBO movie of the same name, based on the incidents surrounding the casualty of the Russian Yankee submarine K-219. The United States Navy "categorically denies that any U.S. submarine collided with the Russian Yankee submarine (K-219) or that the Navy had anything to do with the cause of the casualty that resulted in the loss of the Russian Yankee submarine." Between 1979 and 1994 all Yankee submarines were removed from operational status and their missile compartments cut out to comply with arms control agreement ceilings. During their operation time the 667A and 667AM Yankee submarines had carried out 590 patrols all over the world. Two of the submarines were taken out of service in 1979, two in January 1980, one in January 1981, two in January 1982, one in November 1982, one in June 1983, one in January 1984, two in April 1985, two in March 1986, two in 1987, and the rest in 1988 and 1989.

A number of Yankee ballistic missile submarines were modified to perform other missions. 









In 1977 the "K-140" submarine was equipped with the first D-11 Soviet sea based solid-fuel missiles and received the designation 667AM Yankee II. The 12 P-31 missiles loaded on the submarine could be fired from a depth up to 50 meters. The torpedo tubes could be reloaded in less than in one minute using a "dry" launch technique. Its submerged displacement increased to 10,000 tons. The submarine "K-420" was converted to test the "Meteorite" (SS-N-24) cruise missiles. The re-equipped submarine received the designation 667M (Yankee SSGN or Yankee Sidecar). The length and the width of the SSBN were increased up to 153 m and 15-16 m respectively. Outside of the pressure hull 12 launchers for the SS-N-24 missiles were located. The re-equipment began in December 1982 and the first launches of a cruise missile was conducted in December 1983. From 1982 to 1991 some Yankee I SSBNs were equipped with 20 up to 40 launchers of SS-N-21 "Grenade". They were designated as 667AT (Yankee Notch). Unlike the "K-420" that was converted to carry the SS-N-24 missiles, the shape of the deck behind the cabin was not altered. The displacement of the submarine was increased up to 11,500 tons and the body was lengthened to 140 meters. From 1979-1984 the ballistic missile submarine "K-403" was converted into a submarine for special purposes designated as Yankee Pod. Instead of a missile compartment, it had was equipped with radio equipment and a towed hydroacoustic station. In 1990 the SSBN "K-411" was converted under the project 09774 (Yankee Stretch) into a carrier of supersmall "KS-411" submarines.

Between 1988 and 1994 most converted Yankee submarines were removed from operational status. The converted K-411 (Yankee Stretch) and K-420 (Yankee Sidecar) are reliably reported to remain in service, and some reports also suggest that K-395 [a Yankee Notch] and K-403 [Yankee Pod] may also remain in service.

Specifications Soviet Designation

667A 667AU Navaga

667 Am Navaga

US-Designation

Yankee I

Yankee II

Development began

1958

Design Bureau

Central Design Bureau for Marine Engineering "Rubin"

Chief designer Builders Construction and

S.H. Kovalev

O.YA. Margolin

Severodvinsk Komsomolsk na Amure 667A: 1964-1974

1977-1980

Outfit

667AU: 1972-1983

Service time

667A: 1967-1983 667AU: 1972-1994

1980-1990

Number of ships

34

1 converted

Armament

667A: D-5 launch system with 16 R-27 missiles

D-11 launch system with 12 R-31 missiles

667AU: D-5U launch system with 16 R-27U missiles 4-533mm torpedo tubes 2-400mm torpedo tubes Power Plant

2 pressurized water reactors 2 steam turbines, 52.000 hp each

Length

132 meters

Beam

11.6 meters

Deposit

8 meters

Displacement

7760 m3 Surfaced 9600 m3 Submerged

Maximum depth

400 meters

Speed

12 knots Surface

10000 m3 Submerged

25 knots Submerged

24 knots Submerged

Crew

120 men

130 men

Endurance

70 days

Class Listing Boat

Chronology Shipyard

# num ber

Nam e

1 K137

Lenin 402 ets Sevmash

2 K140

402 Sevmash

Laid Down

Launch Comm. Stric ed ken

Notes

11/09/1 08/28/1 11/05/1 ------ 1994 deactivated 964 966 967 ---1998 planned to scrap --------- --------- 12/30/1 1990 08/23/1968 reactor 967 accident 1977-80 project

667AM converted (Yankee II) 3 K-26

402 Sevmash

--------- --------- 09/03/1 -----968 ----

4 K-32

402 Sevmash

--------- --------- 10/26/1 1999 1999 dismantled 968

5 K216

402 Sevmash

--------- --------- 12/27/1 ------ in storage in Sayda 968 ---Bay

6 K207

402 Sevmash

--------- --------- 12/30/1 -----968 ----

7 K210

402 Sevmash

--------- --------- 08/06/1 ------ in storage in 969 ---Severodvinsk

8 K249

402 Sevmash

--------- --------- 09/27/1 -----969 ----

9 K253

402 Sevmash

--------- --------- 10/28/1 -----969 ----

1 K0 395

402 Sevmash

--------- --------- 12/05/1 969

1 K1 408

402 Sevmash

--------- --------- 12/25/1 ------ 1982-91 project 969 ---667AT("Grusha") converted to SSGN(Yankee Notch)

1 K2 411

402 Sevmash

--------- --------- 08/31/1 970

1 K3 418

402 Sevmash

--------- --------- 09/22/1 1999 project 970 667AT("Grusha") converted to SSGN(Yankee

1982-91 project 667AT("Grusha") converted to SSGN(Yankee Notch) 1999 remains operational

project 09780 converted to a midget carrier(Yankee Stretch),redesignated KS-411 remains operational

Notch) 1 K4 420

402 Sevmash

--------- --------- 10/29/1 970

1979-80 project 667M("Andromeda") converted to SSGN(Yankee Sidecar)

1 K5 423

402 Sevmash

--------- --------- 11/13/1 ------ project 971 ---667AT("Grusha") convertedto SSGN(Yankee Notch)

1 K6 426

402 Sevmash

--------- --------- 12/22/1 -----970 ----

1 K7 415

402 Sevmash

--------- --------- 12/30/1 1994 1982-91 project 971 667AT("Grusha") converted to SSGN(Yankee Notch) 1994 dismantled

1 K8 403

402 Sevmash

--------- --------- 08/20/1 971

1 K9 245

402 Sevmash

--------- --------- 12/16/1 -----971 ----

2 K0 214

402 Sevmash

--------- --------- 12/31/1 -----971 ----

2 K1 219

402 Sevmash

--------- --------- 12/31/1 1986 10/06/1986 lost 971

2 K2 228

402 Sevmash

--------- --------- 12/31/1 1995 dismantled 972 ?

2 K3 241

402 Sevmash

--------- --------- 12/23/1 1994 dismantled 971 ?

2 K-

402

--------- --------- 12/09/1 ------ in storage in

1978-80 project 09774("Akson") converted to a special operation ship(Yankee Pod),redesignated to KS-403 1999 remains operational

4 444

Sevmash

-

-

972

----

Severodvinsk

2 K5 399

199 --------- --------- 12/24/1 ------ 1982-91 project Komsomols 969 ---667AT("Grusha") k converted to SSGN(Yankee Notch)

2 K6 434

199 --------- --------- 10/21/1 -----Komsomols 970 ---k

2 K7 236

199 --------- --------- 12/27/1 ------ 1982-91 project Komsomols 970 ---667AT("Grusha") k converted to SSGN(Yankee Notch)

2 K8 389

199 --------- --------- 1970 Komsomols k

---------

2 K9 252

199 --------- --------- 1971 Komsomols k

---------

3 K0 258

199 --------- --------- 1971 Komsomols k

---------

3 K1 446

199 --------- --------- 1971 Komsomols k

---------

3 K2 451

199 --------- --------- 1971 Komsomols k

---------

3 K3 436

199 --------- --------- 1972 Komsomols k

---------

3 K4 430

199 --------- --------- 1972 Komsomols k

---------

667AM YANKEE II In 1977 the "K-140" submarine was equipped with the first D-11 Soviet sea based solidfuel missiles and received the designation 667AM Yankee II. The 12 P-31 missiles loaded on the submarine could be fired from a depth up to 50 meters. The torpedo tubes could be reloaded in less than in one minute using a "dry" launch technique. Its submerged displacement increased to 10,000 tons. The Nunn-Lugar Cooperative Threat Reduction program is scheduled to dismantle 25 Delta-class, five Typhoon-class, and one Yankee-class ballistic missile submarines capable of launching over 400 missiles with over 1,700 warheads, by the year 2003. As of September 1999 US specialists had helped disassemble one Yankee- and six Deltaclass submarines, while the Russians had destroyed another five ballistic missile subs on their own using American equipment.

Specifications Soviet Designation

667A 667AU Navaga

667 Am Navaga

US-Designation

Yankee I

Yankee II

Development began

1958

Design Bureau

Central Design Bureau for Marine Engineering "Rubin"

Chief designer

S.H. Kovalev

Builders

O.YA. Margolin

Severodvinsk Komsomol Na Amur

Construction and Outfit

667A: 1964-1974 667AU: 1972-1983

1977-1980

Service time

667A: 1967-1983 667AU: 1972-1994

1980-1990

Number of ships

34

1

Armament

667A: D-5 launch system with 16 R-27 missiles

D-11 launch system with 12 R-31 missiles

667AU: D-5U launch system with 16 R-27U missiles 4-533mm torpedo tubes 2-400mm torpedo tubes

Power Plant

2 pressurized water reactors 2 steam turbines, 52.000 hp each

Length

132 meters

Beam

11.6 meters

Deposit

8 meters

Displacement

7,760 tons Surfaced 9,600 tons Submerged

Maximum depth

400 meters

Speed

12 knots Surface

10,000 tons Submerged

25 knots Submerged

24 knots Submerged

Crew

120 men

130 men

Self-sufficiency

70 days

Class Listing Boat # number Name 1 K-140

Chronology Shipyard

Laid Launched Comm. Down

402 Sevmash ------- ------------

Stricken

12/30/1967 1990

Notes

08/23/1968 reactor accident 1977-80 project 667AM converted (Yankee II)

667AR YANKEE NOTCH The submarine "K-420" was converted to test the "Meteorite" (SS-N-24) cruise missiles. The re-equipped submarine received the designation 667M (Yankee SSGN or Yankee Sidecar). The length and the width of the SSBN were increased up to 153 m and 15-16 m respectively. Outside of the pressure hull 12 launchers for the SS-N-24 missiles were located. The re-equipment began in December 1982 and the first launches of a cruise missile was conducted in December 1983. From 1982 to 1991 some Yankee I SSBNs were equipped with 20 up to 40 launchers of SS-N-21 “Grenade”. They were designated as 667AT (Yankee Notch). Unlike the "K420" that was converted to carry the SS-N-24 missiles, the shape of the deck behind the cabin was not altered. The displacement of the submarine was increased up to 11,500 tons and the body was lengthened to 140 meters. Between 1988 and 1994 most converted Yankee submarines were removed from operational status. Some reports suggest that K-395 [a Yankee Notch] may remain in service.

Specifications Soviet Designation

667AT Navaga

US-Designation

Yankee Notch

Development began Design Bureau

Central Design Bureau for Marine Engineering "Rubin"

Chief designer

S.H. Kovalev

Builders

Severodvinsk, 'Komsomol Na Amur

Construction and Outfit

1982-1991

Service time

1983-1994?

Number of ships

6

Armament

20-40 SS-N-21 "Grenade" missiles 4-533mm torpedo tubes 2-400mm torpedo tubes

Power Plant

2 pressurized water reactors 2 steam turbines, 52.000 hp each

Length

132 meters

Beam

11.6 meters

Deposit

8 meters

Displacement

9.250 tons Surfaced 11,500 tons Submerged

Maximum depth

400 meters

Speed

12 knots Surface 25 knots Submerged

Crew

120 men

Endurance

70 days

667B DELTA I In comparison with the Yankee submarines the Delta submarines have a greater displacement and larger external dimensions. The pressure hull of the 667B submarine consists of ten compartments. The 667B submarines were equipped with D-9 launch systems and 12 R-29 missiles. The range of the R-29 missiles allowed the 667B to maintain constant combat patrol in remote areas. They are also capable of maintaining combat alert when moored at their bases. The Delta-class submarines could deploy on alert patrols in the marginal ice seas of the Soviet arctic littoral, including the Norwegian and Barents seas. Consequently, unlike their predecessors they no longer needed to pass through Western SOSUS sonar barriers to come within range their targets. And deployed close to home, they could be protected in "bastions" by the rest of the Soviet Navy. The submerged firing of the missiles can be conducted in a single salvo while the submarine is moving at a speed of 5 knots. A high degree of automation allowed a significant reduction in the time required for pre-launch preparations in comparison with the Yankee class. To improve the accuracy of the missiles, the Delta I submarines are equipped with the "Tobol-B" navigation system and the "Cyclone-B" satellite navigation system. The development of the 667B Delta I submarine was authorized in 1965, with the Rubin Central Design Bureau for Marine Engineering was in charge of the program. The Delta I submarine "K-279" was build at the Northern machine-building enterprise in Severodvinsk and was incorporated into the Northern fleet on 22 December 1972. Between 1972 and 1977 18 Delta I submarines were launched, 10 in Severodvinsk and 8 in Komsomol Na Amur. In 1973 the 667B submarine was incorporated into a division of strategic submarines of the Northern fleet based at Yagyelnaya bay. The formation of the 41st division of strategic submarines consisting of Delta I submarines was completed the same year. In 1974 the division was incorporated into the 11th flotilla of submarines. The Delta I submarines which belong to the Pacific fleet form the 25th division of strategic submarines and are based on Kamchatka. In the early 1990s the submarines were transferred to the Pavlovsk base in Primorye. The zones of patrol of the Northern fleet submarines were located in the area around Greenland and the Barents Sea, two or three days away from the submarine bases. The Delta I submarines that served in the Pacific fleet began patrols in 1976. In 1991 nine Delta I submarines served in the Northern and Pacific Fleet. Their decommissioning began in 1994, and by 1997 the missile compartments were scheduled to be removed. It is anticipated that all 667B submarines will be decommissioned in compliance with the provisions of the START-1 treaty. The prcise tatus of individual hulls, including the dates on whcih they may have been withdrawn from service, cannot be readily determined from the public record.

As of June 2000 the Russian Navy claims that it operates 26 strategic nuclear submarines carrying 2,272 nuclear warheads on 440 ballistic missiles. This force is said to consist of 5 Typhoon class submarines, 7 Delta-IV class submarines, and 13 Delta-III class submarines [which only adds up to 25, not 26 submarines]. Not all of these submarines are presently seaworthy. The Russian Navy reportedly believes that 12 strategic nuclear submarines with ballistic missiles represent the minimum necessary force structure. The Nunn-Lugar Cooperative Threat Reduction program is scheduled to dismantle 25 Delta-class, five Typhoon-class, and one Yankee-class ballistic missile submarines capable of launching over 400 missiles with over 1,700 warheads, by the year 2003. As of September 1999 US specialists had helped disassemble one Yankee- and six Deltaclass submarines, while the Russians had destroyed another five ballistic missile subs on their own using American equipment.

Specifications Soviet Designation

667B Murena

667 BD Murena-M

US-Designation

Delta I

Delta II

Development began

1965

November 1967

Design Bureau

Central Design Bureau for Marine Engineering "Rubin"

Chief designer

S.H. Kovalev

Builders

Severodvinsk Komsomol Na Amur

Severodvinsk

Construction and Outfit

1971-1977

1973-1975

Service time

1973-

1975-1996

Number of ships

18

4

Armament

D-9 launch system with 12 R-29 missiles

D-9 launch system with 16 R-29 missiles

4-533mm torpedo tubes

4-533mm torpedo tubes 2-400mm torpedo tubes

Power Plant

2 pressurized water reactors 2 steam turbines, 52.000 hp 2 steam turbines, 55.000 each hp each

Length

139 meters

Beam

12 meters

Deposit

9 meters

Displacement

9000 m3 Surfaced

155 meters

10500 m3 Submerged

11000m3 Surfaced

13000 m3 Submerged

Operating depth

390 meters (design) 450 meters (maximum depth)

Speed

12 knots Surface 25 knots Submerged

24 knots Submerged

Crew

120 men

130 men

Endurance

80 days

Class Listing Boat # numb Name er

Chronology Shipyard

Laid Launche Comm. Do d wn 01/**/1 972

12/22/1 972

Strick en

Notes

1 K279

402 Sevmash 197 1

------- 10/30/1986 --collided with USS SSN710 1992 in reserve 1998 planned to scrap

2 K447

402 Sevmash ----- 1973 -----

---------- ------- 1994 defueled ---

3 K450

402 Sevmash ----- 1973 -----

---------- ---------

4 K336

199 ----- 1974 Komsomolsk -----

---------- ------- hull NO. --possibly K366

5 K385

402 Sevmash ----- 1974 -----

---------- ---------

6 K417

199 ----- 1974 Komsomolsk -----

---------- ---------

7 K457

402 Sevmash ----- 1974 -----

---------- ------- 05/05/1998 --missile fuel leak,in reserve

8 K-

402 Sevmash ----- 1974

---------- ------- hull NO.

465

-----

---

possibly K453

9 K460

402 Sevmash ----- 1975 -----

---------- ---------

1 K0 472

402 Sevmash ----- 1975 -----

---------- 1999

1999 dismantled

1 K1 475

402 Sevmash ----- 1975 -----

---------- 1999

1999 dismantled

1 K2 477

199 ----- 1975 Komsomolsk -----

---------- ---------

1 K3 497

199 ----- 1975 Komsomolsk -----

---------- ---------

1 K4 171

402 Sevmash ----- 1976 -----

---------- ---------

1 K5 500

199 ----- 1976 Komsomolsk -----

----------

199 ----- 1976 Komsomolsk -----

---------- ------- 10/28/1988 --named 1991 unnamed

1 K7 523

199 ----- 1977 Komsomolsk -----

---------- ---------

1 K8 530

199 ----- 1977 Komsomolsk -----

----------

1 K6 512

70 Let VLKSM

1999 remains operational ??

1999 remains operational ??

667BD DELTA II The 667BD was primarily developed to increase the number of missiles on strategic submarines. Its development was approved in June 1972 under the direction of the Rubin Central Design Bureau for Marine Engineering. The 667B Delta I served as the basis for the main design features. The pressure hull was lengthened by 16 meters in the area of the fourth and fifth compartments where four additional missile tubes were located. The displacement increased in 1,500 tons, and the full speed decreased 1 knot. The 667BD submarines are equipped with the D-9D launch system and 16 R-29DD missiles. During the development of the new ballistic missile submarine several measures were applied to decrease the radiated noise level. The steam turbines include a two-spool system of shock-absorbers, the pipelines and hydraulic devices are isolated from the hulls and a new hydroacoustic coating was applied. The first 667BD entered the Navy on 30 September 1975. Between 1973 and 1975 four submarines of this project were constructed at the Northern machine-building enterprise in Severodvinsk. The 667BD submarines formed part of the 3rd flotilla of submarines of the Northern fleet based in the Yagyelnaya bay. In 1996 one submarine was removed from operational status. It is anticipated that all 667BD submarines will be decommissioned in compliance with the provisions of the START-1 treaty. The Nunn-Lugar Cooperative Threat Reduction program is scheduled to dismantle 25 Delta-class, five Typhoon-class, and one Yankee-class ballistic missile submarines capable of launching over 400 missiles with over 1,700 warheads, by the year 2003. As of September 1999 US specialists had helped disassemble one Yankee- and six Deltaclass submarines, while the Russians had destroyed another five ballistic missile subs on their own using American equipment.

Specifications Soviet Designation

667B Murena

667 BD Murena-M

US-Designation

Delta I

Delta II

Development began

1965

November 1967

Design Bureau

Central Design Bureau for Marine Engineering "Rubin"

Chief designer

S.H. Kovalev

Builders

Severodvinsk Komsomol Na Amur

Severodvinsk

Construction and

1971-1977

1973-1975

Outfit Service time

1973-

1975-1996

Number of ships

18

4

Armament

D-9 launch system with 12 R-29 missiles

D-9 launch system with 16 R-29 missiles

4-533mm torpedo tubes

4-533mm torpedo tubes 2-400mm torpedo tubes

Power Plant

2 pressurized water reactors 2 steam turbines, 52.000 hp 2 steam turbines, 55.000 each hp each

Length

139 meters

155 meters

Beam

12 meters

Deposit

9 meters

Displacement

9000 m3 Surfaced

10500 m3 Submerged

11000m3 Surfaced

13000 m3 Submerged

Operating depth

390 meters (design) 450 meters (maximum depth)

Speed

12 knots Surface 25 knots Submerged

24 knots Submerged

Crew

120 men

130 men

Endurance

80 days

Class Listing Boat # numb Name er 1 K182

Chronology Shipyard Laid Down

Launche Comm. d

Strick en

Notes

Shestidesyati 402 letie Sevmash Velikogo Oktyabrya

04/**/1 973

01/**/1 975

09/20/1 975

------- 11/04/1977 --named 1996 in reserve

2 K-92

402 Sevmash

04/**/1 973

01/**/1 975

12/17/1 975

------- 1996 in --reserve

3 K193

402 Sevmash

1974

1975

12/30/1 975

1999

12/1997 prepared for

decommissio ning 1999 dismantled 4 K421

402 Sevmash

1974

1975

12/30/1 975

------- 1996 in --reserve 2000 planned to be defuelled

667BDR DELTA III The development of the 667BDR Delta III ballistic missile submarine began in 1972 at the Rubin Central Design Bureau for Marine Engineering. This strategic submarine is equipped with the D-9R launch system and 16 R-29R missiles, and is the first submarine that can fire any number of missiles in a single salvo. The R-29R missile is the first sea-based Soviet ballistic missile carrying 3 to 7 multiple independently targetable reentry vehicles (MIRVs), with a range of 6,500 to 8000 km, depending on the number of reentry vehicles. The Delta III is equipped with the "Almaz -BDR" battle management system ensuring firing of deep-water torpedos. The inertial navigational system "Tobol-BD" is of the Delta II was replaced with the "Tobol-M-1" system, and subsequently with the "TobolM-2". The Delta III is also equipped with the "Bumblebee" hydroacoustic navigational system to determinate its position through hydroacoustic buoys. Instead of the hydroacoustic system "Kerch" was used on the 667BD submarines, the Delta III uses the new "Rubikon" hydro-acoustic system. The advanced Delta III SSBN entered service in 1976, and by 1982 a total of fourteen submarines were commissioned. All of them were build at Severodvinsk. The operational lifetime of these submarines is estimated to be 20-25 years. The Delta III submarines which served in the Northern fleet formed a division and were based in the port of Sayda in the Yagyelnaya bay and in the Olyenya port. In the early 90s the ballistic missile submarines were transferred to Yagyelnaya. The Delta III that served in the Pacific Fleet formed a division of SSBNs which is based on Kamchatka. When the START-1 treaty was signed in 1991 five 667BDR SSBNs still served in the Northern (3 - in Yagyelnaya, 2 - in Olyenyey ) and nine in the Pacific Fleet. One Delta III submarine of the Northern fleet was decommissioned in 1994. The Nunn-Lugar Cooperative Threat Reduction program is scheduled to dismantle 25 Delta-class, five Typhoon-class, and one Yankee-class ballistic missile submarines capable of launching over 400 missiles with over 1,700 warheads, by the year 2003. As of September 1999 US specialists had helped disassemble one Yankee- and six Delta-class submarines, while the Russians had destroyed another five ballistic missile subs on their own using American equipment. As of June 2000 the Russian Navy claims that it operates 26 strategic nuclear submarines carrying 2,272 nuclear warheads on 440 ballistic missiles. This force is said to consist of 5 Typhoon class submarines, 7 Delta-IV class submarines, and 13 Delta-III class submarines [which only adds up to 25, not 26 submarines]. Not all of these submarines are presently seaworthy. The Russian Navy reportedly believes that 12 strategic nuclear submarines with ballistic missiles represent the minimum necessary force structure. According to media reports a classified presidential decree of 04 March 2000 established this force goal for the period through 2010.

Specifications Soviet Designation

667BDRM Dolphin

US-Designation

Delta IV

Development began

1972

Design Bureau

Central Design Bureau for Marine Engineering "Rubin"

Chief designer

S.H. Kovalev

Builders

Nr. 402 Severodvinsk

Construction and Outfit

1975-1981

Service time

1976-

Number of ships

7

Armament

D-9 RM launch system with 16 R-29R missiles 4-533mm torpedo tubes

Power Plant

2 pressurized water reactors, 90 MW each 2 steam turbines, 20.000 hp each

Propellers

2 × 7 blade fixed-pitch

Length

155 meters

Beam

11.7 meters

Draft

8.7 meters

Displacement

8,940 tons Surfaced 10,600 tons Submerged

Operational depth

320 meters (design) 400 meters (maximum depth)

Speed

13-14 knots Surface 22-24 knots Submerged

Crew

130 men

Endurance

80 days

Class Listing Boat #

numbe Name r

Chronology Shipyard

Laid Dow

Launched

Comm.

Stricke n

Notes

n 1 K-441

26 Zvezd a KPSS

402 Sevmash

1975

2 K-424

402 Sevmash

3 K-449

1976

12/**/197 6

---------

04/1992 unnamed 1996 in reserve

------- ------------

1977

---------

1997 in reserve

402 Sevmash

------- ------------

1977

---------

1996 in reserve

4 K-455

402 Sevmash

------- ------------

1978

---------

1998-99 in reserve

5 K-490

402 Sevmash

------- ------------

1978

---------

1998-99 in reserve

6 K-487

402 Sevmash

------- ------------

1978

---------

1998-99 in reserve

7 K-44

402 Sevmash

------- ------------

1979

---------

1997 in reserve

8 K-496

402 Sevmash

1976

01/**/197 8

1979

9 K-506

402 Sevmash

1977

01/**/197 9

1979

1 K-211 0

402 Sevmash

1977

01/**/197 9

1980

1 K-223 1

402 Sevmash

------- ------------

1980

---------

1998-99 in reserve

1 K-180 2

402 Sevmash

1978

1980

1 K-433 3

402 Sevmash

------- ------------

1981

---------

1997 in reserve

1 K-129 4

402 Sevmash

1979

1981

---------

1997 in reserve possibly still in

12/**/198 0

12/**/198 1

operatio n

667BDRM Dolphin DELTA IV The 667BDRM Delta IV submarine, which was constructed parallel to the Typhoon class, is a further modification of the previous Delta. In comparison with the Delta III submarine the diameter of the pressure hull was increased and the bow was lengthened. As a result the displacement of the submarine was increased by 1,200 tons and it was 12 meters longer. To increase the reliability of the pressure hull, the tip and intercut-off bulkheads are made of specially processed steel. The Delta IV submarines employs the D- 9RM launch system and carries 16 R-29RM liquid-fueled missiles which carry four multiple independently targetable reentry vehicles.Unlike previous modifications, the Delta IV submarine is able to fire missiles in any direction from a constant course in a circular sector. The underwater firing of the ballistic missiles can be conducted at a depth of 55 meters while cruising at a speed of 67 knots. All the missiles can be fired in a single salvo. The 667BDRM Dolphin submarines are equipped with the TRV-671 RTM missiletorpedo system that has four torpedo tubes with a calibre of 533 mm. Unlike the Delta III, it is capable of using all types of torpedos, antisubmarine torpedo-missiles and antihydroacoustic devices. The battle management system "Omnibus-BDRM" controls all combat activities, processing data and commanding the torpedo and missile-torpedo weapons. The "Shlyuz" navigation system provides for the improved accuracy of the missiles and is capable of stellar navigation at periscope depths. The navigational system also employs two floating antenna buoys to receive radio-messages, target destination data and satellite navigation signals at great depth. The submarine is also equipped with the "Skat- VDRM" hydroacoustic system. During the development of the 667BDRM SSBN several measures were included to reduce its noise level. The gears and equipment are located on a common base isolated from the pressure hull, and the power compartments are also isolated. The efficiency of the antihydroacoustic coatings of the light outer hull and inner pressure hulls have been increased. Newly designed five-bladed propellers with improved hydroacoustic characteristics are employed. The development of the Delta IV submarine began on 10 September 1975 by the Rubin Central Design Bureau for Marine Engineering. The first Dolphin submarine was launched in January 1985 and in December 1985 the first Dolphin submarine was introduced into Northern fleet. Between 1985 and 1990 seven Dolphin SSBN were constructed by the Sevmashpredpriyatiye Production Association in Severodvinsk. Initially all the Delta IV submarines were based with the Northern Fleet at Olenya. All the submarines of this class serve in the 3rd flotilla of strategic submarines of the Northern fleet, which has relocated to Yagyelnaya.

The operational lifetime of these submarines is estimated to be 20-30 years, though in order to operate a ship for this period requires that a major overhaul be performed every 7-8 years. Otherwise, a submarine's service life shrinks to 10-15 years. The four-year repair works on the first Delta-IV (K-51) submarine were completed in November 1999 at Zvezdochka shipyard in Severodvinsk. The submarine was expected to operate from its home base in Gadzhievo at the Kola Peninsula for 5-7 more years. As of June 2000 the Russian Navy claims that it operates 26 strategic nuclear submarines carrying 2,272 nuclear warheads on 440 ballistic missiles. This force is said to consist of 5 Typhoon class submarines, 7 Delta-IV class submarines, and 13 Delta-III class submarines [which only adds up to 25, not 26 submarines]. Not all of these submarines are presently seaworthy. The Russian Navy reportedly believes that 12 strategic nuclear submarines with ballistic missiles represent the minimum necessary force structure. According to media reports a classified presidential decree of 04 March 2000 established this force goal for the period through 2010.

Specifications Soviet Designation

667BDRM Dolphin

US-Designation

Delta IV

Development began

September 1975

Design Bureau

Central Design Bureau for Marine Engineering "Rubin"

Chief designer

S.H. Kovalev

Builders

Nr. 402 Severodvinsk

Construction and Outfit

February 1981-1992

Service time

December 1985-

Number of ships

7

Armament

D-9 RM launch system with 16 R-29 RM missiles 4-533mm torpedo tubes

Power Plant

2 pressurized water reactors, 90 MW each 2 steam turbines, 20.000 hp each

Propellers

2 × 7 blade fixed-pitch

Length

167 meters

Beam

12 meters

Draft

8.8 meters

Displacement

11,740 tons Surfaced

18,200 tons Submerged Operational depth

320 meters (design) 400 meters (maximum depth)

Speed

13-14 knots Surface 22-24 knots Submerged

Crew

130 men

Endurance

80 days

Class Listing Boat # num ber

Name

Shipyar Laid d Down

Chronology Launch Comm. Stric ed ken

Notes

1 K-51

402 02/23/1 01/**/1 12/29/1 Sevmash 981 985 986

1996-11/1999 deactivated for refit 2000 in service

2 K-84

402 11/**/1 12/**/1 02/**/1 Sevmash 984 985 986

in service

3 K-64

402 11/**/1 12/**/1 02/**/1 Sevmash 985 986 988

in service

4 K114

402 12/**/1 09/**/1 02/**/1 Sevmash 986 987 989

late 1999 planned to dismantle at Zvezdochka

5 K117

402 09/**/1 09/**/1 03/**/1 Sevmash 987 988 990

in service

6 K-18

402 09/**/1 11/**/1 02/**/1 Sevmash 988 989 991

in service

7 K407

Novomos kovsk

402 11/**/1 01/**/1 02/20/1 Sevmash 989 991 992

in service

K8 ???

402 Sevmash

Cancelled under construction

K9 ???

402 Sevmash

Cancelled under construction

941 TYPHOON During the Cold War the Typhoon submarines prowled the waters of the North Atlantic. These submarines do not have to submerge or go to sea to launch their long-range missiles. They are able to do so tied up at their docks. The Typhoon is the world’s largest submarine and was one of the most feared weapons of the Cold War. Each submarine is capable of carrying twenty long-range ballistic missiles with up to 200 nuclear warheads that were once aimed at the United States. The design of the Typhoon submarine is multi-hulled and bears resemblance to a catamaran. The submarine has two separate pressure hulls with a diameter of 7.2 m each, five inner habitable hulls and 19 compartments. The pressure hulls are arranged parallel to each other and symmetrical to a centerplane. The missile compartment is arranged in the upper part of the bow between the pressure hulls. Both hulls and all compartments are connected by transitions. The pressure hulls, the centerplane and the torpedo compartment are made of titanium and the outer light hull is made of steel. A protected module, comprising the main control room and electronic equipment compartment, is arranged behind the missile silos above the main hulls in a centerplane under the guard of retractable devices. The submarine's design includes features to enable it to both travel under ice and for icebreaking. It has an advanced stern fin with horizontal hydroplane fitted after the screws. The nose horizontal hydroplanes are in the bow section and are retractable into the hull. The retractable systems include two periscopes (one for the commander and one for general use), radio sextant, radar, radio communications, navigation and direction-finder masts. They are housed within the sail guard. The sail and sail guard have a reinforced rounded cover for ice-breaking. The submarine is equipped with the D-19 launch system with 20 solid-fuel propellant R39 missiles which have a range of up to 10,000 km. They are arranged in silos in two rows in front of the sail between the main hulls. The Typhoon has an automated torpedo and missile loading system including 6 torpedo tubes with calibres of 650 and 533 mm. The main machinery consists of two reactors each and two steam turbines of 190 MW that provide a maximum speed of 25-27 knots. Compared to the first and second generation of SSBNs the Typhoon enjoys far greater maneuverability Despite of its larger displacement the Typhoons are less noisy than their predecessors. To reduce the acoustic signature a two-spool system of rubber-cord pneumatic shock-absorption is employed as well as a block layout of gears and equipment, a new sound isolation and andrihydroacoustic coating. The Typhoons are equipped with the "Slope" hydroacoustic system that consists of four hydroacoustic stations. The "Slope" system allows to track 10-12 vessels simultaneously. It also employs two floating antenna buoys to receive radio messages, target designation data and satellite navigation signals at great depth and under an ice cover.

The development of the 941 heavy strategic submarine was authorized in December 1972, and on 19 December 1973 the governmental officially issued the order to design and build the 941 ballistic missile submarine. The developer was the Leningrad design bureau which is now the Central Design Bureau for Marine Engineering "Rubin". After intensive testing the heavy ballistic missile submarine 941-"TK-208" was commissioned in September 1980 and introduced into the Northern fleet on 12 December 1981. Between 1981 and 1989 six Typhoon submarines entered service. They formed part of the 1st flotilla of atomic submarines based in the Western Theater of the Northern fleet based at Nyerpichya. A seventh vessel was begun but never finished. The Typhoon submarines were initially intended to be retrofitted with a replacement of the D-19 launch system with an advanced system, and the new SS-N-28 missile. The lead unit of this class, the TK-208, had been in overhaul since 1992 with the intent of receiving these modifications, but it now appears that it will not return to service. All but one of the Typhoon class submarines are slated to be withdrawn from service within a few years, and it is unlikely that units of the class would be modified to accomodate new missiles. In 1997 two Typhoon submarines were decommissioned. The operational lifetime of these submarines is estimated to be 20-30 years, though in order to operate a ship for this period requires that a major overhaul be performed every 7-8 years. Otherwise, a submarine's service life shrinks to 10-15 years. Navy officials claim that it is possible to extend operations of the Typhoons until 2005-2007. The Nunn-Lugar Cooperative Threat Reduction program is scheduled to dismantle 25 Delta-class, as many as five Typhoon-class, and one Yankee-class ballistic missile submarines capable of launching over 400 missiles with over 1,700 warheads, by the year 2003. In 1999 Secretary of Defense Bill Cohen approved the contract to begin dismantlement of the first Typhoon nuclear submarine. If and when all of these submarines are dismantled, 1,200 nuclear weapons will be removed from operational systems. As of June 2000 the Russian Navy claimed that it operates 26 strategic nuclear submarines carrying 2,272 nuclear warheads on 440 ballistic missiles. This force was said to consist of 5 Typhoon class submarines, 7 Delta-IV class submarines, and 13 Delta-III class submarines [which only adds up to 25, not 26 submarines]. Not all of these submarines are presently seaworthy. According to one published report as of 1999 only a single Typhoon remained operational [probably TK-20], and most estimates would suggest that no more than three boats were in service by early 2000. In January 2000 it was reported that three of six Russian Typhoon-class submarines would remain in active operation to test the new Bark-class strategic missiles, contrary to both the plans of the Co-operative Threat Reduction program and reports that Bark-class missiles had been cancelled due to design failures. The Russian Navy reportedly believes that 12 strategic nuclear submarines with ballistic missiles represent the minimum

necessary force structure. According to media reports a classified presidential decree of 04 March 2000 established this force goal for the period through 2010.

Specifications Soviet Designation

941 Akula

US-Designation

Typhoon

Development began

December 1973

Design Bureau

Central Design Bureau for Marine Engineering "Rubin"

Chief designer

S.H. Kovalev

Builders

Nr. 402 Severodvinsk

Construction and Outfit

March 1977-September 1989

Service time

December 1981-

Number of ships

6

Armament

D-19 launch system with 20 R-39 missiles 2-650mm torpedo tubes 4-533mm torpedo tubes

Power Plant

2 pressurized water reactors, 190 MW each 2 steam turbines, 50.000 hp each

Propellers

2×7 blade fixed-pitch shrouded

Length

170-172 meters

Beam

23-23.3 meters

Draft

11-11.5 meters

Displacement

23,200-24,500 tons Surfaced 33,800-48,000 tons Submerged

Maximum diving depth

500 meters

Speed

12-16 knots Surface 25-27 knots Submerged

Crew

150 men (50 officers)

Endurance

90-120 days

Class Listing

Boat # numb Na er me

Chronology Shipyard

Laid Down

Launche Comm. d

Strick en

Notes

1 TK208

402 Sevmash

03/03/1 977

09/23/1 980

12/12/1 981

1992 missile accident, deactivated for refit 2001 reactivated?

2 TK202

402 Sevmash

10/01/1 980

04/26/1 982

12/28/1 983

3 TK12

402 Sevmash

04/27/1 982

12/17/1 983

12/27/1 984

1997- deactivated for refueling 2000 in reserve

4 TK13

402 Sevmash

01/05/1 984

02/21/1 985

12/29/1 985

1997- undergoing overhaul 2000 in reserve

5 TK17

402 Sevmash

02/24/1 985

08/**/1 986

11/06/1 987

in service slated for dismantlement ??

6 TK20

402 Sevmash

01/06/1 987

07/**/1 988

09/04/1 989

in service

TK7 210

402 Sevmash

2000

1997- deactivated for refueling 2000 dismantled

Cancelled under construction

935 Borei On 16 October 1996 Commander in Chief of the Russian Navy ADM Feliks Gromov announced that work would start on a new-generation strategic nuclear-powered submarine, which he said would be "two or three times more powerful" than any submarine currently in the fleet. The keel of the fourth-generation strategic missile submarine Yuri Dolgoruky was laid down at the Sevmash State Nuclear Ship-Building Centre at Severodvinsk on 2 November 1996. The keel-laying was postponed for a week after poor weather made it impossible for high ranking officials to attend, including First Deputy Defense Minister Andrei Kokoshin, Presidential Chief of Staff Anatoly Chubais, Moscow mayor Yuri Luzkhov, and Admiral Gromov. Kokoshin described the new Yuri Dolgoruky as a stateof-the-art submarine with "substantial improvements" over those currently in service, and Chubais termed the new submarine "a totally unique thing, a submarine for the next century." The city of Moscow is sponsoring the project, as the lead vessel is named after Prince Dolgoruky, the traditional founder of the city. The wages of shipyard workers and the crew of the new boat will [reportedly] be paid by the city in the event that the federal government is unable to pay. So-called "Presentation" weapons were commonplace in the Red Army during the Great Patriotic War. Presentation weapons were almost always the result of monetary collections taken up locally and voluntarily, and offered towards the cost of various vehicles or other items in the name of some personality or entity. Thus, the workers of a factory, town, or even just local citizens could take up a collection and "buy" a tank or aircraft (etc.) in the name of their Factory, group, or perhaps a local or even national figure -- contemporary or historical. One of the oldest Russian annals, the Lavrenty Chronicle, was compiled in Nizhny Novgorod at the request of Prince Dmitry Konstantinovich. It contains "The Instructions to His Children of Vladimir Monomakh". Vladimir Monomach ruled in Kiev, the then capital of the Russian state, between 1113 and 1125. He was the father of Yuri Dolgoruky, the founder of Moscow. The meeting of Prince Dolgoruky and Prince Svyatoslav Olgovich on 04 April 1147 in Moscow is the oldest mentioning of Moscow in chronicles. This is the first submarine of the new Borei-class [Boreas], with a length of 170 meters, a body diameter around 10 metres, and a submerged speed of over 25 knots (over 45km/h). With about half the displacement of the Typhoon, the 935 class will nonetheless carry 20 SLBMs of a new type. The lead unit of Russia's fourth generation ballistic missile submarine would have reached initial operational capability by 2004, if the current plan of launching it by 2002 remained on track. But the Navy leadership's plans to launch one new-generation submarine per year beginning in 2002 appear unrealistic with the planned financing of

national defense. Consequently no more than 9-12 missile-armed submarines with a total of 800-1,000 warheads are likely to remain in the naval strategic nuclear forces by 2010, although the START I and II treaties allow Russia to have up to 1,750-1,900 warheads in the naval component. As of early 1999 it appeared that construction had ceased on the first unit of the Boreiclass, pending a redesign of the ship to accomodate a different missile from the originally intended SS-N-28, which had failed its first three test firings and was subsequently said to have been abandoned. The first remains under construction with a scheduled launch in 2005. Other sources state the commissioning year to be 2007-2010, depending on availability of funds. The creation of D-19UTH missile complex designed for the new nuclear strategic submarines of the Borei-class has been undertaken at GRTs KB named after V. P. Makeev. The D-19UTH launch complex is to replace the D-9 launch complex with RSM52 ballistic missiles. The new complex will be equipped with a solid-fuel ballistic missile of greater reliability and longer range, capable of being fired from the surface and underwater positions. As of June 2000 the Russian Navy claims that it operates 26 strategic nuclear submarines carrying 2,272 nuclear warheads on 440 ballistic missiles. This force is said to consist of 5 Typhoon class submarines, 7 Delta-IV class submarines, and 13 Delta-III class submarines [which only adds up to 25, not 26 submarines]. Not all of these submarines are presently seaworthy. The oldest of these boats, which entered service in 1983, will reach the end of their 20-25 year service life about the time the first 935 is commissioned. The Russian Navy reportedly believes that 12 strategic nuclear submarines with ballistic missiles represent the minimum necessary force structure. According to media reports a classified presidential decree of 04 March 2000 established this force goal for the period through 2010.

Specifications Builders: Power Plant:

nuclear reactor, geared steam turbines, shaft

Length:

170 meters

Beam:

meters

Displacement:

11,750-12,250 tons Surfaced 16,750-24,000 tons Submerged

Speed:

+ 25 knots

Crew:

Officers, Enlisted

Armament:

20 R-39M Grom RSM-52V SS-N-28

Date Deployed:

Class Listing Boat

Chronology

# numb Name er

Shipyard Laid Down

1 -----

402 Sevmash

Yuri Dolgoruky

10/25/19 96

Notes

Launch Commisio Strick ed ned en 20052010?

1998 redesigne d and reconstruc ted

2

402 Sevmash

20062011?

?

3

402 Sevmash

20072012?

?

4

402 Sevmash

20082013?

?

5

402 Sevmash

20092014?

?

6

402 Sevmash

20102015?

?

7

402 Sevmash

20112016?

?

8

402 Sevmash

20122017?

?

9

402 Sevmash

20132018?

?

1 0

402 Sevmash

20142019?

?

1 1

402 Sevmash

20152020?

?

1 2

402 Sevmash

20162021?

?

Tu-4 BULL The massive World War One Il'ya Muromets bomber [namded after a legendary Russian folk hero who destroyed the Tartar Army single handed] was the largest four-engined aeroplane of its time. Designed by Igor Sikorsky, it able to carry a significant bomb load and to engage in long distance reconnaissance missions. In 1935 Tupolev built the world's largest passenger plane, the Maxim Gorky, which was used for propaganda flights. The Soviets began the development of a heavy bomber force prior to 1935, and by 1940 they had the largest force of four engined bombers in the world (the Soviets had 10,000 to 12,000 aircraft of all types at the outbreak of World War II). However, strategic bombing played a minor role in Soviet wartime military operations. During World War II an arrangement of aerial maneuvers code-named FRANTIC comprised the largest and most complete military projects linking the United States of America and the Union of Soviet Socialist Republics as allies against Germany. This was the only direct combat cooperation between the American and Soviet war efforts. The United States Army Air Force conducted FRANTIC as an extension of the Combined Bomber Offensive (CBO) in Europe. The 8th and 15th Air Forces flew B-17 Flying Fortresses deep into central Europe to attack German war materiel and military bases, then continued east to land in the Ukraine. Soviet troops serviced and protected the Army Air Force units, which rearmed and flew of to hit more targets enroute to their home stations. Work on a long range bomber, capable of striking at targets in deep enemy territory, began in the Soviet Union in 1943. Three American B-29 bombers flying against Japan had landed in Siberia and were seized by the Soviets. By August 1944 the the "64" design had been developed at OKB-156 under the direction of A.N. Tupolev, with similar characteristics. The maximum range of the Soviet bomber carrying a load of 4,000 kg was planned to be 6,500 km. However, in June 1945, after development began, the Soviet Union decided to drop the project "64" and build an exact copy of the B-29 bomber instead. This Soviet copy of the B-29 was also built by OKB-156, under the designation B-4 or product "P". The project received the highest priority and was under direct control of the Politbureau, and was supposed to be completed within two years. In mid 1945 the three American B-29 bombers were delivered to Moscow. One plane was transferred to the Flight-test institute in Zhukovski to train pilots for preparing flight training manuals, the second plane was disassambled to study its' design and the third was left as a yardstick. However, the Soviets decided not to attempto to copy the American engine, and instead equipped the bomber with the Soviet ASH-73TK engine designed by A.D. Shvetsov. This engine retained the B-29's original turbocompressor and the magnet and heat-resistant bearings. The Soviet bomber also carried improved gun turrets of Soviet design.

The Bull is a midwing, four-engine, medium bomber with two bomb bays centrally located in the fuselage, extending fore and aft of the wing. Defensive armament consists of four turrets located in upper forward, lower forward, lower rear, and tail positions. The first B-4 bomber was finished in the spring of 1947 and carried out its' first flight on 19 May 1947. Flight tests continued through 1949. Full-scale production of the aircraft, under the designation Tu-4. began in 1947 at the plant Nr. 22 in Kazan and at plant Nr. 18 in Kuibyshev. In 1948, an additional construction plant in Moscow, Nr. 23, was adapted to build the TU-4. Production in Moscow began in 1950 and when total production of the TU-4 finally finished in 1952, a total of 847 bombers had been produced [according to Russian sources -- according to Western estimates, a maximum of about 1,300 were deployed by 1954]. The deployment of the TU-4 bomber began in 1949, and they replaced wartime bombers such as the IL-4, B-25, PYE-8, B-17 and B-24 aircraft in Long-Range Aviation units. Patrolling mainly over Soviet territory, the bombers had a capability to strike at Europe, Northern Africa, the Near East and Japan. Immediately after serial production of the Tu-4 was initiated, work began to adapt the bomber to strike at American territory. Some airplanes were outfitted to carry nuclear bombs and were designated as TU-4A. During re-equipment, the bomber was equipped with a thermostatically controlled heated bomb bay, a suspension unit for the bomb was developed, and biological protection devices for the crew were supplied. Some TU-4 bombers were equipped with aerial refueling devices, and very few were outfitted with additional fuel tanks located under the wings. They were deployed in 1952, though the majority of the TU-4 were not re-equipped with air refueling. Although the limited range of the Tu-4 rendered it incapable of striking the United States and subsequently returning to bases in the Soviet Union, neither country was a stranger to one-way strategic bombardment missions, given the precedent of the FRANTIC operations in World War II. In 1948, work on the "Comet" missile project began. The modified version of the Tu-4 bomber - the TU-4K - was supposed to be equipped with two KS-1 air to surface missiles and the "Comet-1"/"Comet-2" guidance system. The first TU-4K prototype was finished in 1951, with production testing in 1951 and 1952. Between July 1952 and January 1953 the bomber was tested, and subsequently deployed with naval aviation. In 1950 OKB Tupolev studied the possibility of equipping the TU-4 with the turbo-prop engines of the TB-2 aircraft. But the flight performance was only increased by 14-20 percent, and the project did not proceed into development. The "Burlak" weapon system was developed in the early 1950s to protect the bomber from attacks. The TU-4 bomber towed a pair of MIG-15 fighters as an escort. However, after proving that this was technically feasible, the project was cancelled. Some TU-4 were converted into secret command centers and though designed primarily as a bomber, the Tu-4 could also be equipped for reconnaissance missions.

From 1954 on, the bombers Tu-4 were gradually replaced by Tu-16 medium-range bombers, and from 1956 on by Tu-95 intercontinental bombers. Although the Soviets have phased it out as an operational bomber, it was used for this purpose for some years thereafter in the Chinese Air Force. From the early 1960s on, the TU-4 were only used as transport aircraft, training aircraft and flying airforce laboratories. In 1955 some 300 TU-4 aircraft were converted to the transport aircraft TU-4D configuration, which remained in operational service through the mid-1960s. This modification was adapted to transportation and airdrop 28 parachute air-troopers with their equipment. Despite this, the aircraft bomber retained its long-range bombing capabilities. In 1956, the TU-4 was experimentally converted into a troop carrying aircraft (TU-4T). The TU-4 served as the basis for the passenger plane TU-70 and the military transport aircraft TU-75. In the early 1960s, a total of six Tu-4 were converted into flying laboratories (TU-4LL) to support testing of piston, turbo-prop and turbojet engines. In the late 1950s some aircraft were converted to the TU-4USHS trainer.

Specifications Soviet Designation

TU-4

US-Designation

Bull

Design Bureau

OKB-156 Tupolev

Manufacturer

Plant Nr. 22 Kazan Plant Nr. 18 Kuibyshev Plant Nr. 23 Moscow

Power Plant

4 ASH-73TK engines

Thrust

1790 kw each

Length

30.179

Height

8.46

Wingspan

43m

Wing surface

161.7sqm

Speed

558 km/h (at 10250m) 435 km/h (ground)

Ceiling

11.200m

Weight (empty)

35.270kg

Fuel weight

4.280kg

Maximum take-off weight

65.000kg

Normal load

6.000kg

Maximum load

9.000

Operational Range

5.400km (with a load of 3.000kg) 3.580 km (with a load of 9.000kg)

Maximum Range

6.200km (with a load of 3.000kg)

Armament

Six 1000-Kt bombs (TU-4) 1 nuclear bomb (TU-4a) 2 KS missiles (TU-4K)

Systems Crew

7

Accomodation Unit cost Development began

1945

First Flight

5/19/1947

Series production

1945-1952

Date deployed

1949

Inventory

Historical Review - Western Estimates Soviets possess partial sets of B-29 blueprints (according to post-war defector)

1943

B-29 lands at Vladivostok in flying condition and is interned

July 1944

USSR acquires two more wartime B-29s

November 1944

Estimated start of flight testing

1945

First discovery

1946

Estimated start of series production

1947

Initial operational capability

1949

Significant operational capability

1950

Production complete

1953

Phase out complete

1960

Il-28 BEAGLE (ILYUSHIN) The first jet bomber to enter service with the Soviet air force, the Il-28 tactical day bomber was Russia's equivalent to the British Canberra. First flown on the 08 August 1948, the Il-28 entered service with bomber squadrons in 1950 and remained in production for many years. This jet-powered medium bomber was built in enormous numbers [over 6000 were built by the Soviet Union and China, according to some estimates] and adapted to fulfil a variety of roles. Designed in the late 1940s with an orthodox configuration, the Il-28 was powered by Rolls-Royce turbojets supplied by Britian just before the Cold War started. Two Klimov VK-1 centrifugal-flow turbojets (developed from the Rolls-Royce Nene) were mounted beneath the wings in pods, which extend beyond wings’ leading and trailing edges. The high-mounted wings featured a straight leading edge and forward-tapered trailing edge with blunt tips. The unswept wing contrasts with the swept tailplane but ensures pitch control in high Mach dives. The tubular fuselage was cigar-shaped, and tapering to the rear, with a rounded, glassed-in nose and bubble canopy. The WWII-style greenhouse contains the bombardier/ navigator's electronics and visual bombsight. The tail fin is swept-back and tapered with a blunt tip. The tail of the Beagle contains the rear gunner/radio operator and two more 23mm NR-23 cannon. Flats are low-mounted on the fin, swept-back, and tapered with blunt tips. A glassed-in tail gunner compartment is to the rear of the tail. It is armed with two 23 mm NR-23 cannon in a fixed nose installation and two 23 mm NR-23 cannon in the tail turret. Up to 3000 kg of disposable stores can be carried in a lowerfuselage weapons bay. The Il-28R variant is a three-seat tactical reconnaissance version with four or five cameras. This model was also used for electronic intelligence gathering with a revised electronic fit. The Il-28U variant is an operational conversion trainer lacking radar and armament but fitted with a second cockpit in the nose. The Il-28 was retired from the Soviet Air Force and Navy in the 1980s, serving as target tugs and ECM platforms. It also served with a large number of export customers, and was exported to over 20 countries]. Beagles served with most of the major Arab air forces. The arrival of 50 Il-28s in Egypt in 1956 was alarming to the Israelis, and a significant factor in the origins of the 1956 Suez War, in which all the Il-28s sent to Nasser were destroyed on the ground. Again in 1967 and yet again in 1973, the Il-28 featured as a significant ground target for the Israeli Air Force. During the Cuban Missile Crisis of 1962, Soviet Premier Khrushchev agreed to remove the offensive missiles as well as the medium range twin-jet Il-28 "Beagle" bombers being assembled in Cuba. Il-28s also saw service with the Nigerians during the Biafra War. East Germany and Finland flew only the target-towing version, without armament. By the early 1990s more than 300 Beagles remained in service with a number of ex-Soviet allies and clients.

Specifications Primary Function:

Light bomber

Similar Aircraft

Canberra, Yak-28 Brewer

Contractor:

ILYUSHIN

Power Plant:

two Klimov VK-1A

Thrust:

26.48 kN (5,952 lb st) each

Length:

57 ft, 11 in (17.6 m)

Height:

6.70 m

Wingspan:

70 ft, 5 in (21.5 m)

Speed:

902 km/h at 4500 m [maximum] 800 km/h at sea level 876 km/h cruising speed at optimum altitude

Ceiling:

12300 m

Weight: empty

11890 kg

Maximum Takeoff Weight:

21200 kg

Range:

2400 km at 10000 m 1135 km at 1000 m

Armament:

Bombs, two 23-mm cannons in tail

Crew:

Three

Unit Cost: Date Deployed: Current Users:

Romania and People’s Republic of China (H-5)

Former Users:

Afghanistan, Egypt, Hungary, Iraq, North Korea, Poland and Yemen

Tu-16 BADGER (TUPOLEV) The Tu-16 was designed as an high-speed jet bomber for operations in theaters close to the Soviet Union. Intended to replace the propeller-driven TU-4, the greatest challenge during development was to doubling the speed to improve survivability in the face of enemy fighters. OKB A.N. Tupolev started working on the design of a new jet bomber soon after development of the TU-4 was completed. The resulting design "82" consisted of a sweptwing aircraft with RD-45F or VK-1 turbojet engines. The bomber was supposed to have a speed of Mach 0.9-0.95 with a range and payload were comparable to the TU-4. After the bomber's operational characteristics were coordinated with the military, the government officially approved the development of the "82" aircraft in 1948. The prototype, which was the first Soviet aircraft with swept-wings, made its' first flight on 24 March1949. It reached a speed of 934 km/h, 20 percent faster than the TU-14 which also had BK-1 engines. The "82" design was initially supposed to serve as the basis for the "83" bomber, but with the start of serial production of the Il-28, the project was dropped. Based on the results of the "82" aircraft, in 1950 OKB Tupolev started developing the "492" heavy long-range bomber that had a better performance than the TU-4 and the Il28. The design provided for a bomb load of 6000 kg, a range of 7,500 km, a speed of 1000 km/h and a ceiling of 12000-13000 m. The maximum bomb load could be increased up to 12000kg. The aircraft could be outfitted with three different types of engines: two AM-3 engines with a thrust of 8750 kg, 4 engines ТR-3A engines (5000 kg) or 4 TR-5 two circuit engines (5000 kg). As the TR-5 engines were the most reliable at that time, Tupolev was charged with the development of an experimental long-range bomber (project "88") equipped with two TR-5 engines. However, work on the AM-3 engines continued and was completed in August 1951. The wings of the Badger are mid-mounted, swept-back, and tapered with blunt tips. There are fences on top of the wings and its landing gear pods extend beyond the wings’ trailing edges. The Badger's engine(s) are two turbojets mounted in wing roots which extend beyond the leading and trailing edges of the wing root. The engines also have round air intakes. Its fuselage is long, slender, and bulging where the engines are mounted and tapered to the tail. It has a round, glassed-in nose and a stepped cockpit. The tail is swept-back, tapered fin and flats with blunt tips. The Badger also has a tail gunner compartment. All models of Badger are equipped for aerial refueling. The first prototype of the "88" aircraft received the designation Tu-16 and carried out the first flight on 27 April 1952. During flight tests, the aircraft exceeded the expected speed but lagged in range due to insufficient engine performance. As a result, the second prototype had a reduced weight though less speed at small and medium altitudes. In April 1953 it actually exceeded the expected range.

In December 1952, series production was initiated. In 1953 series production of the TU16 began at the plant Nr. 22 in Kazan and in 1954, also at the plant Nr.1 in Kuibyshev and at the plant Nr. 64 in Voronezh. During production, the aircraft were outfitted with a modified AM-3 engine - the PD-3MT. While the bombers were already operational, the AM-3 and PD-3M engines were replaced by PD-3M-500 engines with improved characteristics. When production of the TU-16 finally stopped in 1963, a total of 1509 aircraft had been built. Deployment of the first TU-16 bombers started in 1954. They replaced the TU-4, operating in theaters close to Soviet territory.  

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Badger-A - Tu-16 -- The initial production version was lighter than the first prototype, and largely met the original performance requirement. Badger-A - Tu-16A -- Primarily employed as a medium bomber, the TU-16A carried nuclear bombs - the A suffix stood for Atomic. It had a re-configurable thermostatically controlled heated bomb bay compatible with nuclear weapons, and a special skin for protection against nuclear thermal effects. Externally similar to the basic Tu-16, it featured more powerful RD-3M-200 engines, and an improved self-defense gun fire control system. This was the primary production version, with over 700 built, many of which were subsequently converted to other versions. Badger-A - Tu-16E -- To increase range, the TU-16 subsequently received an air refueling system. Some TU-16 were converted into tanker aircraft, which were first tested in 1955 and received the designation TU-16E [some Western sources suggest the designation was Tu-16Z]. However, they could still be used as bombers. This initial inflight refuelling tanker version used a novel "wingtip-towingtip" method, with a hose trailed from the right wingtip and snagged by grapnel trailed by receiver, then winched into fitting in receiver's port wingtip. It also had provision for additional transfer fuel in removeable tanks in bomb bay. Badger-A - Tu-16M -- The Tu-16M AV-MF maritime strike version was similar to the Tu-16A with a few minor differences. Badger-A - Tu-16N -- A secondary mission for Badger A is as a tanker. From 1963 on the TU-16 was converted into TU-16N tanker aircraft. This tanker version featured a 'Probe and drogue' system with a Yakovlev-built centerline fueling unit in the bomb bay and ARK-5 beacon. It was mainly used to support probe-equipped Tu-22 and Tu-22M Blinder bomber regiments. Badger-A - Tu-16T -- In the middle of the 1950s series production of the TU16T started. It was equipped with an air-to-surface missile for anti-shipping purposes, with provision for mines, depth charges or for four RAT-52 or TAN-53 torpedos. This torpedo bomber version was built in limited numbers, and after 1965 all TU-16T aircraft were converted into the TU-16S. Badger-A - Tu-16S -- The Tu-16S search and rescue model, a 1965 conversion of all the TU-16T aircraft, featured additional fuel and extra radios and carried a radio-controlled lifeboat in the bomb compartment. Badger-A - Tu-16Ye -- In the middle of the 1950s, the TU-16N and the TY16Ye were created for electronic warfare. The Yolka ECM system featured a row

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of three steerable antennas under the bomb bay and a bulk chaff-cutter/dispenser. This aircraft is designated Badger-K when fitted with two radomes rather than three. A few Tu-16As were rebuilt as Elint/EW platforms, though most Tu-16Ye were produced by conversion of redundant Tu-16K-10 missile Badger-D carriers. Badger-B - Tu-16KS -- The Badger B is equipped with two Kennel air-to-surface missiles suspended beneath the wings. The TU-16KS began initial tests in August 1954. It carried two KS-1 Kometa air-to-surface missiles with a range of 90 km, and had an operational range of 1800 km. The Kobalt-N guidance transmitter was installed, though the glazed 'bomber' nose was retained. The aircraft subsequently served in the Soviet Naval Air Force [AV-MF]. Badger-C - Tu-16K-10 -- In 1955 work began on using the Tu-16 as the carrier for the K-10S (AS-2 Kipper) cruise missile for the Soviet Naval Air Force for use in an anti-shipping role. The missile's guidance system was added as an onboard system, with the missile mounted semi-submerged under the fuselage on the centerline in the bomb bay area. The glazed nose was replaced by broad flat radome housing antenna for the YeN targeting radar. A missile top-off fuel tank was housed in the bomb bay, along with a small pressure cabin for the YeN radar operator. The TU-16K-10 prototype was finished in 1958 and series production started in 1959. Deployment into the Soviet Naval Air Force began in October 1961. A total of about 220 were built, many of which were subsequently converted to Elint/EW platforms. Badger-C (Mod) - Tu-16K-10-26 -- Small numbers of Tu-16K-10s were later modified to carry KSR-2, KSR-5S and later K-26 missiles underwing. Badger-D - Tu-16Ye -- Badger D is a modified Badger C reequipped to perform an ELINT reconnaissance mission. This EW conversion of Tu-16K-10 and K-1026 is generally similar to Tu-16A and Tu-16KS-based EW conversions (Tu-16Ye 'Badger-A' and 'Badger-B'), though retaining the distinctive broad flat nose radome. Badger-E - Tu-16R -- The TU-16R reconnaissance aircraft represented another modification of the TU-16 Badger which was tested from 1955 on. The Badger E is a modified Badger A reequipped to perform photographic reconnaissance, with a camera pack in former bomb bay and the pilot's forward firing gun usually removed. Badger-E - Tu-16RM -- The Tu-16RM is a similar maritime reconnaissance version for the Soviet Naval Air Force [AV-MF]. Badger-E - Tu-16KRM -- Small numbers of Tu-16RMs were modified with underwing launch rails for rocket-powered target drones. Badger-F - Tu-16RM-2 -- Badger F is a photographic reconnaissance variant of the Badger E Tu-16Rs and RMs with the addition of ELINT pods beneath the wings or fuselage. Badger-G - Tu-16K-11-16 -- The Badger G has the concurrent capability of carrying two Kelt AS-5 (125 nm) or two AS-6 (300 nm) air-to-surface missiles suspended beneath the wings and dropping bombs from an internal bomb bay. The new missile system K-11-16 with KSR-2 (AS-5B) and KSR-11 (AS-5B) missiles and the "Rubin-1" radar system was developed in 1962 based on a modification of equipment of the MIG-15. The Badger G/Kelt weapon system

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was developed as a stand-off weapon for the LRA and for an anti-shipping role for the SNAF. It probably has an anti-radiation role also. The AS-6 would have similar roles. It is equipped for aerial refueling. A number of Tu-16As and Tu16KSs were re-fitted with Rubin radar undernose and with provision for K-11 or K-16 missiles. The TU-16K-11-16 aircraft that were converted from TU-16, TU16A and TU-16KS aircraft could carry either two KSR-2 or KSR-11 missile beneath the wings. They served in the Soviet Naval Air Force. Badger-G (Mod) Tu-16K-26 -- Development of the K-26 missile system started in 1962, using the KSR-5 (AS-6) air-to-surface anti-ship missiles. They were deployed on TU-16K-26 aircraft that entered service in the second half of the 1960s. The Tu-16K-26 aircraft was modified to launch K-26 missiles, with launch attitude indicator on the nose glazing. The characteristics of the K-11-16 and K26 weapon systems allowed the aircraft to retain their original bomber capabilities. Badger-G (Mod) Tu-16K-10-26 -- During development of the TU-16K-26, the K-10 weapon system was upgraded and replaced by the K-10S system that had two KRS-5 or KSR-2 missiles. The retrofitted aircraft received the designation TU-16K-10-26. After the K-10S system missiles were phased out, these aircraft carried only KSR-5 missiles. Badger-H - Tu-16PP or Tu-16P Elka -- The Badger H is believed to be an ECM support aircraft with a primary mission of sowing chaff corridors to protect follow-on weapons-carrying aircraft. It also has a limited capability to provide active ECM against search and acquisition radars. This stand-off jammer version was produced by conversion of Tu-16A or Tu-16KS, with underfuselage radomes at each end of the bomb bay, and with a new bulk chaff-cutter/dispenser serving three chutes in the former bomb bay doors. Badger-J - Tu-16P Buket -- The Badger J active jamming platform is estimated to carry a multichannel click jammer to perform both stand-off and escort-active ECM. It features a ventral canoe fairing and flat plate antennas forming wingtip extensions. Badger-K - Tu-16Ye -- Badger K probably supplements Badger F and is probably an automatic system designed for precision ELINT collection in a dense signal environment. This EW conversion of Tu-16KS is generally similar to Tu16Ye Badger-B, though with two rather than three underfuselage radomes mounted on the area of the former bomb bay [rather than at each end as on Badger-F]. Badger-L - Tu-16P and Tu-16PP -- The Badger-L is an advanced ELINT platform with a self-protection active jammer and an associated thimble nose radome, along with a distinctive extended ECM tailcone.

The TU-16 remained in Soviet and later Russian service until 1993. They were used during the war in Afghanistan. The Badger is used by Egypt, Iraq, the People’s Republic of China (H-6), and Ukraine. In 1958, delivery of TU-16 bombers to China began, where series production received the designation H-6. In the summer of 1961, twenty TU-16KS were sold to Indonesia. In the 1960s, TU-16 bombers were delivered to Egypt which also

received TU-16KS aircraft in 1967 and Tu-16K-11-16 in 1973. Iraq also received TU16K-11-16 bombers in the 1960s.

Specifications Design Bureau

OKB-156 Tupolev

Manufacturer

Plant Nr.22 Kazan Plant Nr. 1 Kuinyshevs Plant Nr. 64 Voronezh

Power Plant

2 AM-3A Turbojet engines 2 PD-3M Turbojet engines 2 PD-3M-500 Turbojet engines

Thrust

8,750 kg each 9,500 kg each 9,500 kg each

Length

34.8

Height

10.36

Wingspan

33m

Wing surface

164.65 sqm

Speed

TU-16 - 900-950km/h (cruise) / 1050km/h (maximum) TU-16K - 750-850km/h

Ceiling

12,800m

Weight (empty)

37,200kg

Fuel weight

36,000kg

Maximum take-off weight

79,000kg

Normal load

3,000kg

Maximum load

9,000kg

Operational Range

5,800km (with a load of 3.000kg) 4,850km (with 2 missiles underneath the wings)

Range

7,200 km

Operational Fuel Unrefueled Aircraft Payload Capacity Combat Model Wt. (lb) Empty (gal) Radius

Altitude Speed Over Cruise/ Remarks Target Combat

(lbs)

(ft)

(kn)

Badger 83,500 A

11,200

1,450

10-30,000 40,400

445/500 bomber

Badger 90,300 B

9,300

1,000

12,000

15,000

445/480 Kennel ASM

Badger 86,600 C

10,300

1,350

9,100

39,400

445/480 Kipper ASM

Badger 88,840 D

11,370

n.a.

n.a.

n.a.

n.a.

ELINT Recce

Badger 85,000 E

11,570

n.a.

n.a.

n.a.

n.a.

Photo Recce

Badger 87,000 F

11,570

n.a.

n.a.

n.a.

n.a.

Photo/ELINT

Badger 86,000 G

9,460

1,100

17,620

38,100

445/495 ASM

Badger 83,500 H

11,200

n.a.

n.a.

n.a.

n.a.

ECM/Chaff

Badger 83,500 J

11,200

n.a.

n.a.

n.a.

n.a.

ECM/Jammer

Badger 83,500 K

11,200

n.a.

n.a.

n.a.

n.a.

ELINT

Historical Review - Western Estimates Estimated start of flight testing

1953

First discovery Badger A

1953

Badger B

July 1961

Badger C

July 1961

Badger D

September 1964

Badger E

January 1963

Badger F

1959

Badger G

July 14, 1966

Badger H

March 1965

Badger J

March 1965

Badger K

September 1968

Estimated start of series production

1953

Public display in significant numbers

May 1, 1954

Initial operational capability

1954

Significant operational capability

1955

c

Tu-95 BEAR (TUPOLEV) The Tu-95 BEAR was perhaps the most successful bomber produced by the Soviet aviation, enjoying long service in a variety of roles and configurations. It was the only bomber deployed by any country to use turbo-prop engines, which provided extraordinarily long endurance at speeds only slightly less than comparable turbojetpowered heavy bombers. Development of the TU-95 intercontinental bomber began in the early 1950s after series production of the medium-range TU-4 started.. Initially, several designs were considered, including a modification of the TU-4 and production of a new aircraft with piston engines. Prototypes of these aircraft were developed and tested from 1949 through 1951, it was concluded that bombers with piston engines could not provide adequate performance for the intercontinental attack mission. In March 1951 development of the T-4 intercontinental jet bomber began. However, KB Tupolev did not support the development of a bomber with turbojet engines, believing that the proposed AM-3 jet engines would not provide for the required range of more than 10,000 km. As an alternative, KB Tupolev proposed an aircraft with four turbo-prop engines that would provide a range of more than 13,000 km and speeds of more than 800 km/h at altitudes of 10,000 meters. The aircraft-design was designated as "95". The design of the wings drew heavily on the experience gathered by Tupolev and the Central Aerohydrodynamic Institute (TSAGI) during the development of the swept wing TU-16. The wings of the "95" were swept back at an angle of 35 degrees, allowing the placement of a large bomb bay behind of the torsion box of the wings' central unit at the aircraft's center of gravity. The Bear's wings are mid-mounted, swept-back, and tapered with blunt tips. Its engines consist of four turboprops with contrarotating propellers located on the wings. The engine nacelles extend well beyond the wings’ leading edges. The fuselage of the Bear is tubeshaped with a rounded nose that tapers to the rear. It also has a stepped cockpit and a tail gun compartment. The tail of the aircraft is a fin that is swept-back and tapered with a square tip. The greatest difficulties during the development were the engines. After studies on different engine combinations and versions, the final design of the aircraft incorporated four turbo-prop engines with a thrust of about 10,000-shp. In the late 1940s, the most powerful turbo-prop engine available was the BK-2 prototype which had significantly less thrust (4800-shp). In the early 1950s OKB-276 N.A. Kuznetsov developed the TV-2 engine and the TV-2F booster engine with a thrust of 6,250-shp. while work on the TV12 engine with sufficient thrust for the "95" aircraft continued. After consideration of Tupolev's proposals, on 11 July 1951 the government officially approved the development of the "95" aircraft: Two versions were built, one with eight TV-2F engines coupled through the reduction gearbox in four pusher-tractor tandem

pairs, and a second version with four TV-12 engines. N.I. Bazenkov became the chief designer of all subsequent TU-95 versions. When he died in 1975, N.V. Kursanov took over as chief designer, and from the end of the 1980s, D.A. Antonov became head of the program. In 1952, the first prototype "95/1", equipped with 8 2TV-2F engines, was built at Plant Nr. 156. The reduction gearbox and the four-blade contra-rotating propellers were developed by OKB-120 headed by K.N. Zhdanov. Each pair generated a thrust of 12,000shp. The first flight of the "95/1" airplane took place on 12 November 1952, but on 11 May 1953 during its' 17th flight the plane crashed and burned due to an engine fire. The second prototype ("95/2"), equipped with TV-12 engines, was completed in June 1954 with a first flight on 16 February 1955. During tests, while carrying a load of 5000 kg, it reached a range of about 15,000 km, a speed of 993 km/h and a ceiling of 11,300 m. Series production of the aircraft -- now designated as TU-95 -- started in January 1956 at Plant Nr. 18 in Kuibyshev, while production tests were still underway.

VARIANTS With the exception of Bear A, all models are equipped with a nose probe for aerial refueling. 

BEAR A - TU-95 / TU-95M -- The Bear A is a long-range strategic bomber that is capable of high-altitude precision bombing. The TU-95 and TU-95M bombers were designed to carry 9,000 kg of bombs at their maximum design range, which could be further increased by reducing the aircraft's range. They carried six radarcontrolled turret-mounted AM-23 guns for self-defense. The first two fully equipped Tu-95 aircraft left the plant in August 1955 and began flight tests in October 1955. Carrying a load of 5,000 kg, it reached a maximum speed of 850 km/h and a service ceiling of 10,200 m with a maximum range of 12,100 km. The bomb bay was 14.2 m (46.6 ft) long. The subsequent aircraft, designated as TU95M, had more powerful and more fuel-efficient NK-12M engines that allowed increased take-off weight. During tests in September and October 1957, it reached a maximum speed of 905 km/h, a ceiling of 12,150 m and a range of 13,200 km. Despite falling short of range and speed requirements, deployment started in October 1957. During work on these aircraft, development of a bomber with improved abilities to counter air defenses continued. In 1952 the government ordered a high-altitude strategic bomber with a ceiling of 17,000 m. A prototype equipped with NK-12M engines was used in tests, but development was halted because the increased altitude did not increase the survivability of the bomber. Most 'Bear-As' were subsequently converted to the missile-carrying Bear-B configuration. About a dozen surviving 'Bear-As' were converted to Tu-95U configuration for training duties  BEAR - TU-95V -- The Tu-95V, built in 1956, was intended to carry large hydrogen bombs. As these bombs were not made operational in the end of the 1950s, this aircraft was used for training purposes. Nevertheless, in 1961, overhaul of a TU-95V aircraft took place at the plant Nr. 18 in Kuibyshev. The aircraft carried the hydrogen bomb that was tested on 31 October 1961, which

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weighed about 27,500 kg and had a yield of 58 megatons. This version of the BEAR A was apparently not recognized as a distinct variant by Western intelligence, and did not receive a separate designation. BEAR - TU-95N -- In 1958 a single aircraft was converted into the TU-95N used to carry the "PS" attack aircraft "RS" developed by OKB-256 P.V. Tsibina, but this line of development proved unpromising and was soon discontinued. The fact of the existence of this project was apparently not detected at the time by Western intelligence, and this variant did not receive a separate designation in the West. BEAR B - TU-95K / TU-95KD -- The Bear B carried one Kangaroo (350 nm range) air-to-surface missile partially recessed within the aircraft fuselage. The most visible change from the BEAR A TU-95M is the addition of the broad, flatbottomed radome under the nose, which housed a 3.3-meter wide low I-band A336Z Crown Drum scanning antenna for the missile guidance radar. Development of the TU-25K-20 weapon system, consisting of the TU-95K and the supersonic Kk-20 (AS-3) air-to-surface missile, began in March 1955. The "K-20" nomenclature appears to encompass both the aircraft and the missile, and the "Tu95K-20" nomenclature used by some sources may be in error]. With a range of 350 km, sufficient to overcome air defenses, the air-to-surface missile was located under the fuselage. The first flight of the prototype was on 01 January 1956, and through development continued on the missile launch and guidance system, the aircraft's airframe, and the onboard electronics. Series production of the TU-95K began in the spring of 1958, with operational deployment beginning in September 1959. The additional fuel tanks and the missile of the Tu-95K resulted in an increase of weight and drag that reduced the range of the aircraft. This performance deficit had to be offset by a aerial refueling. Work on this "hosecone" system started in May 1960 and was completed in 1961. The bombers that were outfitted with this air refueling system received the designation Tu-95KD. Some 'Bear-Bs' were relegated to training duties. BEAR C - TU-95KM -- In the 1960s several TU-95K and TU-95KD bombers received a new radio engineering and navigation system, and their designation changed to TU-95KM [some Western sources claim that the Tu-95KM Bear-C was a new-build aircraft, rather than a conversion]. The Bear C is similar in appearance to the late-series Bear B Tu-95KDs, with the addition of two pairs of reconnaissance radomes located on opposite sides of the aft section of the fuselage. Many Tu-95KMs were upgraded to the 'Bear-G' configuration and none are believed to remain operational in the original configuration. BEAR D - TU-95RTs -- The Bear D is a variant of Bear A which can also perform ELINT reconnaissance. The TU-95RTS maritime reconnaissance aircraft was developed in the early 1960s, and conducted its' first flight test in September 1962, with series production beginning in 1963 [some Western sources suggest that the aircraft were converted from surplus Tu-95M 'Bear-As]. The TU-95RTS began flying with naval aviation in 1964 and was introduced into the operational inventory by spring of 1966. The Bear-D was first identified by Western intelligence in 1967. The new variant was distinguished by a new enlarged chin radome, and a much larger Big Bulge I-band search radar in place of the former weapons bay. This search radar provided mid-course missile guidance, acquiring

targets for ship-, submarine- and air-launched missiles. The Tu-95RTs, although built on the airframe of a heavy bomber, was designed and built as a maritime patrol airplane. The TU-95RTs maritime patrol airplanes have not been and are not heavy bombers, nor have they been equipped with air-to-surface weapons or undergone conversion. Tu-95RTs airplanes have external features distinguishing them from heavy bombers of the Tu-95 type: they have no bomb bays, no external carrier beams to suspend or carry aerial bombs or missiles, and no equipment necessary for control of such weapons. Other differences characteristic of these airplanes are the additional three-dimensional radomes of the surface situation surveillance equipment under the fuselage and on the sides of the airplane. As of mid-1991 the Soviet Union had 37 Tu-95RTs airplanes, which were based only at naval air bases. Under the START I Treaty, all Tu-95 variants should be either deployed heavy bombers, non-nuclear heavy bombers, test heavy bombers, training heavy bombers, or former heavy bombers. The START II Twelfth Agreed Statement, however, exempts the 37 existing TU-95RTs (Bear D) maritime patrol airplanes from being considered as former heavy bombers. The proposal complements and amplifies that Agreed Statement by providing information on the Tu-95RTs, as well as the opportunity to verify that information. The 31 July 1991 exchange of letters between Ambassadors Brooks and Nazarkin stipulated that the airplanes are for maritime operations, are not heavy bombers, and have not been equipped with air-to-surface weapons or undergone conversion; it also lists distinguishing features for these airplanes and stipulates that the Soviet Union has 37 such airplanes. The 37 airplanes were not to be based at air bases for heavy bombers or former heavy bombers, heavy bomber flight test centers, or training facilities for heavy bombers. They would not be considered to be former heavy bombers and thus would not be "accountable" under the Treaty limits for heavy bombers equipped for nonnuclear armaments, training heavy bombers, and former heavy bombers. In the event the Soviet Union continued to produce such airplanes, all such new airplanes would be treated as former heavy bombers under the Treaty and subject to inspection to confirm that they are not equipped for air-to-surface weapons. The Parties agreed that not later than 240 days after signature of the Treaty, the Soviet Union is (i) to provide photographs to aid in the identification of such airplanes, (ii) conduct an exhibition of one such airplane, under specified conditions, and (iii) exhibit, upon request of the United States, the other 36 such airplanes under specified conditions. About 15 were believed to remain in service with the AV-MF in 1994.  BEAR E - TU-95U -- The Bear E is a variant of Bear A modified to perform photoreconnaissance. According to Western sources about 12 were produced for Naval Aviation by conversion of surplous Tu-95Ms. The aircraft features a slightly bulged removeable reconnaissance pallet in the former bomb bay, with seven camera windows -- three side-by-side pairs of windows forward with a single window further aft to starboard. Under the START I agreement, the Parties agreed that all airplanes formerly known to the United States of America as Bear E and now known as Bear T, which are designated by the Union of Soviet Socialist Republics as Tu-95U, were to be considered to be training heavy

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bombers. Red bands are painted around the rear fuselage for verification purposes. BEAR F - TU-142 / TU-142M -- Bear F exists in two major versions with differing numbers of radomes, consisting of at least four distinct variants [up to at least the Bear-F Mod IV]. The mission of the Bear F is the detection and destruction of submarines. Development of the Tu-142 maritime reconnaissance aircraft began in the mid-1960s, soon after the initiation of the BEAR D Tu95RTS. Design changes include a new cockpit and slightly longer nose' along with a new undercarriage (with bulged undercarriage doors) and an extendedchord rudder. The Tu-142 lacks dorsal and ventral gun turrets. This upgraded version of the TU-95RTS, with more powerful NK-12MV engines, began flight tests in the summer of 1968 and was deployed with naval aviation in December 1972. According to Russian sources, series production took place at the plant Nr. 18 in Kuibyshev and from the mid-1970s at Plant Nr. 86 in Taganrog. Western sources report that the production line at Taganrog reopened in 1983 to build the Bear-F and Bear-H. Upgrading of the TU-142 in 1972 resulted in the TU-142M, used for anti-submarine warfare. The first flight of the TU-142M [Bear F Mod 2 ] was on 04 November 1975, and deployment to the Soviet Naval Aviation began in 1980. The Tu-142M2 [Bear-F Mod 3], which entered service around 1982, featured a new MAD in a spike-like tail fairing and a lengthened sonobuoy bay. The Tu-142M3 [Bear-F Mod 4] incorporated a new undernose sensor pacakge. First identified by Western intelligence in 1986, the Bear-F Mod 4 remained in low volume production at the end of the 1990s. The Tu-142 (Bear F) antisubmarine warfare patrol airplanes, although designated by the Soviet Union as a separate type of airplane from the Tu-95, have a design essentially identical to the design of the Tu-95 heavy bomber. Under the START I agreement, all airplanes designated by the Union of Soviet Socialist Republics as Tu-142, which are known to the United States of America as Bear F or Bear J, depending on how a particular airplane is equipped, were not considered to be former heavy bombers. BEAR F - TU-142LL -- At least one 'Bear-F' was converted to serve as an engine testbed , with the test engine mounted in a semi-retractable cradle under the center-section. BEAR - TU-95K5 -- In 1976-1977 work began on developing a new Bear modification, the TU-95K-5, that was supposed to carry two KSR-5 [AS-6 KINGFISH] missiles. However, all activities soon halted due to a decision to produce the TU-95K-22, and the development of the TU-95MS aircraft. The fact of the existence of this design project was not detected at the time by Western intelligence, and this variant did not receive a separate designation in the West, since it did not enter flight tests or production. BEAR G - TU-95K22 -- In the early 1970s work began on equipping older existing TU-95K and TU-95KD bombers with Kh-22 air-to-surface missiles and the guidance systems that were used on the Backfire bombers. These older BEAR aircraft configured to carry air-to-surface missiles (ASMs) were reconfigured to carry the new supersonic AS-4 missile in place of the subsonic AS-3. These bombers received the designation TU-95K-22 and carried either one Kh-22M

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missile under the fuselage or two Kh-22H missiles on pylons underneath the wings. The broad flat nose radome differs in detail from that of the Bear-B and Bear-C, and accommodates the antenna for the Down Beat guidance radar for the Kh-22. The comprehensive defensive avionics suite is evidenced by the numerous radomes and fairings on the fuselage, marking a fundamental shift in survivability ideology. The self-defence armament is correspondingly reduced compared to earlier models. An extended tailcone replaced the tail turret and the dorsal turret was removed entirely, leaving only a single ventral gun turret. First flight tests of the TU-95K-22 took place in October 1975 and by the end of the 1970s reequipment of the TU-95K started. After operation testing, the TU-95K-22 was introduced into the active inventory in 1982. Several of these reconfigurations (BEAR G) had been completed by 1985. By 1998 more than 45 of these reconfigured aircraft were operational. BEAR - TU-95M-55 -- In the middle of the 1970s work on the Kh-55 long rang air-to-surface missile started. Originally planned for deployment on the new TU160 supersonic bombers, studies were conducted to outfit the TU-95 with the Kh55. The tests of TU-95 bombers outfitted with Kh-55 missiles, designated Tu95M-55, started in 1978. After their completion, the project was rejected and development of a new Tu-95MS aircraft to carry the Kh-55 missiles was initiated. It is unclear whether the fact of the existence of this design project was detected at the time by Western intelligence, and in any event this variant did not receive a separate designation in the West. BEAR H - TU-95MS -- The Tu-95MS aircraft is based on the Tu-142 and thus differs in a number of details from the TU-95. The nose of the Tu-95MS is similar to that of the Bear-C and Bear-G, but with a deeper, shorter radome, cable ducts running back along both sides of the fuselage. It lacks the 178-cm forward fuselage plug of the maritime Tu-142, and retains the shorter fin and horizontal, undrooped refuelling probe of prevoius bomber variants. The rear gun turret is a new design, with a single twin-barrelled GSh-23L cannon in place of the pair of single-barrel NR-23s carried on earlier models. After carrying out successful tests, the first of which was in September 1979, series production started in 1981. With the reopening of the BEAR production line, the Soviets began producing a new, upgraded variant of the BEAR turboprop bomber, thereby increasing their longrange bomber force. This entirely new variant of the BEAR bomber - the BEAR H - became the launch platform for the long-range Kh-55 [AS-15] air-launched cruise missile. The initial version carried Kh-55 air-to-surface missiles located in the bomb bay on a catapult. This was the first new production of a strike version of the BEAR airframe since the 1960s. With the BEAR H in series production, the decline in the inventory of BEAR aircraft, characteristic of the late 1970s, was reversed. By 1988 BEAR H bombers were regularly observed simulating attacks against North America. BEAR H6 - TU-95MS6 -- The version designated as TU-95MS6 aircraft carried Kh-55 air-to-surface missiles located in the bomb bay on a rotary launcher. BEAR H16 - TU-95MS16 -- The TU-95MS16 carried six missiles inside the fuselage and 10 missiles underneath the wings. Three underwing pylons are fitted

under each inner wing panel, the outboard pair carrying three missiles and the other two single missiles.  BEAR J - TU-142MR -- The TU-142MR was a further modification of the Tu142M used for submarine communication relay, allowing national command authorities and strategic missile-carrying submarines to communicate. The underfuselage search radar has been removed, and the aircraft is equipped with an underfuselage winch pod for a several kilometer long trailing wire antenna. The Tu-142 (Bear J) maritime communications relay airplane, although designated by the Soviet Union as a separate type of airplane from the Tu-95, has a design essentially identical to the design of the Tu-95 heavy bomber. Under the START I agreement, all airplanes designated by the Union of Soviet Socialist Republics as Tu-142, which are known to the United States of America as Bear F or Bear J, depending on how a particular airplane is equipped, were not considered to be former heavy bombers.  BEAR T - TU-95U -- About a dozen surviving 'Bear-As' were converted to Tu95U configuration, with sealed bomb bays and a broad red band painted around the rear fuselage. Under the START I agreement, the Parties agreed that all airplanes formerly known to the United States of America as Bear E and now known as Bear T, which are designated by the Union of Soviet Socialist Republics as Tu-95U, were to be considered to be training heavy bombers. Most served with the Long-Range Aviation training center at Ryazan, and most were withdrawn from use during 1991 and 1992 Russia, Ukraine and India (Bear F) use the Bear. When the START-1 treaty was signed in 1991, 147 bombers and missile carriers still served in the Russian forces: 84 TU-MS and 63 TU-95K-22, TU-95K and TU-95M. An additional 11 TU-95U were used for training. After the dissolution of the Soviet Union, one unit of Bear aircraft remained in Ukraine, with twenty three TU-95MS, one TU-95K and one TU-95M aircraft. These aircraft were passed to Ukraine, and were subject to decommissioning under the provisions of the START-1 treaty. A total of 11 strategic bombers and 600 air-launched missiles exchanged by Ukraine to Russia in payment for the gas debt were transfered in midFebruary 2000. Two Tu-160 bombers flew from Priluki in the Ukrainian Chernigov region for the Russian air base in Engels. The missiles were sent to Russia by railroad. Three Tu-95MS bombers and six Tu-160 airplanes had already arrived at Engels since October 1999 in fulfilment of the intergovernmental agreements. Before being moved to Russia, 19 Tu-160 airplanes were stationed at the Priluki airfield and 21 Tu-95MS were located in Uzin. At the time of the breakup of the Soviet Union, thirteen TU-95MS-16 and twenty seven TU- 95MS-6 were based in Kazakhstan. Subsequently, all Bear aircraft located in Kazakhstan were transferred to Russia.

Russian Tu-95 and TU-95MS aircraft are now deployed at two air bases A total of nineteen TU-95MS16 and two TU-MS6, operating in the 121st heavy bomber air regiment, which forms part of the 22nd Air Division that is headquarteed in Engels Air Base in the Moscow region. At the Ukrainka airbase (73th Heavy Bomber Air Division) at Svobodny, there are 16 TU-95MS16 and 26 TU-95MS6 bombers that were redeployed from the Dolon airbase at Semipalatinsk in Kazakhstan. The TU-95K-22 bombers are subject to decommisioning. In early 1997 five TU-95K-22 were decommissioned and reequipped in Zngyelse, and five at the Ryazan training center. Eight TU-95 are located at the flight-test institute in at Zhukovskiy [Ramenskoye], and one TU-95K aircraft serves as a static display in Ryazan. The TU-95MS, constructed in in the middle and early 1990s, will be operational until 2010 and 2015. Russia is currently working on a new air-to-surface missile to replace the existing Kh-55. In late June 1999 two TU-95 Bear bombers flew within striking distance of the United States as part of Moscow's largest military exercises since the end of the Cold War. The bombers were intercepted by four US F-15 fighters and a P-3 patrol plane near Iceland and escorted in a clockwise flight around the island. The Bears, and two Blackjacks, were from the Donbass Red Banner 22nd heavy bomber division based at Engels Air Base east of Moscow. They initially flew acoss the central Norwegian Sea. When they got about halfway across, the Blackjacks split off from the Bears and flew along the Norwegian coastline. On 16 September 1999 a pair of Russian Tu-95 Bear bombers were detected by the US Air Force headed toward the Alaska coast. U.S. fighter jets were sent to intercept the aircraft which had been caught on radar. Air Force officials said both bombers turned before crossing into US airspace and about 90 miles from the approaching fighters. The Soviet Union regularly tested U.S. air defenses by flying toward Alaska during the Cold War, but this was the first time the Air Force had documented it happening since March 1993. Ten Tu-142 entered Indian service in April 1988 for long-range surface surveillance and anti-submarine warfare Negotiations are currently going on with Russia to procure 6 to 8 more Tu-142 aircraft. The aircraft will be probably from refurbished ex-VVS storage stocks. India is making substantial purchases of the Novator 3M-54 Alfa missile to equip Kilo class submarines and its new frigates. It is believed that an air-launched variant will be purchased to arm the Tu-142s currently in service and the six to eight additional aircraft being sought by the Navy. If an air-launched version of the Alfa is procured, it is anticipated that India's Tu-22M3s will eventually be equipped to fire them.

Specifications TU-95M

TU-95K

TU-95KM TU-95RTs TU-95U TU-142

TU-95K22 TU-95MS

TU-142MR

Bear A

Bear B

Bear C

Bear G

Bear J

Bear D

Bear E

Bear F

Bear H

sson

Kangaroo Kangaroo ASM plus ELINT ASM recce recce carrier radomes

Bomber

sign reau

Photo Recce

Kh-22 ASM

Kh-55 [AS-15] ALCM

Plant Nr. 18 Kuibyshev

Plant Nr. 18 Kuibyshev Plant Nr. 86 in Taganrog

velopment gan

6/11/1951

st Flight

11/12/1952 1/1/1956

September 1962

te ployed

August 1957

Spring 1966

ew

8 men

Autum 1959

December 1972

October 1975

September 1979

1982

1981 7 men

wer Plant

Four turboprop NK-12

ximum gine Power 12,500 SHP)

NK-12M

NK-12MV

12,500

14,800

NK-12MP 15000

ngth [m]

47

49.50

49.6

ight [m]

12.5

12.12

13.4

ingspan [m] 50.05 ing surface 2]

submarine communicatio relay

OKB-156 Tupolev

nufacturer

wer Plant

Antisubmarine

51.10

283.7

288.9

eed ximum

925

eed Cruise /hr)

435

425

425

440

440

440

eed mbat /hr)

470

470

475

300

300

490

11750

11500

14000

450

450

iling eters]

12000

titude Over

12000

830 550

rget eters) nge (with rmal load) ]

13200

13200

10300

nge (with ximum d)

mbat dius (km)

eight pty)

6500

7600

6750

6400

6750

70455

70910

72275

71360

3650 [Unrefueled, 7125 3-hr loiter, 15,000 ft. cruise] 71825

94.400

72500

el weight el Capacity l) ximum e-off ight [kg] keoff Gross eight (kg) rmal rmal load ) ximum d (kg) mament mary

84.000kg 29,100

26,900

26,400

29,100

29,100

30,100

182000

185000

165900

165900

165900

9000

11400

11400

162,275 162,275

162,275

8500

20000 Bomb tonnage up to 12.000kg

One H-20 missile

One or two H-22 missiles none

mament -

10500

Six Am-23

Four AM-23 (23mm)

none

two AM-23

6 Kh-55 missiles (TU95MS6) 16 Kh- none 55 Missiles (TU95MS-16) Two GSH-

condary

stems

(23mm) guns in 2 installations guns in 3 installations

Crown Drum missile guidance radar

(23mm) guns in one installation

Big Bulge Iband search radar

23 (23mm) guns in one installation Down Beat missile guidance radar

Historical Review - Western Estimates Estimated start of flight testing

1953

First discovery Bear A

1955

Bear B

July 9, 1961

Bear C

February 1962

Bear D

March 1965

Bear E

April 1965

Bear F

April 1972

Estimated start of series production

1954

First public display in practice for May Day flyby

April 21, 1955

Public display of three (some observers say nine) aircraft

May 1, 1955

Initial operational capability

1956

Significant operational capability

1959

Bear H16 Tu-95MS16 with AS-15 Mod A RKV-500A ALCM

Bear H6 Tu-95MS6 with AS-15 Mod A RKV-500A ALCM

Bear G Tu-95K22

Bear B Tu-95K

Bear T Tu-95U Training Heavy Bomber

Bear A

Bear D

Bear E

Bear F

Bear G

Bear H

Molot M-4 / Mya-4 / 3M Myasishchev 'Bison' The Molot (Hammer) was designed as a strategic bomber, but excessive fuel consumption of its engines and other design shortcomings limited its range to 8,000 km, which was insufficient for striking North American targets and returning to base. Consequently, along with the development of an improved version of the bomber with more fuel-efficient bypass engines and a new wing, a program was also initiated to develop a specialized aircraft for aerial refueling. To facilitate operational support and formation flight in the refueling process the bomber and the tanker aircraft were intended to have identical design and performance characteristics. Development of an intercontinental bomber with a strike capability at US-territory began in the early 1950s. The governmental order of 24 March 1951 provided for the establishment of a new design bureau headed by V.M. Myasishchev. The design bureau was in charge of organizing and manufacturing the development of the bomber which would have a range of 11000-12000 km, a maximum speed of 900km/h and could carry a payload of 5000 kg. The Bison was a Four-engined, swept-wing jet bomber with engines were buried in the wing roots. An unusual feature was the tandem landing gear, with small stabilising wheels at the tips of the drooping wings, and a nosewheel leg extended at take-off to achieve the correct angle of incidence. Due to the fact that the high-power BD-5 engines for the aircraft were still in the development stage, the aircraft used four AM-3A turbojet engines developed by OKB A.A. Mikulina. The first prototype was finished in December 1952 and carried out its' first flight on 20 January 1953. It reached a speed of 947 km/h and a ceiling of 12500 m. Although the bomber had a range of only 8500 km, which did not allow strikes at US territory, series production of the M-4 bomber began in 1955 at the plant Nr. 23 in Moscow. In July 1955, deployment of the first ten bombers started. 

Bison A - M-4/2M -- The Bison A was the original version produced. It is characterized by a greenhouse nose and a nose refueling probe. It can be used in a free-fall strategic bombing role, but it is used primarily as a tanker for other Bison and Bear aircraft requiring in-flight refueling. Between 1956 and 1957, the M-4 was equipped with more powerful and low-consumption PD-3M and PD-3M500A engines to increase range. And a prototype of the M-4, the M-4A, was equipped with an air refueling system and carried out its' first flight in 1956. Soon after series production started, studies were conducted on equipping the M-4 with the Kh-20 air-to-surface missile to strike at targets outside of the bomber's and to overcome air defenses. However, the landing gear did not allow placement of the missile under the fuselage and accommodation of the missile above the fuselage was rejected. In order to increase the range of the M-4 bomber, it was subsequently outfitted with new more powerful VD-7 engines. This new bomber had improved flight characteristics and a bigger propellant capacity relative to the

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M-4, with the maximum range increased up to 11850 km. An air refueling system increasing range up to 15400 km, which made these bombers the first strategic bomber capable of delivering its' payload into deep enemy territory and returning. The first flight of this bomber designated as 3M bomber took place in March 1956. At the end of 1956 series production of the 3M aircraft started at plant Nr.23, and deployment started in 1958. Bison B - 3M/M-6 -- The modified 3M (M-6) bomber was created in 1955. The Bison B has the same basic airframe configuration as Bison A, but it has a slightly larger wing, a longer nose, increased fuel load, higher thrust an improved bomb/nav system. Bison B is fitted with a nose refueling probe. Its primary mission is free-fall strategic bombing, but it can conduct alternate missions as a tanker when a removable bomb-bay refueling package is installed. Bison B - 3MS/M-6 -- The reliability of the VD-7 engines caused several problems and as a result, between 1958 and 1960 the bomber was outfitted with new RD-3M-500A engines. This bomber version is designated as 3MS. The range of the bombers without additional fuel tanks decreased to 9400 km. Bison B - 3MS/M-6 -- The associated 3MS2 tanker aircraft included refueling equipment in the bomb bay. The tanker variant used the "drogue and probe" aerial refueling technique in which the aircraft being refueled inserts a probe into a drogue at the end of a flexible hose extended from the tanker. This technique was also adopted by the U.S. Navy and the air forces of Great Britain, France, Italy, China and other countries. In unique contrast, the US Air Force adopted a refueling technique in which a telescoping boom is lowered from the tail portion of the tanker and enters a special socket on the aircraft being refueled). Bison C - 3MD/M-6 / 3MN -- In 1960 the 3MD bomber was developed, characterized by a slightly larger wing, a more pointed nose, a shorter and relocated nose refueling probe, and a larger tail radome. The Bison C has the same operational performance. Its primary mission is free-fall strategic bombing, but it can conduct alternate missions as a tanker when a removable bomb-bay refueling package is installed. The 1960 modification of the VD-7 engine - the VD-7B - provided better overall performance though smaller thrust was developed. The bombers outfitted with these engines received the designation 3MN. Their range was increased by 15 percent though they had a lower speed and a reduced ceiling. Bison C - 3MN-2 -- Several 3M bombers were converted into M-4-2 tanker aircraft, and during the development of the 3MS bomber the 3MS-2 tanker aircraft was developed in parallel. The tanker aircraft that was based on the 3MN received the designation 3MN-2. The 3MS-2 tanker aircraft air regiment was in operational service until 1994. Project 28 -- To overcome air defenses, a high-altitude version of the M-4 (project 28) was studied but not developed prior to the in 1960 to shut down the Myasishchev OKB. When OKB-23 was shut down in 1960, all activities to upgrade the Bison bombers ended. In the mid 1970s a Bison was experimentally equipped with two Kh-22 two air-to-surface missiles but this version was not deployed.



3M-T / BM-T "Atlant" -- In the late 1970s a single 3M bomber was converted to transport outsized components for the Energiya-Buran space launch system from the manufacturing facility to the Baikonur launch site. The cargo, including propellant tanks and the Buran orbiter itself, were placed on external mounting points located above the fuselage. This particular aircraft had a strengthened fuselage, a longer two-fin tail and a new flight control system. The original designation of the aircraft was 3M-T but was subsequently changed to BM-T "Atlant". The first flight took place on April 29, 1981 and the first flight with freight in January, 1982. The plane carried out a total of 150 flights.

In 1963, production of the Bison bombers stopped. A total of 93 aircraft, including ten M-4 and nine 3MD13 were built. The 3M bombers were in service with the Air Forces until the end of the 1980s, and were removed in accordance with the START-1 treaty on offensive strategic force reductions. The 3MS2 tankers remained in service through 1994. The three airplanes that had been converted to transport oversized cargo are used for purposes unrelated to the START I Treaty; and are not reconnaissance airplanes, tanker airplanes, or jamming airplanes, and thus do not meet the definition of the term "former heavy bomber" provided for in the Definitions Annex to the Treaty. These airplanes are not included within the Treaty totals, though all other airplanes of the Bison type were considered to be former heavy bombers.

Specifications Soviet Designation

M-4/2M

3M/M-6

3MS/M-6

3MD/M-6

US-Designation Bison A

Bison B

Bison B

Bison C

Remarks

Basic Aircraft

Slightly lager and improved

Design Bureau

Myasishchev

Manufacturer

Plant Nr. 23 Moscow

Development began

3/24/1951

First Flight

1/20/1953

Series production

1954-1963

Date deployed

1956

1958

Crew

8 men

7 men

Power Plant

Four AM-3, or

Four VD-7

Slightly changed nose and tail radome

3/27/1956

Four RD-3M-

Four VD-7B

Four RD-3M500, or Four RD-3M500A

500A

Thrust

8,750kg 9,500kg 10,500kg each

11,000kg each

Length

47.67m

51.7m

Height

11.5m

Wingspan

50.53m

53.14m

Wing surface

326.35sqm

351.7sqm

10,500kg each

9,500 kg each

Speed Cruise [km/h]

800

800

800

800

Speed Maximum [km/h]

930

940

925

925

Ceiling

12,500m

Altitude Over Target (m) Weight (empty) [kg] Operational Wt. Empty (kg) Fuel Capacity (gal)

12800

12725

79700

74430

69500

71800

29,500

12725

71800

34,000

34,000

Fuel weight Maximum Takeoff Gross Weight [kg]

165900

181800

Normal load

5,000kg

5,000kg

Maximum load

18,000kg

24,000kg

Operational Range

8,100km

Operational Range with

8,100km

181800 5,000kg

5,000kg

11,850km

9,440km

10,950km

15,400km

12,400km

13,600km

refuelling Unrefueled Combat Radius (kmi)

4500

5000

5000

Maximum Range Armament:

18.000kg of free Free falling falling bombs bombs with a caliber of up to 9.000kg when carrying a load of 24.000kg, two nuclear bombs with ha weight of 2.000kg or one 4.000kg bomb

Historical Review - Western Estimates Bison A Estimated start of flight testing First discovery

Bison B

Bison C

1953 30 July 1953

1956

1960

Estimated start of series production

1953

1956

1960

Initial operational capability

1955

1958

1960

First public display (single aircraft}

01 May 1954

Public display of 13 aircraft

01 May 1955

End production

1961

M-50 / M-52, Myasishchev 'Bounder' OKB Myasishchyev began working on the supersonic intercontinental bomber M-50 in 1956. The aircraft was intended to be equipped with and the supersonic long-range M-61 cruise missile, also developed by OKB Myasishchyev. The bomber had a strategic strike capability due to its range of 10,000 km plus the 1000 km range of the missile. The M-50 had forward trailing triangular wings, a wing span of 35.1 meters and a length of 57.5 meters. Powered by four "16-17" engines developed by P.F. Zubets, two engine pods were mounted outboard on the wings and two less powerful engines at the tip of the wings. The prototype was constructed in 1959 and made the first flight on 27 October 1959. As engines the which were supposed to equip the airplane were at that time not yet available, on the prototype version two VD-7 engines and two VD-7g were used. In this configuration the demonstrated a speed of Mach 0.99. The second M-50, designated the M-52, carried the Zubets engines around which the aircraft had been designed. The engine installation was modified, and a second tailplane was added to the top of the fin. In December 1960, N. S. Khruschev, First Secretary of the Central Committee of the Communist Party of the Soviet Union (CPSU) made a speech at the Supreme Soviet session in which he proclaimed the inexpedience of the further development of military aircraft. The Soviet leader, fascinated by the triumph of Russian space technology and exploration, directed that all the tasks formerly executed by the combat aircraft be performed by guided missiles of various types. The Council of Ministers and the CPSU Central Committee issued a joint decree terminating work on new aircraft. The first victims of the decree were the Lavochkin and Myasischev aircraft design bureaus. They had to fully reorganize their work. V. Myasischev was appointed director of TsAGI. He was very disappointed at the fact that only a few of his M-50 and M-52 long-range supersonic bombers were produced. In 1960 development of the M-50 bomber was halted when OKB Myasishchyev was dis-established. Surprisingly little is known about the Bounder. One writer commented that it was "an outstanding failure which revealed an embarassing lack of understanding of the problems of high-speed flight."

Specifications Primary Function:

Heavy bomber

Contractor: Power Plant: Thrust: Length: Height:

4*28660lb Soloviev D-15 or 4*Zubetc ?? [M-52]

Wingspan: Speed: Ceiling: Weight: Maximum Takeoff Weight: Range: Armament: Crew: Unit Cost: Date Deployed: Inventory:

M1.4

S-100 Work on a new large medium-range bomber began in the late 1950s, in response to the disappointing results obtained with the TU-22 BLINDER, which was intended to replace the TU-16 [which had not met Air Force requirements]. In 1961 the operational and technical requirements for the new airplane were approved, specifying a supersonic missile-carrier with a speed of up to 3,000 km/h [since the overseas XB-70 could fly at a speed of 3,000 km/h] and an operational range of 2000 km, capable of hitting enemy aircraft carrier battle groups out in the ocean. The design bureaus A.N. Tupolev, A.S. Yakovlev and P.O.Sukhoi competed for the project, and the results were summed up at the scientific and technical council held in July 1962. The Tupolev design bureau submitted the "aircraft 135" project, whose take-off weight equalled 190 tons. The design failed to match its cruising speed to that of the required one, i.e. 2,500 km/h instead of 3,000 km/h. Yakovlev proposed the Yak-35 aircraft, which resembled the American Hustler, with a take-off weight of 90 tons and a cruise speed of 3,000 km/h. The T-4/S100 design submitted by KB Sukhoi was selected, with the support of the military and the State Committee Scientific and Technical Council. The initial design developed in 1964 called for a tailless delta-wing aircraft with four turbojet engines placed in a single "gondola" under the fuselage. The wing had a break in the leading edge, and a small forward stabilizer was included. The plane was to be equipped with three controlled H-45 solid-fuel missiles, located under the fuselage. KB Rybinsk developed the RD-36-41 engines under the direction of P.A. Kolesov. Initially KB Sukhoi was in charge of the project, but ultimately KB Raduga took over the task. During the design process, the arrangement of the aircraft engines was modified and the number of missiles was reduced to two. Construction made extensive use of titanium and steel alloys, and the T-4 used an advanced electrohydraulic, quadruple redundancy flyby-wire system. It was fitted with a 'droop snoot' that offered good visibility in the landing configuration, but when the nose of the aircraft was up and locked, the pilots had no forward visibility and all flying was on instruments. The final design was 44.5m long, had a wing span of 22m, a wing surface of 295.7 square meters and a lift-off weight of 114 tons. The calculated flight-characteristics indicated that the bomber would have a range of 6000 km, a maximum speed of 3200 km/hr at an altitude of 20,000-24,000 meters and an absolute ceiling of 25,000-30,000 meters. In December 1966, the Sukhoi design bureau presented the Air Force with the mock-up of the T-4 strike/reconnaissance aircraft. In 1967, the Soviet government issued a decree ordering an experimental batch of seven T-4 aircraft to be built, of which one should be used for static research and the rest to be flight-tested. A mock-up airplane was built in 1968, and construction of the first prototype began in 1969 at the Series Production Plant 82 in Tushino (Moscow). The first flight of the prototype T-4 took place on 22 August 1972 and subsequently the plane made 10 flights which were completed in 1974. During these flight trials the plane reached an altitude of 12,100 meters high and a speed of Mach

1.28. It is believed that the 'aircraft 101' that set a Mach 1.89 record over 2,000 km closed circuit was a T-4. Soon after testing began, preparation for construction of the first pilot batch of planes was begun. In 1974, work on the T-4 bomber was cancelled, given the beginning of serial production of the more conventionally designed TU-22M bomber. Although frequently compared to the American XB-70 intercontinental strategic bomber, which it superficially resembled, the T-4 medium bomber was a rather smaller aircraft intended as a medium-range theater system.

Between 1967-1969, KB Sukhoi also developed a design for the rather larger variablegeometry T-4M strategic bomber, derived from the basic T-4 design. On 10 January 1969 the Minister of Aviation Industry issued an order for research and development of a strategic supersonic bomber. A competition was initiated among the aircraft design bureaus of Tupolev, Myasishchev and Sukhoi. In 1969 and 1970 Sukhoi designed the T4MS bomber that also had variable wings and which was entered into this competition for building a supersonic strategic bomber. The work proceeded slowly, and the T-4MS design effort was ended in favor of work on the Su-27 and other high priority tactical

aircraft. In 1975 the contest between Myasishchev's M-18 design [resembling the B-1 in appearance] and Tupolev's Tu-160 was decided in favor of Tupolev.

Specifications T-4 (Project)

"101"

Powerplant

4x jet engines

4x RD36-41

Thrust lb (kg) each

33,060(15,000)

35,262(16,000)

Length ft(m)

-

145.96(44.5)

Wingspan ft(m)

-

72.16(22)

Height ft(m)

-

36.72(11.195)

Wing area ft^2 (m^2)

-

3,182.62(295.7)

Max takeoff weight lb(kg)

264,480 (120,000)

275,500 (125,000)

Takeoff gross weight lb(kg)

220,400-242,440 (100,000110,000)

251,256 (114,000)

Empty weight

55,600 kg

122,542 (55,600)

Fuel weight lb (kg)

-

125,628 (57,000)

Wing loading lb/ft^2 (kg/m^2)

-

78.54 (385)

Thrust-to-weight ratio

0.545-0.6

0.56

Cruise speed mph (km/h) 1,863(3,000)

1,987(3,200)

Range @ cruise speed (km)

4000 km

w/o drop tanks

3,726(6,000)

4,347(7,000)

w/drop tanks

4,347(7,000)

-

Service altitude mi (km)

13.66-14.90(22-24)

12.42-14.90(20-24)

Takeoff run ft(m)

5,576(1,700)

3,116-3,280(9501,000)

Landing run ft (m)

1500 m

2,624-3,116(800950)

Landing speed

-

-

T-60S In the mid-1990s, the first priority for the air forces was the Su-T-60S multirole bomber, which had been designed to replace the Tu-22M and the Su-24 . The Su-T-60S is a longrange supersonic tactical/operational nuclear-capable bomber with built-in stealth technology developed by the Sukhoy Design Bureau. Although its development was officially secret, the Su-T-60S was reported to be in the prototype stage and ready for flight testing in mid-1996. The T-60S project for a high-altitude, high-speed bomber was initiated by the Sukhoi bureau in 1984 and originally intended to enter service in 2003. Very little information is available concerning either the design or current status of this aircraft. The T-60S may consist of a blended-body fuselage and a swing-wing construction. The design may be capable of supercruise at Mach 2, with engines possibly equipped with two-dimensional thrust vectoring nozzles to solve the problem of insufficient area of horizontal control surfaces at high speeds encountered during the T-4MS development effort. The aircraft was intended to replace the current fleet of Tu-22M supersonic bombers, although this project has probably been deferred.

Conjectural Specifications Type

intermediate-range strike/interdiction aircraft

Powerplants

two 23,500 kg (51,800 lb) turbofans

Max speed

Mach 2.04

Cruising speed

Mach 2.02

Max altitude

20,000 m (65,500 ft)

Cruising altitude

15,000 m (49,000 ft)

Max range

6,000 km (3,250 nm)

Range with max load

2,200 km (1,200 nm)

Weight (empty)

32,000 kg (70,500 lb)

MTOW

85,000 kg (188,000 lb)

Max load

20,000 kg (44,000 lb)

Wing span (extended)

37 m (121 ft)

Wing span (swept)

24 m (79 ft)

Wing angle (extended) 70 deg Wing angle (swept)

30 deg

Length

38 m (125 ft)

Height

10 m (33 ft)

Armament

maximum of 20,000 kg (44,000 lb) of free fall nuclear and conventional bombs, guided munitions, up to 8 cruise missiles, including Kh-101, Kh-55MS (AS-15 Kent) , Kh-15P (AS-16 Kickback)

Tu-22 BLINDER (TUPOLEV) With performance roughly similar to that of the American B-58 Hustler, the BLINDER was capable of supersonic dash and cruises at high subsonic speeds, At least three major variants of the BLINDER entered operational service in the Soviet Air Forces — a freefall bomber, an ASM carrier, and a photo/electronic reconnaissance variant. Development of the supersonic TU-22 bomber began after the start of production of the TU-16. During preliminary studies, OKB Tupolev considered three versions: a supersonic attack bomber "98", a long range supersonic bomber "105" and an intercontinental supersonic bomber "108". The first two required swept-wings while the "108" bomber had triangular wings. In the end, the "105" design served as the basis for the TU-22 while the design of the "98" was applied to the long range fighterplane TU128. The "108" design was completely dropped. The original design drew heavily on the TU-16 and provided for four BD-5 or BD-7 turbojet engines. The angle of the sweptback wings was increased up to 45 degrees. The project was finally approved by the Soviet government in August 1954, despite numerous objections within the Communist Party leadership. This supersonic medium-range bomber is a swept-wing aircraft with two engines positioned as the base of the tailfin. The low-mounted swept-back wings are tapered with square tips and a wide wing root. The landing gear pods extend beyond wings’ trailing edges. Two turbojets engines are low-mounted on the tail fin, with round air intakes. This eliminated the need for a complicated boundary layer separation system in the intakes, but added a 15% weight penalty, and made engine maintenance much more difficult because of how high they were off the ground. The fuselage is tube-shaped with a solid pointed nose and a stepped cockpit. Tail flats are low-mounted on the fuselage, sweptback, and tapered with square tips. The fin is swept-back, and tapered with square tip. The prototype of the "105" aircraft with BD-7M engines made its' first flight on 21 June 1958, but was subsequently extensively modified and upgraded. The Russians apparently had engine development problems early in the BLINDER program, and BLINDER prototypes were fitted with interim engines. In April 1958, even before the first flight, the decision was made to equip the aircraft with more powerful HK-6 engines and to build a second prototype with BD-7M engines. As development of the HK-6 engines was delayed, only the second prototype was actually built, which carried out its' first flight in September 1959. During testing, numerous problems arose, and a number of crewman were lost in crashes. Series production of this aircraft -- designated the TU-22 -- started at the plant Nr.22 in Kazan in 1959, where more than 300 TU-22 bombers were built through 1969. It entered operational service in 1962 and by 1970 there were 180 BLINDER aircraft in LRA service. Several versions of the Blinder-bomber were built:







 

Blinder A - Tu-22B -- Blinder A is primarily employed as a medium bomber dropping free-fall bombs, All of the ten 22B bombers were mainly used for training purposes. The aircraft also could be modified to serve as a tanker. Initially, converted TU-16Z planes served as tankers, but from 1972 on they were replaced by TU-22RM aircraft carrying new onboard avionics. Blinder B - Tu-22K -- The Tu-22K was equipped to carry one Kh-22 (AS-4 Kitchen ) 250-nm range air-to-surface The TU-22K carried a missile, and could also carry free-fall bombs. It carried out its' first tests in 1961 and deployment started in 1967 after conclusion of the testing phase. Blinder C -- In 1962 the maritime reconnaissance aircraft TU-22P was equipped with an air refueling system and received the designation TU-22PD. About 70 'Blinder-C' reconnaissance and electronic warfare aircraft were produced Blinder D - Tu-22U -- The - Tu-22B is a trainer version similar to Blinder A, though with a raised student cockpit. Blinder E - TU-22RDM -- Further upgrading in the 1980s lead to the TU-22RDM reconnaissance aircraft.

From 1965 on, all Blinder aircraft were equipped with an air refueling system, consisting of a refueling probe which folds into the fuselage when not in use. And beginning in 1965 the TU-22 fleet was re-equipped with more powerful RD-7M2 engines which allowed an increase in the maximum speed up to 1,600 km/h. The TU-22 bombers was intended to replace the TU-16, but due to its' poor performance it was deemed unsatisfactory. Carrying a similar payload to only a slightly greater range, the Tu-22 offered no real increase in capability. Its limited range was its main disadvantage, though the TU-22K only carried one missile whereas the TU-16 carried up to three. Unreliable and prone to accidents, the Blinder was not built in sufficient numbers to replace the aging Tu-16 Badgers, which remained in service well into the 1970s. Subseqeuntly, KB Tupolev sought to upgrade the TU-22 in the form of a new design [designated "106"] that was supposed to have a range of 6700km, a speed of 2,000km/h and new HK-6 engines. This effort eventually led to the development of the Tu-22M BACKFIRE. The Tu-22 was used by the Soviet Union in the Afghanistan War, and served the Soviet Air Force, and Navy into the late 1980’s. Iraq received about 12 Blinders in 1973, while Libya received their 12 to 18 from 1977 to 1983. They were used by Iraq during in IraqIran War, and by Libya during the conflicts in Sudan and Chad. A number of Blinders from each nation were lost to SAM’s of opposing nations. As of 2000, Ukraine remains the sole operator of the type, with the Libyan, and Iraqi aircraft thought to be unserviceable.

Specifications Design Bureau

OKB Tupolev

Manufacturer

Plant Nr. 22 Kazan

Power Plant

Two VD-7M or Two RD-7M-2 turbojet engines

Thrust

16,000kg 16,500kg

Length

41.6 m 42.6 m with air refueling

Height

10-10.7 m

Wingspan

23.5 m

Wing surface

163.2sqm

Crew

[3 in tandem] One pilot one navigator/systems officer rear gunner

Soviet Designation

Tu-22B TU-22RM Tu-22K

US-Designation

Blinder A Blinder B Blinder C Blinder D Blinder E Basic Medium Bomber

Mission Air Refueling Tanker Development began

August 1954

First Flight

6/21/1958

Series production

19591969

Date deployed

1962

Maximum Takeoff Gross Weight (kg)

85500

Operational Wt. Empty (kg)

39050

TU-22P

Tu-22U

Kitchen ASM Carrier

Maritime Recce Aircraft

Tandem Trainer

1967

1962

1968?

94000 4100048100

84100

84100

41000

39050

TU-22RDM

Recce Aircraft

Fuel weight [kg] Fuel Capacity (gal) Combat Radius (km) Unrefueled Maximum Range [km]

42,500 13,600 2450

42,500 12,350 13002200

34,000

13,600

4400 n.a.

5,650 7,150 (with air refueling)

4900

Normal load

3000

5850

Maximum Payload (kg)

12000

12000

4500 n.a.

Altitude Over Target (m)

11000

11000

12750 n.a.

Ceiling

13,300-14,700 meters

Speed Cruise

832

825

835 n.a.

Speed Combat

1610

1570

910 n.a.

Speed Maximum

1510 km/h (with VD-7M engines) 1610km/h (with RD-7M-2 engines)

Armament: Primary

Bombs One H-22 from missile 250kg up to 9.000kg or nuclear bombs

Armament: Secondary

One R-23 (23mm) gun

Historical Review - Western Estimates Estimated start of flight testing

1959

First discovery Blinder A

January 1960

Blinder B

1961

Blinder C

June 1965

Blinder D

1966

Estimated start of series production

1959

Initial operational capability

1961

Significant operational capability

1962

Tu-22M BACKFIRE (TUPOLEV) The BACKFIRE is a long-range aircraft capable of performing nuclear strike, conventional attack, antiship, and reconnaissance missions. Its low-level penetration features make it a much more survivable system than its predecessors. Carrying either bombs or AS-4/KITCHEN air-to-surface missiles, it is a versatile strike aircraft, believed to be intended for theater attack in Europe and Asia but also potentially capable of intercontinental missions against the United States. The BACKFIRE can be equipped with probes to permit inflight refueling, which would further increase its range and flexibility. After designing the TU-22, the Tupolev design bureau started working on a new bomber that was based on the TU-22. Initially Tupolev considered modifying the TU-22 by changing the angle of the swept wings and equipping it with more powerful engines. However after developing the design "106" and various analysis, the design did not meet the flight characteristic requirements. Tupolev also developed the design "125". The aircraft was supposed have two VK-6 engines, a range of 4500-4800 km and an operating speed of up to 2500 km/h. The design provided for the use of titanium alloys and advanced electronic systems. In 1962, the "125" design was examined by the Government but rejected, as the T-4 aircraft designed by KB Sukhoi was accepted. As an alternative to the T-4 aircraft, KB Tupolev developed the "145" airplane which was a modification of the TU-22. This airplane represented a multi-mode supersonic bomber which was capable of flying at subsonic speed at small altitudes and at supersonic speed to overcome air defenses. The range at subsonic speed was supposed to be 6000-7000 km. The wings are swept-back and had a variable geometry to meet the speed and range requirements. The aircraft should carry Kh-22 air-to-surface missiles which had already been deployed on other aircraft. After activities on the T-4 bombers were halted, KB Tupolev was officially charged with building the "145" aircraft in 1967. The new bomber was intended to have a maximum speed of 2300 km/h and a range of 7000 km without refueling. It received the designation TU-22M. The Tu-22M designation was used by the Soviets during SALT-2 arms control negotiations, creating the impression that the Backfire-A aircraft was a modification of the Tu-22 Blinder. This designation was adopted by the US State and Defense Departments, although some contended that the designation was deliberately deceptive, and intended to hide the performace of the Backfire. Other sources suggest the "deception" was internal, because this made it easier to get budgets approved. According to some sources, the Backfire-B/C production variants were believed to be designated Tu-26 by Russia, although this is disputed by many sources. At Tupolev the aircraft was designated the AM. Many of the development steps in manufacturing the AM were unique in their time. Special attention was given to the construction of the variable sweep wing - the basis of

the whole project. The mid-mounted wings are variable, swept-back, and tapered with curved tips and a wide wing root. Two turbofan engines are mounted in the body, with large rectangular air intakes and dual exhausts. The fuselage is long and slender with a solid, pointed nose and stepped cockpit. The body is rectangular from the air intakes to the exhausts. The tail fin is swept-back and tapered with a square tip. The flats are midmounted on the body, swept-back, and tapered with blunt tips. The wing consists of a center section and two outer panels that have five fixed positions with respect to the leading edge sweep. The two-spar centre section has a rear web and bearing skin panel. The outer wings are secured to the centre section with the aid of hinged joints. The highlift devices include three-section slats and double-slotted flaps on the outer wings (extension angle: 23~ for takeoff and 40~ for landing) and a tilting flap on the centre section. 









Backfire A - TU-22MO -- The first TU-22M received the designation TU-22MO but was only produced in small quantities due to inadequate performance. In February 1973 two TY-22Mo bombers were transferred to a training center. Backfire A - TU-22M -- The first prototype of the TU-22M was finished in July 1971. The test phase of the few TU-22M lasted four years, after which they were deployed with Soviet Naval Aviation. Backfire B - TU-22M2 -- The first large-scale modification of the TU-22M was the TU-22M2, which conducted first flight tests in 1973. It was equipped with NK-22 engines, had range of 5100 km and a maximum speed of 1800 km/h. It carried up to three Kh-22 air-to-surface missiles. The aircraft did not have an automatic terrain-following system but was nevertheless capable of low-level flight to overcome air defenses. In 1976, the TU-22M2 was deployed with the air force and naval airforce. A total of 211 TU-22M2 aircraft were produced at the plant Nr.23 in Kazan between 1973 and 1983. Soon after series production of the TU-22M2 began, the aircraft received new NK-23 engines to increase speed and range. The NK-23 is a booster version of the NK-22 engine, which did not achieve the expected goals. Backfire B - TU-22M2Ye -- Some aircraft were outfitted with new NK-25 engines and an sophisticated new flight-control system. They were designated as TU-22M2Ye, but did not achieve improved flight characteristics. Backfire C - TU-22M3 -- During subsequent upgrades the nose was lengthened, the air intakes changed and the maximum angle of the swept-variable geometry wings increased up to 65 degrees. The aircraft received the designation TU-22M3 and carried out its' first flight test on 20 June 1977. The TU-22M3 began operational evaluation in the late 1970s, and in 1983 it was introduced into the active inventory. Cleared of some of the shortcomings of its predecessor this aircraft soon proved its worth in service with long-range and naval aviation units. The range of the bomber was increased to 6800 km, the maximum speed up to 2300 kms/h and the payload was twice that of the Tu-22M2. The bomber is equipped with a maximum of three Kh-22 cruise missiles or up to ten Kh-15 (AS16) short-range missiles. It can also carry nuclear bombs. In 1985 the TU-22M3 conducted high-peed flight tests at low altitude that demonstrated the capability of countering air defenses.



Backfire - TU-22MR -- In 1985, the long-range reconnaissance aircraft TU22MR entered service.  Backfire - TU-22ME -- Improvement of flight and fighting characteristics continued, and in 1990 the TU-22ME was developed. When the new supersonic bomber appeared at the Kazan aircraft plant in 1969, it validated the long-held Air Force prediction of a new Soviet bomber. In 1971, the aircraft, now designated the Backfire, was noted in aerial refueling from a tanker near the test center of Ramenskoye, just east of Moscow. The mission of the bomber, peripheral attack or intercontinental attack, became one of the most fiercely contested intelligence debates of the Cold War. The key variable was the estimate of the range of the aircraft. A series of competitive analyses to determine the range produced divergent results and failed to end the debate. Tupolev claimed a radius of action of only 2,200km for the early model Backfires. The US Defense Intelligence Agency (DIA) initially had estimated the Backfire's unrefuelled combat radius at approximately 5,000 km, sufficient to pose a strategic threat to the United States, while the Central Intelligence Agency (CIA) estimate was about 3,700 km. subsequently the DIA estimate was reduced to about 4,000 km, and the CIA estimate to 3,360-3,960 km. The dominant view of the American intelligence community was that the Backfire was a peripheral attack weapon and would not play a significant role in a strategic air attack on the United States. This view was based on the Backfire's limited payload, modest selfdefense capabilities, and anticipated difficulty in staging the aircraft from northern Siberian bases. The US lacked hard evidence that the Backfires ever rehearsed intercontinental strike missions. The Air Force estimate of range and intent argued that the Backfire could be used for intercontinental attack -- even if the aircraft flew one-way missions for an attack on the United States. Athough a significant number of Backfire bombers were targeted on US naval vessels, the Backfire was the focus of a hotly contested arms control debate that focused on failure to limit further modernization and production of Backfire fleet. Although the Backfire bomber had an exclusively theater mission, under certain circumstances, it could be used to strike targets in the United States. Arms control opponents contended that the United States left open a loophole the Soviets would eventually exploit. The United States stated that as it can be refueled in flight -- allowing it to reach the United States -the Backfire was an intercontinental bomber and should be subject to the same restrictions as other strategic bombers. The Soviets consistently maintained that the Backfire was not a strategic bomber because of its non-intercontinental range. During the SALT II process, the United States negotiating team obtained a statement from then-Soviet Premier Brezhnev that the Backfire's refueling capabilities would not be upgraded to allow them to function as intercontinental strategic bombers, and that the Soviets would only build 30 of these bombers per year. When the SALT-2 treaty was signed in 1979, the Soviets informed the USA that it would not equip the TU-22M

bombers with air refueling devices. SALT II was not ratified, though subsequently the air refueling system was removed from all TU-22M. According to press reports in the late 1980s, a defector stated that the Backfire was regularly exercised at intercontinental range, that this intercontinental range was greater than the Bison's, that the Backfire had a screw-in type refueling probe, that this screw-in refueling probe was stockpiled for every Backfire at all bomber bases, and that the Soviets had an active program of camouflage, concealment, and deception to mislead the West about the intercontinental range capability of the Backfire. According to press reports, the Soviets tested long range ALCM's on the Backfire in the late 1970's. The CIA in 1987 made the unclassified judgment that it would consider Backfires as ALCMcarriers in the event of confirmed Soviet breakout from SALT II. The CIA's rationale for their judgment was that in the absence of SALT II constraints, the Soviets would use the ALCM-capable Backfire to attack the United States. The Defense Department publication Soviet Military Power published in March, 1983, stated on page 26 that: "The Soviets are developing at least one long-range air-launched cruise missile (ALCM) with a range of some 3,000 kilometers. Carried by the Backfire, the Blackjack, and possibly the Bear, it would provide the Soviets with greatly improved capabilities for low-level and standoff attack in both theater and intercontinental operations."DIA stated in its unclassified February 1990 Soviet Force Structure Summary publication on page 6 that: `The Backfire has an intercontinental strike capability when equipped with a refueling probe.' The US proposed to the Soviets that they sign a politically binding declaration outside of START, which would commit them to: (1) not give the Backfire an intercontinental capability by air-to-air refueling or by any other means; (2) deploy no more than 400 Backfire; and (3) include all Backfire -- including naval Backfire--in the Conventional Forces in Europe [CFE] aircraft limits. On 31 July 1991 the Soviet side declared as part of the START I negotiations that it would not give the Tu-22M airplane the capability of operating at intercontinental distances in any manner, including by in-flight refueling. The Soviet Union stated that it would not have more than 300 Tu-22M airplanes at any one time, not including naval Tu22M airplanes, and that the number of naval Tu-22M airplanes would not exceed 200. In view of the fact that there must be no constraints in the START Treaty on arms that are not strategic offensive arms, Tu-22M airplanes would thus not be subjected to that Treaty. During the 1980s Backfires were used for conventional bombing raids in Afghanistan, particularly during the last year of direct Soviet involvement. By 1991 it was reported that, due to a shortage of spare parts, some Backfire units had mission-capable rates of 30-40%. During the 1990s many Backfires were transferred from Long Range Aviation

forces to Russian naval units in north Russia. However, by the late 1990s, at least 125 were in service with Long-Range Aviation and another 47 were in service with in Naval Aviation. In December 1999 it was announced that India would lease four Tu-22M3 Backfire bombers, with the aircraft slated arrive in India as early as June 2000. India's Tu-142 and Il-38 aircraft will be upgraded in Russia. An initial batch of five aircraft will be sent to Russia and during this period the Tu-22M3s will undertake a maritime role armed with AS-20 Kayak anti-ship missiles. India is making substantial purchases of the Novator 3M-54 Alfa missile to equip Kilo class submarines and its new frigates. It is believed that an air-launched variant will be purchased to arm the Tu-142s currently in service and the six to eight additional aircraft being sought by the Navy. If an air-launched version of the Alfa is procured, it is anticipated that India's Tu-22M3s will eventually be equipped to fire them.

Specifications Soviet Designation

TU-22M0

TU-22M1

TU-22M2

TU-22M3

USDesignation

Backfire A

Backfire A

Backfire B

Backfire C

Design Bureau

OKB-156 Tupolev

6/1/1971

1972

6/20/1977

1971

1973-1983

From 1977 on

1976

1976

1981

Manufacturer Plant Nr. 22 Kazan Approved Development 1967 began First Flight

8/30/1969

Series production Date deployed

Not deployed

Crew

4 men

Unit cost Power Plant

Two NK144-22 turbojet engines

Two NK-22 turbojet engines

Two NK-22 turbojet engines

Two NK-25 turbojet engines

Thrust

20.000kg

22.000kg

22.000kg each

25.000kg

each

each

each

Length

41.5m

41.5m

41.46m

42.46m

Height

11.05m

Wingspan (minimum)

22.75m

25m

25m

23.3m

Wingspan (maximum)

31.6m

34.28 m

34.28 m

34.28 m

Wing surface

183.5sqm (at minimum sweep), 175.8sqm (at maximum sweep)

Speed (cruise) Speed (maximum)

1.530km/h

Ceiling

13.000m

Weight (empty)

53,500kg

1.660km/h

900km/h

900km/h

1.800km/h

2.300km/h 14.000m

Fuel weight Maximum take-off weight

121.000kg

Normal load

122.000kg

122.000kg

6.000kg

Maximum load Operational Range [Russian Sources] Combat Radius unrefueld [US

126.400kg

24.000kg 4,140km

5,000km

5,100km

4,000-5,000 km [DIA] 3,360-3,960 km [CIA]

7,000km

estimates] Armament:

Two GSH23 (23mm) guns

One to three H-22 missiles two GSH-23 (23mm) guns

One to three H-22 missiles six to ten H-15 missiles 24.000 kg of 2509,000kg free fall bombs one doublebarrelled GSH-23 (23mm) guns

Tu-160 BLACKJACK (TUPOLEV) The Tu-160 is a multi-mission strategic bomber designed for operations ranging from subsonic speeds and low altitudes to speeds over Mach 1 at high altitudes. The two weapons bays can accommodate different mission-specific loads, including strategic cruise missiles, short-range guided missiles, nuclear and conventional bombs, and mines. Its basic armament of short-range guided missiles and strategic cruise missiles enables it to deliver nuclear strikes to targets with preassigned coordinates.In the future, after the aircraft is equipped with high-precision conventional weapons it may also be used against mobile or tactical targets. The Tu-160 was the outcome of a multi-mission bomber competition, which included a Tupolev proposal for an aircraft design using elements of the Tu-144, the Myasishchev M- 18, and the Sukhoi a design based on the T-4 aircraft. The project of Myasishchev was considered to be the most successful, although the Tupolev organization was regarded as having the greatest potential for completing this complex project. Consequently, Tupolev was assigned to develop an aircraft using elements of the Myasishchev M-18 bomber design. The project was supervised by V.N. Binznyuk. Trial operations in the Air Forces began in 1987 with serial production being conducted at the Kazan Aviation Association. The Tu-160 is characterized by low-mounted, swept-back, and tapered, variable geometry wings with large fixed-center section. The variable geometry wings (from 20 degrees up to 65 degrees) allows flight at supersonic and and subsonic speeds. Four NK32 TRDDF [turbojet bypass engines with afterburners] of 25,000 kilograms-force power the T-160. The four turbofans, developed by OKB Kuznetsov in 1977, are mounted in pairs under the fixed-center section with square intakes and exhausts extending behind the wings’ trailing edges. The fuselage's slim structure is marked by a long, pointed, slightly upturned nose section and a stepped canopy. Tail flats are swept-back, tapered, and mid-mounted on the fin. The tail fin is back-tapered with a square tip and a fairing in the leading edge. The tail cone is located past the tail section. During the design of the aircraft, special attention was paid to reducing its signature. Measures were applied to reduce the signature of the engines to infra-red and radar detectors. Tests of these survivability measures were first tested on a TU-95 aircraft in 1980. As the most powerful combat aircraft of the Soviet Air Forces, the T-160 flies at 2,000 km/hr and can exceed the 2,000 mark with a mission-specific load. The T-160 can climb 60-70 meters per second and reach heights of up 15,000 meters. The bomber can be refueled during flight by IL-78 and ZMS-2 tanker aircraft. The air refueling system consists of a probe and drogue airborne refueling system. The TU-160 can carry up to 12 Kh-55 long range missiles and Kh-15 short range missiles. The weapons bays can accommodate different loads: carries various bombs: From fee falling nuclear and regular up to 1500 kg bombs. The bomber is not equipped with artillery armament.

The Tu-160 is equipped with a combined navigation-and-weapon aiming system, RID; [radar] for detecting targets on the ground and sea at long distances, an optical-electronic bombsight, an automatic terrain-following system, and active and passive radioelectronic warfare systems, as well as a probe-and-drogue airborne refueling system. It is equipped with K-36DM ejection seats. The cockpit instruments are the traditional electromechanical type. The aircraft is controlled with the aid of a central control column. The engine control throttles are located between the pilots' seats. There is a rest area, a toilet, and a cupboard for warming up food. Studies have also been conducted on using the aircraft as a launch platform for the "Burlak" space launch vehicle, which is designed to carry payloads with a mass of 300 to 500 kg in polar orbits at an altitude of 500 to 700 km. Under this concept the launch vehicle, which has a solid-fuel engine and a delta wing, would be suspended under the airplane's fuselage. In 1981 OKB Tupolev built two prototypes of the bomber and one mock-up that was used for static tests. The first flight test of the "70" aircraft took place on 19 December 1981. During flight tests, one of the two original planes was lost. Shortly after tests began, series production started. In 1984, the factory in Kazan started producing the bomber which received the designation TU-160. Initial plans provided for the construction of 100 airplanes but when their production was stopped in 1992, only 36 bombers had been built. In May 1987, deployment of the first bombers began. Until the end of 1991, 19 TU-160 bombers served in the 184th regiment in Ukraine and became Ukrainian property after the dissolution of the USSR. In 1992 the 121th air regiment based at the aerodrome B.G. Engels was equippd with TU-160 bombers. Subsequently the bombers were tested to carry long range missiles. It was reported on 02 July 1999 that the Gorbunov Kazan Air Industrial Association received an order from the Ministry of Defense of Russia to complete the production of one Tu-160 strategic bomber. According to the Association's general director Nail Hairullin the contract for the aircraft production was worth 45 million rubles. In July 1999 the Minister of Defense of Ukraine Alexander Kuzmuk confirmed that Kiev officially proposed that Moscow accept as payment for the gas debts "about 10 strategic bombers Tu-160 and Tu-95". He refused to tell the exact cost of missile carriers, however, in his judgement, it would be "considerably more" than 25 million dollars for each machine. On 12 October 1999 the Russian air force announced an agreement that would allow Ukraine to pay some of its multimillion-dollar energy debts by handing over 11 strategic bombers. Ukraine had tried to unload the bombers since the Soviet Union collapsed in 1991, but talks had foundered because of differences over the price tag and other conditions. The deal includes eight Tupolev 160 Blackjack bombers and three Tupolev 95 Bears.

The 11 strategic bombers and 600 air-launched missiles exchanged by Ukraine to Russia in payment for the gas debt were transfered in mid-February 2000. Two Tu-160 bombers flew from Priluki in the Ukrainian Chernigov region for the Russian air base in Engels. The missiles were sent to Russia by railroad. Three Tu-95MS bombers and six Tu-160 airplanes had already arrived at Engels since October 1999 in fulfilment of the intergovernmental agreements. Before being moved to Russia, 19 Tu-160 airplanes were stationed at the Priluki airfield and 21 Tu-95MS were located in Uzin.

Specifications Soviet Designation

TU-160

US-Designation

Blackjack

Design Bureau

OKB-156 Tupolev

Manufacturer

Plant Nr. 22 Kazan

Power Plant

4 HK-32 turbojet engines

Thrust

25.000 kg each

Length

54.1

Height

13.1

Wingspan

35.6m (minimum), 55.7m (maximum)

Wing surface

232 sqm

Speed

2200 km/h (maximum), 1030 km/h (ground)

Ceiling

16.000m

Weight (empty)

110.000kg

Fuel weight

148.000 kg

Maximum take-off weight

275.000 kg

Normal load

9.000 kg

Maximum load

40.000

Range

14.000 km (with a load of 9.000kg) 10.500 km (with a load of 40.000 kg)

Armament

12 H-55 or 24 H-15 missiles free falling bombs

Systems Crew

4

Accomodation Unit cost Approved Development began

1975

First Flight

12/19/1981

Series production started

1984

Date deployed

1987

Inventory

AS-1 KENNEL SSC-2a SALISH SSC-2b SAMLET The AS-1 air-to-surface missile is a subsonic,turbojet-powered, cruise missile with a range or 35 to 97 nm. It weighs approximately 6030-lb and has a conventional warhead of 2020-lb. For guidance, it uses a preprogrammed autopilot for launch and climb, a beam rider for mid-course, and semi-active radar for terminal flight. It has a CEP of 150 ft when used in an anti-ship role and a CEP of 1.0 nm when used against land targets. Two AS-1 missiles are carried on the Badger B aircraft. Production of the AS-1 is estimated to have began in 1953, with IOC reached in 1956. It was first seen in 1961. Two versions of the SSC-2 were developed from the Soviet "KENNEL" air-to-surface anti-shipping missile. They resemble a small jet fighter in appearance and are transported on one-axle semitrailers. The field missile SSC-2a "SALISH" is launched from its transport semitrailer which is towed by a KrAZ-214 tractor truck The SSC-2b "SAMLET" coastal missile transport semitrailer is towed by a ZIL-157V tractor truck and is not used for launching. The missile must be removed from the transport semitrailer and placed on a large rail-type launcher for firing. The "SAMLET" coastal defense missile is the most commonly encountered cruise missile, and has been identified in East Germany and Poland.

Specifications Contractor Initial operational capability

1956

Production terminated

1960

First detected

1961

Total length Diameter Wingspan Weight Warhead Weight Propulsion Maximum Speed Maximum effective

range Guidance mode

Mikoyan K-10S (AS-2 Kipper) The AS-2 air-to-surface missile is a supersonic, turbojet-powered, low-level run-in, cruise missile with a range of 30 to 100 nm. The K-10S missile (Article 352), developed specially for the Tu-16K-10 (Badger-C) aircraft as weapon against naval vessels, was in October 1961, together with that aircraft certified for ordnance. One K-10S missile is suspended from the aircraft, under the middle section of the fuselage. It carries either a conventional or a nuclear 2200-lb warhead. The missile weighs approximately 9120 pounds. For guidance, it uses a preprogrammed autopilot for launch and climb, an autopilot with command correction for mid-course flight, and active radar for terminal flight. The guidance system combines inertial guidance during the initial flight stage and active-radar homing close to the target. The missile can carry a nuclear warhead. It has a CEP of 150 ft when used in an anti-ship role and a CEP of 1 to 2 nm when used against land targets.

Specifications Contractor Initial operational capability

1961

First detected

1961

Production terminated

1965

Type

long-range anti-ship standoff missile

Wingspan

4.6-4.88 m

Length

9.5 m

Diameter

0.9 m

Launch weight

4200 kg

Max. speed

1400 km/h

Ceiling

12000 m

Maximum range

260-350 km

Propulsion

Lyulka AL-5 RD-9FK liquid fuel turbojet

Guidance

active radar homing

Warhead

impact with delay-fuzed high explosive, 1000 kg or nuclear 1000-kg warhead

Kh-20 / AS-3 KANGAROO The AS-3 air-to-surface missile is a large, supersonic, turbojet-powered, cruise missile weighing approximately 24,500 lb with a range of 100 to 350 nm. It carries a 5000-lb nuclear warhead. For guidance it uses a preprogrammed autopilot for launch and climb, an autopilot with command guidance for mid-course flight, and a preprogrammed dive to target. It has a CEP of 150 ft when used in an anti-ship role and a CEP of 1 to 3 nm when used against land targets. One AS-3 is carried aboard the Bear B and Bear C aircraft.

Specifications Contractor Type

meduim- to long-range standoff missile

Initial operational capability

1960

First detected

1961

Production terminated

1965

Wingspan

9.2 m

Length

14.9 m

Diameter

1.9 m

Launch weight

11000 kg

Max. speed

2280 km/h

Ceiling

18000 m

Maximum range

650 km

Propulsion

Tumansky R-11 twin spool turbojet with afterburner, 50.9 kN of thrust

Guidance

beam riding

Warhead

high-explosive, 2300 kg, or thermonuclear, 800 kT yield

Raduga Kh-22 (AS-4 Kitchen) Built by A. Berezhnyak's "Raduga" engineering group for Tu-22 and Tu-22M aircraft, this missile is now also arming modified Tu-95K-22 aircraft. During experimental tests conducted from the late nineteen fifties to the early nineteen sixties the Kh-22B version had reached a speed of Mach 6 and an altitude of about 70 km. The "Raduga" Design Bureau, first a branch of Mikoyan's OKB-2-155 Special Design Bureau, became an independent group in March 1957. Since 1974, after the death of Alexander Berezhnyak, its chief engineer is Igor Seleznyev. The Kh-22 missile comes in three variants: 1. Kh22N with a nuclear warhead and inertial guidance; 2. Kh-22M with a conventional load for use against ships and with an active-radar operating during the final flight stage; 3. Kh-22MP for breaking through enemy air defenses (overcoming enemy radars).

Specifications Contractor Type

long-range tactical standoff missile

Wingspan

3.0 m

Length

11.3-11.65 m

Diameter

0.92 m

Launch weight

5780-6000 kg

Max. speed

4000 km/h

Ceiling

24000 m

Maximum range

460-500 km

Propulsion

liquid propellant rocket motor

Guidance

active radar or passive infra-red homing

Warhead

high-explosive, 1000 kg, or nuclear, 350 kT yield

KSR-2 / KS-11 AS-5 KELT The AS-5 air-to-surface missile is a small supersonic, liquid-rocket propelled, cruise missile weighing approximately 7760 lb. It has a maximum speed of Mach 1.2 at an altitude of 30,000 ft. and a range of 80 to 125 nm. It can carry an 1100-lb conventional warhead, or a nuclear warhead weighing 850 to 1200 lb. For guidance, it uses active radar homing from launch to impact when employed in an anti-ship role, and an alternate passive radar homing system when used in an anti-radar role. It has a CEP of 150 ft when used in an anti-ship role, and a CEP of 1 to 2 nm when employed against land targets. The Badger G carries two AS-5 missiles suspended beneath its wings. Production of the missile is estimated to have begun in 1963, with IOC in 1965. It was first seen in 1966.

Specifications Contractor Year

1968

Type

anti-ship and ground attack standoff cruise missile

Wingspan

4.6 m

Length

9.5 m

Diameter

0.9 m

Launch weight

3000 kg

Max. speed

1080 km/h

Ceiling

18000 m

Maximum range

320 km

Propulsion

single stage liquid propellant rocket motor

Guidance

active radar or anti-radar seeker

Warhead

impact- and direct impact-fuzed high explosive, 1000 kg

Service

CIS, Egypt

Raduga KSR-5 (AS-6 Kingfish) The AS-6 air-to-surface missile is a supersonic, liquid-rocket propelled, cruise missile weighing approximately 13,000 lb. It has an estimated maximum speed of Mach 3.5 at an altitude of 65,000 ft. and an estimated range of 300 nm. It can carry an 1100-lb conventional or nuclear warhead. For guidance it uses a preprogrammed autopilot for launch and climb, an inertial guidance system or an autopilot with radio command override for mid-course, and an active radar system for terminal dive when used in an antiship role. It has a CEP of 150 ft when used in the antiship role, and a CEP of 1 to 2 nm when employed against land targets. The AS-6 probably is a follow-on to the AS-2 and AS-5. This is a smaller version of the Kh-22 missile, intended for Tu-16 bomber aircraft. Series production of the KSR-5 (Article D-5) anti-ship version with active-radar homing began in 1966. Target indication is given by either a "Rubin" radar of the Tu-16K-26 or a YeN radar of the Tu-16K-10-26. The KSR-SP antiradar missile entered service in 1972, at which time was also built the KSR-5N version with a nuclear load. On the basis of the KSR-5 was later built the KSR-5NM airborne target for training exercises. Modified Badger C and Badger G aircraft carry two AS-6 missiles. The Backfire may also have been an AS-6 carrier, but evidence is lacking to confirm this estimate. Production is estimated to have begun in 1969,with IOC in Badger aircraft in 1970. IOC with Backfire is estimated in 1974.

Specifications Contractor operational Badger

1970

operational with Backfire

1974

Type

long-range cruise missile

Wingspan

2.5 - 2.61 m

Length

10.0 - 10.52 m

Diameter

0.9 m

Launch weight

3900-4800 kg

Max. speed

3200 - 3400 km/h

Ceiling

20000 m

Maximum range

240-700 km

Propulsion

two stage solid propellant rocket motor

Guidance

active radar or anti-radar seeker

Warhead

proximity-, impact- or impact with delay-fuzed highexplosive, 1000 kg, or nuclear, 350 kT yield 700 kg

Service

CIS, Iraq

Kh-55 Granat AS-15 Kent SS-N-21 Sampson SSC-4 Slingshot The Kh-55 strategic cruise missile is used for destroying targets whose coordinates are known. Its guidance system combines inertial-Doppler navigation and position correction based on comparison of terrain in the assigned regions with images stored in the memory of an on-board computer. The propulsion system is a dual-flow engine located underneath the missile's tail. The missile carries a 200 kt nuclear warhead. The first tests of this missile were conducted in 1978 and a few units were installed on Tu-95MS aircraft in 1984. Three aircraft versions of this missile are known: Kh-55 (Article 120, alias RKV-500, NATO's AS-15a), Kh-55-OK (article 124), Kh-55SM (Article 125, alias RKV-500B, NATO's AS-15b). In addition the land version RK-55 (SSC-X-4) was destroyed in compliance with INF disarmament negotiations. The sea version SS-N-21 Sampson is reportedly deployed on the Akula, Victor III, Yankee Notch, and Sierra class SSN submarines. However, since the SSC-4 coastal defense variant is carried in a 25.6-in (650-mm) diameter canister, some analysts have suggested that the sub- launched variant is probably for launch only from 650-mm diameter torpedo tubes. Russian President Boris Yeltsin announced in January 1992 that he would end the manufacture of all sea- and air- launched cruise missiles. In March 2000 it was reported that the Russian Air Force had tested a new cruise missile with a conventional warhead. It was said to be a Kh-555 missile, which was developed from the Kh-55, with a range of 2000 - 3000 km.

Raduga Kh-65 The Kh-65 missile is a tactical modification of the strategic Kh-55. According to the first available information (on data sheets at the 1992 Moscow Air Show), its range was to be 500-600 km. The reason for shortening its range was that, according to terms of the SALT-2 Treaty, any aircraft carrying missiles with a range longer than 600 km will be regarded as a strategic one and the number of such aircraft is strictly limited. A full-sized versio of the Kh-65SE was displayed for the first time in 1993 (February in Abu Dabi, then September 1993 in Zhukovskiy and Nizhniy Novgorod). The missiles shown at the exhibitions did not differ from the earlier versions except for their range, quoted as 250 km when launched from low altitude and 280 km when launched from high altitude. The Kh-65 was intended for use against large targets with a larger than 300 m2 effective reflecting surface area, particularly warships, under conditions of strong electronic interference. It approaches the target guided by an inertial navigation system while flying

at a low altitude. Having reached the region where the target is located, it rises to a higher altitude and its active-radar target seeking system turns on.

Specifications Version

Kh-55SM

Contractor

Raduga OKB M. I. Kalinin Machine Building Plant

Kh-65SE

Entered Service Total length

8.09 m

6.04 m / 19 ft, 6 in

Diameter

0.77 m; (Kh-55 0.514 m) 0.514 m

Wingspan

3.10 m

3.10 m / 10 ft, 1 in

Weight

1700 kg

1250 kg

Warhead

200-kt nuclear

410 kg HE

Speed

Mach 0.48-0.77

Mach 0.48-0.77

Maximum effective range

3000 km (Kh-55 2500 km)

250-280 km

Propulsion

Flight Altitude Guidance mode

40-110 m

AS 15 Mod A RKV-500A ALCM

AS 15 Mod B RKV-500B ALCM

P-750 Grom BL-10 AS-19 KOALA SS-N-24 SCORPION SSC-5 The P-750 Grom supersonic winged cruise missile with a range of 3000-4000 km was developed for replacing the Kh-55 [AS-15 KENT]. The AS-X-19 Koala was an airlaunched land-attack version derived from the SS-NX-24 Scorpion submarine-launched missile. A pair of AS-19 missiles was expected to arm the Tu-142 Bear-H bomber. The missile carried two warheads independently guided to hit two targets 100 km apart. The letters BL in its American designation refer to the firing range in Barnaul, where it was tested; its Russian industrial index designation is not known. Work on the program was suspended in 1992.

Specifications Contractor

Chelomey

Entered Service

cancelled

Total length

7 meters

Diameter Wingspan Weight

2,000 kg

Warhead

2 x 200 kt nuclear

Propulsion

turbojet or rocket/ramjet

Maximum Speed

supersonic

Maximum effective range Guidance mode

3000-4000 km

Kh-65 / Kh-SD Kh-101 As of 1996 it was reported that at least two next-generation strategic cruise missiles were under development. By late 2000 very few details had emerged concerning either program, neither of which appeared to have received Western designations. It is reported that Russian Air Force plans call for upgrading the Tu-95MS `Bear-H' bomber to carry up to eight Kh-101 or 14 Kh-65 cruise missiles. The status of a plan for the Tu-160 to carry 12 Kh-101s or Kh-65s is unclear, and may have been cancelled. The long-range Kh 101 cruise missile is under development for long-range aviation. It was apparebtly first launched in October of 1998 by Tu-160 during 37th Air Army exercises. It will reportedly be employed with either a nuclear or a conventional warhead. The conventional warhead version required the use of a highly accurate guidance system, which reportedly provides a circular error probable of 12-20 meters. An electro-optic flight path correction system uses a terrain map stored in its onboard computer, as well as a TV-seeker for the terminal stage of flight. The Kh-101's launch weight is 2,2002,400kg and its maximum speed is Mach 0.77. The range of this system probably exceeds 3,000km, and some reports claim a range of as great as 5000 km. Russian President Boris Yeltsin announced in January 1992 that he would end the manufacture of all sea- and air- launched cruise missiles. In March 2000 it was reported that the Russian Air Force had tested a new cruise missile with a conventional warhead. It was said to be a Kh-555 missile, which was developed from the Kh-55, with a range of 2000 - 3000 km. The relationship between the "Kh-555" and the Kh-101, with evidently similar characteristics, is unclear. The Kh-65, also known as the Kh-SD, is reportedly a smaller version of the Kh-101. It is said to be shorter and lighter [by some 600-800kg], with a much shorter range of only several hundred kilometres. It probably uses the same homing system as the Kh-101, but may a Kh-65S anti-ship version may have an active radar seeker. The fact of the existence of this program was first disclosed in data sheets released at the 1992 Moscow Air Show, at which time it appeared to be a tactical derivative of the Kh-55 Granat [AS15 Kent] strategic cruise missile. More recently, it is described as the short range tactical version of the Kh-101. Based on the reported association between the Kh-55 and the Kh-65, it is probably the case that the Kh-101 is a derivative of the previous Kh-55.

Specifications Contractor Designation

Kh-101

Kh-65 / Kh-SD

ground attack standoff cruise missile

Kh-65 ground attack Kh-65S anti-ship

Launch weight

2,200-2,400kg

1,400-1,800kg

Max. speed

Mach 0.75

Mach 0.75

Maximum range

3,000-5,000 km

? 300-500 km

Propulsion

solid booster + cruise turbofan

Year Type Wingspan Length Diameter

Ceiling

Guidance

TERCOM + TV Seeker

Warhead

impact- and direct impact-fuzed high explosive, 1000 kg

Service

Kh-65 TERCOM + TV Seeker Kh-65S TERCOM + active radar seeker

R-1 / SS-1 SCUNNER The R-1 / SS-1 SCUNNER was the first Russian ballistic missile system, incorporating V2 parts and Alcohol and LOX propellants. The SS-1A is essentially unrelated to the SS1b or SS-1c SCUD, which use storable liquid [RFNA and Hydrazine] propellants. The term "scunner" is a Scottish & Northern dialect word for an annoying person or thing, a nuisance, an object of disgust or loathing. The first Russian launch of a V-2 from Kapustin Yar was conducted on 18 October 1947. The first R-1 test flight from Kapustin Yar was conducted on 10 October 1948.

Specifications Total Mass

12,798 kg.

Empty Mass

4,066 kg.

Payload

483 kg.

Core Diameter

1.7 m.

Span

3.6 m.

Total Length

17.0 m.

Engines

1. RD-100

Propellants

Lox/Alcohol

Liftoff Thrust

27,690 kgf.

Thrust (vac)

31,314 kgf.

Isp

233 sec.

Burn time

63 sec.

Isp(sl)

206 sec.

Diameter

1.7 m.

Range

270 km.

Maximum altitude

77 km.

Time of flight

5 minutes.

Max velocity at burnout

1465 m/s.

Accuracy

8 km in range, 4 km laterally.

R-2 / SS-2 SIBLING The ethyl alcohol used in the V-2 and R-1 was replaced by methyl alcohol in the R-2. The first launch of the R-2 missile was conducted from Kapustin Yar on 30 September 1949.

Specifications Total Mass

19,632 kg.

Empty Mass

4,592 kg.

Payload

508 kg.

Core Diameter

1.7 m.

Span

3.6 m.

Total Length

21.0 m.

Engines

1. RD-101

Propellants

Lox/Alcohol

Liftoff Thrust

37,210 kgf.

Thrust (vac)

41,208 kgf.

Isp

237 sec.

Isp(sl)

214 sec.

Burn time

85 sec.

Range

550 km.

Maximum altitude

171 km.

Time of flight

7.5 minutes.

Max velocity at burnout

2175 m/s.

Accuracy

8 km in range, 4 km laterally.

R-11 / SS-1B SCUD-A R-300 9K72 Elbrus / SS-1C SCUD-B The Scud is a mobile, Russian-made, short-range, tactical ballistic surface-to-surface (hence the nomenclature abbreviation SS) missile system. The SCUD-series guided missiles are single-stage, short-range ballistic missiles using storable liquid propellants. The Scud is derived from the World War II-era German V-2 rocket. Unlike the FROG series of unguided missiles, the SCUDs have movable fins. Warheads can be HE, chemical, or nuclear, and the missile, launched vertically from a small platform, has a range of 300 km. Unsophisticated gyroscopes guided the missile only during powered flight - which lasts about 80 seconds. Once the rocket motor shut down, the entire missile with the warhead attached coasted unguided to the target area. Consequently, Scuds had notoriously poor accuracy, and the farther they flew, the more inaccurate they became. SCUD missiles are found in SSM (SCUD) brigades at front/army level. The SCUD series of missiles gave the Soviet front and army commanders an integral nuclear weapons capability. Non-nuclear variants of the SCUD missiles have been exported to both Warsaw Pact and non-Warsaw Pact nations. 

The SCUD-A is also known as SS-1b. The SCUD-B replaced the JS-3-mounted SCUD-A, which had been in service since the mid-1950s.  The longer range SCUD B, also known as SS-1c, can be distinguished by the one meter greater length of the missile and the presence of two air bottles on the side of the superstructure in place of the single bottle used for the "SCUD A" missile. The SCUD B used unsymmetrical dimethylhydrazine (UDMH), a more powerful (and toxic) fuel than the kerosene used on the SCUD A, which required an engine redesign. They were transported originally on a heavy-tracked vehicle based on the JS heavy-tank chassis. This vehicle serves also as an erector and launcher for the missiles. The SCUD-B was introduced on the JS-3 tracked chassis in 1961 and appeared on the MAZ-543 wheeled chassis in 1965. The "SCUD B" missile has appeared on a new transporter-erector-launcher based on the MAZ-543 (8x8) truck. The introduction of this new powerful cross-country wheeled vehicle gave this missile system greater road mobility, reduces the number of support vehicles required, and still preserves a great choice in selecting off-road firing positions. The same basic chassis also has been used for the transporter-erector-launcher for the "SCALEBOARD" surface-to-surface guided missile. In the early 1980s, the SCUD-B was replaced by the SS-23, which has greatly improved range (500 km), increased accuracy, and reduced reaction and refire times.  The SCUD-C SS-1d achieved an initial operational capability with Soviet forces around 1965. It had a longer range, though lower accuracy, than the SCUD B, and was deployed in smaller numbers. As of the late 1990s some remained in service in Russian ground forces.  The SCUD-D SS-1e featured an improved guidance system, possibly incorporating active radar terminal homing, and a wider choice of warheads than

its predecessors. This missile has a range of about 700 km. Initially operational in the 1980s, it may not have been deployed by former Soviet ground forces. At launch, a basic Scud contains about 3,500 kilograms (7,700 pounds) of IRFNA and about 1,000 kilograms (2,200 pounds) of fuel. Most of the IRFNA and fuel is used within the first 80 seconds of flight when the missile is gaining enough speed to reach its target. When this speed is reached, the Scud is designed to shut off its engine by shutting off the propellant tanks (a fuel tank and an oxidizer tank). The unused propellants—roughly 150 kilograms (330 pounds) of RFNA and 50 kilograms (110 pounds) of fuel—remain on board for the remainder of the flight. In the early 1970s, the Soviet Army sought a replacement for the 9K72 Elbrus (SS-1C `Scud B') system, which had a very slow reaction time [around 90 minutes to prepare and fire] and its poor accuracy when using conventional warheads. The replacement system, codename 9K714 Oka [SS-23 Spider], was developed by KB Mashinostroyenia (Machine Industry Design Bureau) in Kolomna. This system was phased out in compliance with the INF Treaty in the late 1980s. Russia’s TBM inventory is limited to thousands of SS1c/Scud B and SS-21/Scarab SRBMs as a result of the Intermediate Nuclear Force (INF) Treaty, which required the elimination of the FSU’s extensive stocks of MRBMs. A second SCUD-followon effort began in the form of the SS-26, which apparently entered service by 1999. The SS-26 SRBM is expected to be both a replacement for the SS-1c/Scud B and an export. By the early 1990s, the `Scud' system was unquestionably obsolete and many of the 9P117 launcher vehicles were retired due to age.

Specifications DIA

SS-1b

SS-1c

SS-1d

SS-1e

NATO

Scud-A

Scud-B

Scud-C

Scud-D

R-11 / R-175

R-300

Bilateral Service OKB/Industry

8K14

Design Bureau

Makeyev OKB Makeyev OKB

Makeyev OKB

Makeyev OKB

Approved

...

...

...

...

Years of R&D

...

...

...

...

Engineering and Testing

...

...

...

...

First Flight Test

...

...

...

...

IOC

...

...

...

...

Deployment

1957

1965

1965 1980s

Date Withdrawn

1978

Type of Warhead

nuclear  Conventional unitary blast Chemical warhead

HE, CHEM  (thickened Conventional VX) unitary blast fuel-air explosive 40 runwaypenetrator submunitions 100 11-lb (5-kg) antipersonnel bomblets

Warheads

1

1

1

1

Yield

...

5-80 kiloton

...

...

11.25 m

11.25 m

11.25 m

Missile Diameter 0.88 m (m)

0.88 m

0.88 m

0.88 m

Launch Weight (t)

6,300 kg

Payload (t) Total length (m)

770-950 kg 10.25 m

Total length w/o warhead (m)

Fuel Weight (t) Range(km)

130 km

300 km

575-600km 700 km

4,000 m

900 m

900 m

CEP (m) (Russian Sources) CEP (m) (Western Sources)

Reaction time

Engine Designation

50 m

60 min

...

...

...

...

Design Bureau

...

...

...

Engine Configuration

One engine

One engine

One engine One engine

Propellants

Liquid Storable

Liquid Storable

Liquid Storable

Liquid Storable

Fuel

Kerosene

UDMH

UDMH

UDMH

Oxidizer

nitric acid

RFNA RFNA RFNA (Russian SG- (Russian (Russian SG02 Tonka 250) SG-02 02 Tonka 250) Tonka 250)

Main Engines Burning time (sec.)

...

...

...

...

Main engines Thrust Sea Level/Vacuum (Tonnes)

...

...

...

...

Main Engines ... Specific Impulse Sea Level/Vacuum (sec.)

...

...

...

SCUD-A

...

SCUD-B/C

R-5 / SS-3 SHYSTER The R-5M missile the [western designation SS-3 Shyster], the first Soviet missile with a nuclear delivery capacity, was a single-stage, medium-range, liquid propellant, roadtransportable, ballistic missile. With a maximum range of 1200 km – sufficient enough to reach strategic targets in Europe – it was also considered to be the first Soviet strategic missile. The missile R-5M was based on the R-5 missile developed by by S.P. Korolev from the Department of the Research Institute of the Special Design Bureau. (OKB-NII) in the early 50's. This predecessor was a single-stage missile with a separable reentry vehicle. According to Western assessments, the initial guidance system for the SS-3 was radioinertial, which was retrofitted with an all-inertial system as more reliable components became available. The R-5M missile differed from its predecessor R-5 in that to increase its reliability an auto-stabilizing command structure was installed. With a larger payload (1300 against 1000 kg) and dry weight (4390 against 4030 kg), the launching weight of the R-5M was more than twice that of the R-1 (28,610 against 13,430 kg). The enhanced design and efficiency in combination with an increase of the specific engine thrust from 206 to 219 seconds allowed an increase in the maximum range almost five-fold relative to the R-1. To maintain an acceptable target accuracy at this increased range, the R-5 missile used a combined guidance/control system with autonomous inertial control plus lateral radio-correction. In-flight control of the missile was maintained with four aerodynamic fins located on the aft bay, and four jet vanes located on the perimeter of the single combustion chamber of the engine. The accuracy of the R-5 was 1.5 km downrange and 1.25 km cross-range from the aim point, and exceeded substantially the accuracy of the R-1 and R-2 missiles. On 10 April 1954 the Soviet Government approved the development of the R-5M. The flight tests of the R-5M were conducted at Kapustin Yar from January 1955 through February 1956. The flight test of the R-5M on 02 February 1956 represented the first full scale testing of a nuclear missile, during which a nuclear warhead with a yield of 300 KT was successfully detonated. The R&D flight test program was assessed by Western intelligence to have begun in 1955, with initial operational capability reached in late 1956. After reaching its IOC the R-5M missile received the index number 8K51 and was introduced into the Strategic Rocket Forces on 02 June1956. Between 1956 and 1957 a total of 48 missiles were deployed, primarily at sites close to the western borders of the Soviet Union. A minimum operational SS-3 field site required only a large presurveyed clearing with soil stabilization or possibly a poured or prefabricated concrete apron. The SS-3 is launched from the vertical position. Reaction time is approximately five hours from the normal readiness condition. The allowable hold time in the most ready prelaunch condition (reaction time equal 15 min) is about one hour. In 1959 they were put on alert for the first time, and it remained in service until 1967. No further

deployment was carried out due to the development of the more effective R-12 missile that subsequently replaced the R-5M Missile.

Specifications DIA

SS-3m

NATO

Shyster

Bilateral

R-5

Service

R-5M

OKB/Industry

8K51 (8A62M)

Design Bureau

(OKB-I), NII-88, (Acad. S. P. Korolev)

Approved

4/10/1954

Years of R&D Engineering and Testing

1955-1956

First Flight Test

1/21/1955

IOC

1956

Deployment Date

6/2/1956

First public display

November 1957

Phase-out completed

1967

Type of Warhead

Single

Warheads

1

Yield (Mt)

1x0.08 - 0.3 MT.

Payload (t)

1.350

Total length (m)

20.747 - 20.8

Missile Diameter (m)

1,652

Diameter of Stabilizers (m)

3.452

Launch Weight (t)

28.9-29.1

Fuel Weight (t)

24.4

Dry weight (t)

4,39

Range(km)

1200

CEP (m) (Russian Sources)

1500 m downrange and 1250 m cross range

CEP (m) (Western Sources)

2500-5000

Number of Stages

1

Booster guidance system

Autonomous/inertial plus radiocontrol

Engine Designation

RD-103M, 8D52

Design Bureau

Acad. V. P. Glushko OKB-456

Years of R & D

1952-53

Propellant

Liquid

Fuel

92% Ethyl Alcohol/water solution

Oxidizer

Liquid Oxygen

Burning time (sec.)

115.4

Thrust Sea Level/Vacuum (Tonnes)

43.86 - 44 / 50.9892 - 51

Specific Impulse (sec.)

219 -220 / 243 -248

Sea Level/Vacuum Basing Mode

Ground-Based

Launching Technique

Hot Launch

Deployed boosters

0

Test Boosters Warheads Deployed Deployment Sites Training Launchers

0

R-12 / SS-4 SANDAL The R-12 was the first Soviet strategic missile using storable propellants and a completely autonomous inertial guidance system. With its capability to deliver a megaton-class nuclear warhead the rocket provided a capability to attack strategic targets at medium ranges. This system constituted the bulk of the Soviet offensive missile threat to Western Europe. It was deployed at both soft launch pads and hard silos. The Sandal is a single-stage rocket with a separable single reentry vehicle. In the integrated fuel tanks the oxidizer was put ahead of the fuel tank, separated by an intermediate plate. During flight this allowed the oxidizer from the lower unit to be spent first thus improving in-flight stabilization. The propulsion system consists of four liquid propellant rocket motors with a common turbopump unit. The flight control was carried out with the help of four carbon jet vanes, located in the nozzles of the rocket motors. The autonomous guidance and control system used center of mass normal and lateral stabilization devices, a velocity control system and an computer-assisted automatic range control system. Its development was accepted on 13 August 1955 by the Ministerial Council and carried out by Yangel's OKB-586. The first tests were conducted at the test site in Kapustin Yar between 22 June 1957 through December 1958. The R-12 missile was introduced into the inventory on 04 March 1959 according to Russian sources, though Western intelligence believed that an initial operational capability was reached in late 1958. Efforts to develop a railway based version of the R-12 missile were suspended. The R-12 missile was surface-launched. However in September 1959 a series of experimental silo launches was conducted and subsequently in May 1960 the development of a new R-12 missile designated as R-12 U was begun. The R-12U was designed to be used with both soft surface launchers and hardened silos. The silo-launch complex of the R-12U missile comprised four launchers and was designated as "Dvina." The testing phase of the missile and the launch complex lasted from December 1961 through December, 1963. The first public display of this system was in November 1960, and they were deployed to Cuba in the Fall of 1962. The first five regiments with surface-based R-12 missiles were put on alert on 15-16 May 1960, while the first regiment of silo-based missiles was placed on alert on 01 January 1963. Reaction time was assessed by the West at one to three hours in the normal soft site readiness condition, and five to fifteen minutes in the normal hard site readiness condition. The allowable hold time in a highly alert condition (reaction time equals three to five minutes ) is long--many hours for soft sites, and days for hard sites.

The R-12 and R-12U missiles reached their maximum operational launcher inventory of 608 in 1964-1966. Some soft-site phase-out began in 1968, with some hard-site phase-out beginning in 1972. In 1978 their phase out and replacement with mobile ground-launched SS-20 "Pioneer" missiles began. The Intermediate-Range and Shorter-Range Nuclear Forces [INF] Treaty was signed on 08 December 1987 and entered into force on 01 June 1988. The fundamental purpose of the INF Treaty was to eliminate and ban US and former USSR (FSU) ground-launched ballistic and cruise missiles, as well as associated support equipment, with ranges between 500 and 5500 kilometers. SS-4 and SS-5 missiles and components were eliminated at Lesnaya. The last of 149 Soviet SS-4 missiles was eliminated at the Lesnaya Missile Elimination Facility on 22 May 1990.

Specifications DIA

SS-4

SS-4

NATO

Sandal

Sandal

Bilateral

R-12

R-12U

Service

R-12

R-12U (Dvina)

OKB/Industry

8K63

8K63U (Acad. M. K. Yangel)

Design Bureau

OKB-586

OKB-586

Approved

8/13/1955

5/30/1960

Engineering and Testing

1957-1959

1961-1963

First Flight Test

6/22/57

12/30/1961

IOC

1959

1963

Deployment Date

3/4/1959

5/30/63

Type of Warhead

Single

Single

Warheads

1

1

Yield (Mt)

1-1.3 / 2-2.3

1-1.3 / 2-2.3

Payload (t)

1.3 -1.4 / 1.63

1.3 -1.4 / 1.63

Total length (m)

22.1 - 22.77

22.1 - 22.77

Total length w/o

18.4 -18.6

18.6

Years of R&D

Warhead (m) Missile Diameter (m)

1.65

1.65

Launch Weight (t)

41.7 - 42.2

41.7 - 42.2

Fuel Weight (t)

37

37

Range (km)

2,080 (2,000)

2,080 (1,800 - 2,000)

CEP (m) (Russian Sources)

5,000

5,000

CEP (m) Western Sources

1500-3000

1500-3000

Basing mode

Ground based

Ground and silo based

Number of Stages Booster guidance system Engine Designation Design Bureau Years of R & D Propellants Fuel Oxidizer

Burning time (sec.) Thrust Sea Level/Vacuum (Tonnes) Specific Impulse Sea Level/Vacuum (sec.) Canister length (m) Canister Diameter (m) Launching Mode Deployed boosters Test Boosters Warheads Deployed Deployment Sites Training Launchers Space Booster Variant

1 Inertial, autonomous RD-214 Glushko, OKB-456 1955-1957 Liquid Storable Tm-185 92%hydrocarbon/kerosene AK-27 I =73% HNO3 + 27%N204 (NTO), Nitrogen Tetroxide concentrated in Nitric Acid 140 64.75 / 74.44 operational 72.00 230 / 264 N/A N/A Hot Launched 0 0 INF Treaty data SL-7 / B-1 Interkosmos booster

R-14 / SS-5 SKEAN The R-14/SS-5 was a single-stage, storable liquid-propellant, intermediate range ballistic missile. The design of the R-14 missile draw heavily on the previously developed P-12 missile. As with the R-12, the Skean missile was a single stage missile with integral fuel tanks though it was larger and twice the maximum range. According to Western estimates it was capable of delivering a 3,500 lb reentry vehicle containing a nuclear weapon to a maximum operational range of 2,200 nm, and using an inertial guidance system with was assessed as having a CEP of approximately 0.5 nm. In comparison to the R-12 the increase of the propellant volume was reached through an increase of the diameter of fuel tanks. Fabrication of tanks with aluminum panels processed by a method of chemical contouring was used for the first time. The propulsion system of the R-14 consists of two identical blocks, each with a two-chamber combustion engine, a turbopump unit, gas generator and automatic control system, as well as a four chambered control motor. The use of hypergolic [self igniting] asymmetrical dimethylhydrazine allowed an increased specific impulse. For the first time a gas generator [instead of hydrogen peroxide] was used to power the main propellant components. The flight control still relied on jet vanes. Unlike the previous single-stage rockets, the R-14 used an efficient system of draining the propellant tanks to reduce required propellant mass. The R-14 marked the first use of a gyro-stabilized platform as part of the autonomous inertial guidance system, allowing fewer instrumental errors and improving accuracy. The R-14 also mounted three solid-propellant retrorockets to prevent accidental collision of the booster with the nose cone after separation. Despite of its substantial longer range, the R-14 demonstrated the same accuracy as the R-12, though given its heavier payload its nose cone was blunted. According to Western intelligence the Mod 1 reentry vehicle had a ballistic coefficient of 1300 lb per sq ft. The development of the R-14 was authorized on 02 July 1958. The authorization provided for the construction of a missile with an approximate range of 4,000 km, surpassing the R-12 by 2,000 km. The designer was M.K. Yangel of KB Yuzhnoye (OKB-586). The preliminary design was completed in December 1958. Flight tests of the R-14 began in July 1960 [Western sources suggest a first flight in June 1960] and were finished between December 1960 and February 1961. On 24 April 1961 deployment of the R-14 missile began. According to Western intelligence the initial operational capability with the Mod 1 reentry vehicle and soft sites was achieved in late 1961. In May I960 the development of the R-14U missile for silo and surface launchers began. The first flight test of the silo-launched R-14U was carried out on 12 January 1962, the surface-launched version was first tested on 11 February 1962. Both were subsequently introduced into the Strategic Missile Forces. The first regiment of surface-based R-14s was put on alert on 01 January 1962. According to Western intelligence an initial

operational capability with hard sites was achieved in early 1963, and the initial operational capability with the Mod 2 reentry vehicle was achieved in mid-1963. The SS-5 was deployed at both soft and hard launch sites. Soft-site reaction time in the normal readiness condition is one to three hours. Hard-site reaction time in the normal readiness condition is five to fifteen minutes. Allowable hold time (reaction time equals three to five minutes) was many hours for soft sites and many days for hard sites. Maximum operational launcher deployment was reached in 1964. Between 1965 and 1969 the deployment of the R-14 and R-14U reached its peak with 97 launchers. Some phaseout of soft sites beginning in 1969 and some phase-out of hard sites beginning in 1971. In the period between 1978 and 1983 they were replaced by SS-20 Pioneer missiles, and in 1984 they were totally withdrawn from service. The Intermediate-Range and Shorter-Range Nuclear Forces [INF] Treaty was signed on 08 December 1987 and entered into force on 01 June 1988. The fundamental purpose of the INF Treaty was to eliminate and ban US and former USSR (FSU) ground-launched ballistic and cruise missiles, as well as associated support equipment, with ranges between 500 and 5500 kilometers. SS-4 and SS-5 missiles and components were eliminated at Lesnaya. Beginning in 1988 the six remaining non-deployed missiles were dismantled in compliance with the INF Treaty. The sixth and final SS-5 missile was eliminated at the Lesnaya Missile Elimination Facility on 09 August 1989.

Specifications DIA

SS-5

SS-5

NATO

Skean

Skean

Bilateral

R-14

R-14U

Service

R-14

R-14U (Chusovaya)

OKB/Industry

8K65

8K65U

Design Bureau

OKB-586

OKB-586 (Acad. M. K. Yangel)

Approved

7/2/1958

5/30/1960

Years of R&D

1958 - 1960

1960 -1962

Engineering and Testing

1960 -1961

1961 -1962

First Flight Test

7/6/1960

2/11/62 (1/12/1962)

IOC

1962

1962

Deployment Date

4/24/1961

1/9/1964

Type of Warhead

Single

Single

Warheads

1

1

Yield (Mt)

1.0 or 2.0 -2.3

1 x 2.3

Payload (t)

1.300 -1.500 or 2.155

1.300 -1.500 or 2.155

Total length (m)

24.3 - 24.4

24.3 -24.4

Total length w/o

21.62

21.62

2.4

2.4

Warhead (m) Missile Diameter (m)

Launch Weight (t) 86.3 - 87

86.3

Fuel Weight (t)

79.2

79.2

Range (km)

4500 or 3200 3700

4500 -3700

CEP (m)

1250 -1900

1250

900-1900

900-1900

(Russian Sources) CEP (m) (Western Sources) Basing mode Ground Based Number of Stages Booster guidance system Engine Designation Configuration Design Bureau Years R & D Propellants Fuel Oxidizer Burning time (sec.) Thrust Sea Level/Vacuum (Tonnes) Specific Impulse Sea Level/Vacuum (sec.)

Ground and Silo Based 1 Inertial, autonomous RD-216m (8D514,M) Cluster of two engines Acad. V. P. Glushko OKB-456 1958-1960 Liquid Storable UDMH AK-27 I = IRFNA =73% HN03 + 27% N204 (NTO) in N02 130 -131 151.4991/171.075 -177.9Total thrust 246-248 / 290-291.3

Canister length (m) N/A Canister length w/o front meters N/A Canister diameter (m) N/A Hardness Launching Technique Deployed boosters Test Boosters Warheads Deployed Deployment Sites Training Launchers Space Booster Variant

Hot launched 0 0 INF Treaty Information SL-8/C-1 Kosmos, Kosmos-3M

Historical Review - Western Estimates First flight test

June 1960

R&D flight testing probably completed

February 15, 1961

Initial operational capability with Mod 1 reentry vehicle

Late 1961

Hard site tests began

Mid 1962

New series of flight tests began

July 12, 1962

Deployment to Cuba began

1962

Initial operational capability with hard sites

Early 1963

Initial operational capability with Mod 2 reentry vehicles

Mid 1963

Maximum operational launcher inventory

1964

First public display.

November 7, 1964

Phase-out of soft sites began

1969

Phase-out of hard sites began

1971

TR-1 SS-12 SCALEBOARD SS-12M SCALEBOARD B SS-22 The SS-12 SCALEBOARD uses the same MAZ-543 (8x 8) chassis as the SCUD-B. The primary recognition difference is the environmental protective container that completely encloses the SCALEBOARD missile. The missile is a liquid-fuel, single-stage system similar to the SCUD, but with greater range (900 km), accuracy, and size of warhead. Like the SCUD, the SCALEBOARD is designed to be fired from a pre-sited position, then moved to another prearranged position. The MAZ-543 has centralized tire pressure control. The SCALEBOARD is a front and theater-level weapon system that gives the Soviet commander a nuclear capability. The SCALEBOARD appeared deployed only with Soviet forces. The mid-range missile can be stationed in the western part of the USSR and still be able to hit important targets in Central Europe. The SS-12 SCALEBOARD, in service since the mid-1960s, was replaced beginning in 1979 with a new missile that had the same range (900 km) with improved accuracy. Initially considered to be a new missile, designated the SS-22, the SS-12M SCALEBOARD B [also known as the SS-12B and the SS-12 mod 2] was subsequently assessed as an improved version of the earlier Scaleboard. By the early 1980s the Soviets were replacing older shorter-range Scaleboard missiles with SS-22s, and were developing the new SS-23 as a follow-on to the Scud missiles. The SS-22 missile had the range to cover a substantial portion of NATO Europe even from its deployment areas within the Soviet Union. The Intermediate-Range and Shorter-Range Nuclear Forces [INF] Treaty was signed on 08 December 1987 and entered into force on 01 June 1988. The fundamental purpose of the INF Treaty was to eliminate and ban US and former USSR (FSU) ground-launched ballistic and cruise missiles, as well as associated support equipment, with ranges between 500 and 5500 kilometers. SS-12 and SS-23 transporter-erector-launcher (TEL) vehicles were eliminated at Stan'kovo. The first Soviet SS-12 missile was eliminated at the Saryozek Missile Elimination Facility on 01 August l988. The last of 718 Soviet SS12 missiles was eliminated at the Saryozek Missile Elimination Facility on 25 July 1989. In February 1997 a top Cuban military defector, Alvaro Prendez, alleged that Cuba was developing biological weapons were to be delivered by five Soviet-made SS-22 missiles that were deployed near the central city of Santa Clara. Prendez and other defectors had heard rumors that the missiles were shipped from Russia to Cuba as late as 1991. Cuba is not known to have any SS-22 missiles, and these claims appear unfounded.

Specifications USA Code Name

SS-12

Nato Code Name:

Scaleboard

Russian Designation:

9M76

Contractors

Nadiradze OKB (design bureau) Votkinsk (missile) Barricade factory, Volgograd, Russia, (TEL)

Stages:

1

Fuel:

Liquid

Inservice:

1969

weight

9,700 kg

length

12.4 m

diameter

1.01 m

Range:

800 km - Mod 1 900 Km - Mod 2

Guidance

inertial

Circular Error Probable (CEP)

0.4 nm / 0.75 km - Mod 1 0.2 nm / 0.37 km - Mod 2

Warhead

500-kiloton nuclear

RT-15 / RT-2P SS-14 SCAMP / SCAPEGOAT The RT-15 / SS-14 medium-range ballistic missile was a two-stage, tandem, solidpropellant missile capable of delivering a nominal reentry vehicle of the 1,200-lb class to a range of about 1,600 nm. Missile gross weight was about 35,800 lb. that was derived from the two upper stages of the SS-13 ICBM. It had an inertial guidance system that was estimated by Western intelligence to have a CEP (at 1500 nm) of about 0.5 nm. The RT-15 [designated the RT-2P according to some sources] was the first Soviet attempt to develop a mobile intermediate range missile. The development of the RT-15 missile was approved on 04 April 1961 and was included in the program of developing the RT-2 / SS-13 missile on whose second and third stages it was based. The missile was intended to be sea and ground launched and had a maximum range of 2000-2500 kms. The designer of the ground-launched RT-15 (8K96) was P.A. Tyurin from KB Arsenal. Two-stage solid fuel missile was deployed on a transport-launching rack, which was placed on the mobile launcher. The launcher was built on the basis of a heavy tank. The SS-14 transporter-erector-launcher was first observed in May 1965, and designated SCAMP by NATO. The SS-14 system was first observed in a Moscow parade in November 1967. the missile inside the container was later seen separately and code named SCAPEGOAT in 1968. Subsequent analysis demonstated that the SCAPEGOAT missile was carried by the SCAMP launcher. In 1968 it was recommended for series production and experimental operation after passing successful tests. Nevertheless the Ministry of Defense refused to accept the deployment of this missile and the program was completely stopped in 1970 after 10 experimental launches were conducted in the years 1969 and 1970. The last flight test observed by Western intelligence was in March 1970, and the program was assumed by Western intelligence to have been cancelled. Less than 30 SS-14s were deployed, all in former Soviet Asia. No permanent facilities other than a benchmark would be necessary at an SS-14 launch site. Preparation of such a site would therefore be minimal. Access to launch sites would be by means of semi-improved or unimproved roads in extremely rough terrain or possibly no roads at all in fairly smooth terrain. Reaction time in the normal readiness condition (condition after arrival at site) would be 20 to 30 minutes. Hold time at peak readiness (reaction time of two to ten minutes) would be about a day.

Specifications DIA

SS-X-14 (SS-14)

NATO*

Scamp/ Scapegoat

Bilateral Service

RT-15

OKB/Industry

8K96

Design Bureau

KB Arsenal (Tyurin-OKB) TsKB-7

Approved

4/4/1961

Years of R&D

1958-63

Engineering and Testing

1966-1968

First Flight Test

9/__/1965

IOC

Not operational 3/__/1970

Deployment Date

Not deployed 3/__/1970

Type of Warhead

Single

Warheads

1

Yield (Mt)

1

Payload (t)

0.535

Total length (m)

11.93

Total length w/o warhead (m)

11.74

Missile Diameter (m)

1.49

Launch Weight (t)

16

Range (km)

2500-2,950

CEP (m) (Russian Sources)

0.9 km

CEP (m) (Western* Sources)

600-2000

Number of Stages

2

Canister length (m)

12,7

Canister length w/o front meters (m) Canister diameter (m)

2,1

Booster guidance system 1st stage

Inertial autonomous 2nd stage

Length (m) Body diameter (m) Fueled weight (t) Dry weight (t) Solid Motor Designation Design Bureau R & D Years Propellants Fuel Oxidizer Burning time (sec.) Thrust Sea Level/Vacuum (Tonnes)

4.74 1.49

6.77 1.01

15D27

15D2 or 15D92

Solid N/A N/A 60 42

Solid N/A N/A 45 22

237/263

271

Specific Impulse (sec.) Basing Mode Hardness Launching Technique Deployed boosters Test Boosters Warheads Deployed Deployment Sites Training Launchers Space Booster Variant

Ground Mobile Hot 0 0

N/A

RT-25 MRBM The RT-25 was intended to be based on the first and third stages of the RT-2. Its maximum range was supposed to be 4000-4500 kms. The governmental order issued on 04 April1961 providing for the development missiles based on solid fuel led to plans to develop this missile. The designated design bureau was Korolev's OKB-1, and the project received the industrial index 8K98 But its development never got beyond the initial stage as the Ministry of Defense suspended further development.

Specifications DIA NATO Bilateral Service

RT-25

OKB/Industry

8K97

Design Bureau

OKB-1/Mashinosteroeniya

Approved

4/4/1961

Years of R&D

1961-1966

Engineering and Testing First Flight Test

No flight tests conducted

IOC

Not operational

Deployment Date

Not deployed

Type of Warhead

Single

Warheads

1

Yield (Mt) Payload (t) Total length (m)

15-16

Total length w/o warhead (m) Missile Diameter (m)

2-1.84

Launch Weight (t)

40-42

Range (km)

4000-5000

CEP (m)

?

Number of Stages

2

Canister length (m) Canister length w/o front meters (m) Canister diameter (m) Booster guidance system

Inertial autonomous 1st stage

2nd stage

Length (m)

8.7

3.83

Body diameter (m)

2.0-1.84

1.01

Fueled weight (t)

34.5

Dry weight (t) Solid Motor Designation

15D23

15D25

Propellants

Solid motor

Solid motor

Fuel

N/A

N/A

Oxidizer

N/A

N/A

Burning time (sec.)

75

Thrust Sea Level/Vacuum (Tonnes)

91

Design Bureau Years R & D

Specific Impulse Sea Level/Vacuum (sec.)

Basing Mode mobile, silo concept Hardness Launching Technique Hot launch Deployed boosters 0 Test Boosters Warheads Deployed 0

Deployment Sites Training Launchers Space Booster Variant N/A

RT-21M / SS-20 SABER The RT-21M / SS-20 is a solid-fuel, two-stage, theater-based ballistic missile based on the first and second stages of the SS-16. The SS-20 was probably intended to replace or augment the SS-4s and SS-5s deployed in the Soviet Eastern European theater, thus providing approximately three times the number of warheads of the older force. The two-stage solid-fuel "Pioneer" with single-nozzle sustainers is derived from the first and second stages of the SS-16 ICBM. The cylindrical casings of the sustainer stages are made from composite materials. The solid propellant charge is rigidly fastened to the sustainer body. The guidance/control system with its onboard digital computer and a gyro-stabilized platform with floating gyros enables the missile to be horizontally positioned and ensures optimal target accuracy. Flight control during the first stage flight is achieved through aerodynamic and jet vanes. During the second stage low temperature gas is injected into the diverging part of the sustainer nozzle. The missile was deployed in a transport-launch canister, which was installed on a roadmobile launcher. The launcher was equipped with systems needed to ensure constant combat readiness, preparation and firing. The missile could be launched from a sliding roof garage at regimental bases or from field deployed sites. Before ignition the launcher was suspended on a hydraulic support, then the container was set upright in a vertical position. Before ignition of the first sustainer stage the missile was popped out of the container with the help of a solid propellant gas generator the missile and the first stage sustainer was started. The control of launch was conducted from a mobile control center. The SS-20 also has the capability to be reloaded and refired. The developer of a complex was the Moscow institute of Thermal Technology which was headed by A.D. Nadiradzye. The flight-design tests were conducted from 21 September 1975 through 09 January 1976 at the Kapustin Yar test site. Deployment of the SS-20 began on 11 March 1976, and the first regiment equipped with the Pioneer missiles was set under airborne alert on 30 August 1976. According to western data, the rocket was tested in three different Mods. The SS-20 Mod1&3 carried a single warhead whereas the SS-20 Mod2 carried a MIRV warhead. The Mod2 equipped with three warheads with a yield of 150 KT each became the standard missile. In this version the warheads are placed on a post-boost vehicle. On 10 August 1979 the tests of the modernized "Pioneer"-UTTKh (15Zh53) began on the Kapustin Yar test site. They continued through 14 August 1980, and on 17 December 1980 the missile designated as SS-20 Mod3 was deployed. This variant had the same propulsion system as earlier versions, but it due to upgrading of a command structure and instrumentation-service unit it was possible to improve accuracy (CEP) from 550 to 450

meters, to increase maximum range by 10 %, and to increase the area covered by the warheads. According to some Western assessments, with a new single, lightweight warhead, or with the addition of a third stage (or both), the SS-20 has the potential to be converted to an ICBM with limited capability against the continental United States. Between 1978 throught 1986 a total of 441 launch complexes for the "Pioneer" missiles were deployed. The SS-20 was one of the missile systems eliminated under the terms of the INF Treaty, which took effect in June 1988. Prior to the INF drawdown, the SS-20 force comprised 48 bases that housed the regularly deployed force of 405 missiles and launchers. The Intermediate-Range and Shorter-Range Nuclear Forces [INF] Treaty was signed on 08 December 1987 and entered into force on 01 June 1988. The fundamental purpose of the INF Treaty was to eliminate and ban US and former USSR (FSU) ground-launched ballistic and cruise missiles, as well as associated support equipment, with ranges between 500 and 5500 kilometers. The first Soviet SS-20 missile and canister were eliminated under INF Treaty at the Kapustin Yar Missile Test Complex on 22 July 1988. The first Soviet SS-20 missiles were eliminated by launching at the Chita and Kansk missile sites on 25 August 1988. The last of 654 SS-20 missiles was eliminated at the Kapustin Yar Missile Test Complex on 12 May l991. And the last of 499 SS-20 launchers was eliminated at the Sarny Launcher Elimination Facility on 28 May 1991.

Specifications Mod-1

Mod-2

Mod-3

DIA

SS-20

SS-20

SS-20/SS-X-28

NATO

Saber

Saber

Saber

Bilateral

RSD-10

RSD-10

RSD-10

Service

RSD10/Pioneer

RSD10/PioneerUTTX

RSD10/Pioneer-3

OKB/Industry

15Zh45 (Temp2C)

15Zh53 (Temp2C)

15Zh53 (Temp2C)

Design Bureau

Moscow Institute of Thermal Technology

Moscow Institute of Thermal Technology

Moscow Institute of Thermal Technology

Approved

3/4/1968

7/19/1977

8/14/1980

Years of R&D

Engineering and Testing

1974-76

1974-1976

1979-1980

First Flight Test

9/21/74

9/21/74

8/10/1979

IOC

1976

1976

1980

Deployment Date

3/11/1976

3/11/1976

12/17/1980

Type of Warhead

Single

MIRV

Single or MIRV

Warheads

1

3

1/3

Yield (Mt)

1.0

0.15

?

Payload (t)

1.5-1.74

1.5-1.74

?

Total length (m)

16.49

16.5

17.0

Total length w/o warhead (m)

14.9

14.9

14.9

Missile Diameter (m)

1.79

1.79

1.79

Launch Weight (t)

37

37

37

Range (km)

600-5000

600-5000

600-5500/7500

CEP (m)

0.550

0.550

0.450

150-450

400-430`

?

Fuel Weight (t)

Russian Sources CEP (m) Western Sources Number of Stages

2

Canister length (m)

19.32

Canister length w/o front (m)

Canister diameter (m)

2.14

Booster guidance system

Inertial, autonomous

1st stage

2nd stage

2nd Stage

Length (m)

8.58

4.4-4.6

4.4-4.6

Body diameter (m)

1.79

1.47

1.47

Fueled weight (t)

26.7

8.63

8.63

Propellants

Solid

Solid

Solid

Fuel

N/A

N/A

N/A

Oxidizer

N/A

N/A

N/A

Burning time (sec.)

63

Dry weight (t) Solid Motor Designation Design Bureau Years R & D

Thrust Sea Level/Vacuum (Tonnes) Special Impulse (sec.) Basing Mode

Ground mobile

Hardness Launching Technique

Mortar Launch

Deployed boosters

0

Test Boosters Warheads Deployed

0

Deployment Sites

INF Treaty data

Training Launchers Space Booster Variant

N/A

SS-23 SPIDER In the early 1970s, the Soviet Army sought a replacement for the 9K72 Elbrus (SS-1C `Scud B') system, which had a very slow reaction time [around 90 minutes to prepare and fire] and its poor accuracy when using conventional warheads. The replacement system, codename 9K714 Oka, was developed by KB Mashinostroyenia (Machine Industry Design Bureau) in Kolomna. The new 9K714 system featured a reaction time of under 30 minutes and used the low-maintenance solid-fuel 9M714 missile. The 300 km range of the R-300 (`Scud') was surpassed by the 400 km range of the 9M714/R-400. In the early 1970s the Warsaw Pact had only a limited ability to strike North Atlantic Treaty Organization (NATO) air bases in Europe. However, by the mid-1980s Soviet forces could strike NATO airfields in all types of weather using tactical ballistic missiles (TBMS) such as the SS-21 and the SS-23. NATO had only limited defense against these weapons, some of which were accurate to within 100 meters. The SS-23 has a range of 310 miles, with speeds of 6,800 miles per hour or Mach 9 that can access most locations in a given theater of war. The Intermediate-Range and Shorter-Range Nuclear Forces [INF] Treaty was signed on 08 December 1987 and entered into force on 01 June 1988. The fundamental purpose of the INF Treaty was to eliminate and ban US and former USSR (FSU) ground-launched ballistic and cruise missiles, as well as associated support equipment, with ranges between 500 and 5500 kilometers. SS-12 and SS-23 transporter-erector-launcher (TEL) vehicles were eliminated at Stan'kovo. On 21 July 1988, US Army Colonel Edward H. Cabaniss led an American INF inspection team to Petropavlovsk in Kazakhstan, approximately 2,000 kilometers east of Moscow. Petropavlovsk was the location of the V.I. Lenin Heavy Machine Building Plant, where the American team conducted a closeout inspection of the former SS-23 missile launcher production facility. The last of 239 SS-23 missiles was destroyed at the Saryozek Missile Elimination Facility on 27 October 1989. The final SS-23 launcher was eliminated the same day at the Stan'kovo Elimination Facility. The Soviet Union had negotiated separate diplomatic agreements with both Czechoslovakia and the German Democratic Republic, where Soviet INF missile units had been based. In the case of the INF Treaty, the Soviet-declared data was not agreed to by each side, and it was not included in the Treaty. Later it turned out that the Soviets had falsified some of their INF data. In April of 1990 the Soviets admitted that they had covertly provided SS-23 missiles banned by the INF Treaty to three East European nations. At least 120 Soviet-controlled SS-23s covertly deployed in Eastern Europe, which the US INF negotiator termed "deceit and mendacity" during the negotiations. In February 1990 President Bush sent Congress a report stating that the Soviet SS-23 deployment did constitute "bad faith." But he didn't say whether it was a violation of the INF Treaty. The State Department was embarrassed by the discovery later that some Soviet-declared INF data was false, because the State Department had repeatedly vouched for its accuracy in public when advocating the Treaty.

Iskander / SS-26 The road-mobile SS-X-26 is the second attempt to replace the `Scud', since the first attempt, the Oka SS-23 SPIDER, was eliminated under the Intermediate Nuclear Forces (INF) Treaty. The operational requirements for the SS-26 are probably similar to those of the original SS-23. One of the major questions concerning the program is the missile's range, which is almost certainly less than the 500 km range limit established by the INF Treaty. The SS-26 may include a longer range (greater than 400 km) variant for the Russian forces, and a shorter range (less than 300 km) variant for export. The new TEL is probably based on the new BAZ-6909 family of trucks, first publicly displayed at a commercial transport show in Moscow in August 1995. Two missiles are carried on each launcher, though the delay between firing each round is unclear. The new TEL is apparently based on the the 9P71 Oka TEL, though the new SS- X-26 TEL has been designed with the INF Treaty in mind, with several external changes that clearly differentiate the two vehicles to prevent treaty compliance problems. The nose of the vehicle has been extended forward, the chassis lengthened, and the access door arrangement has been changes. The tactical parameters of the two vehicles are probably similar. In 1996 Russian television reports depicted the first launch of the SS-X-26, which is a direct evolution of the SS-23 Oka. It appears probable that new features will be incorporated into the design. The SS-X-26 appears to have several different conventional warheads, including a cluster munition warhead, a fuel-air explosive enhanced-blast warhead, a tactical earth penetrator for bunker busting and an electro- magnetic pulse device for anti-radar missions. Given the relatively small warhead, improved terminal precision is a major system requirement, which could be achieved by active terminal sensor such as a millimetre wave radar, satellite terminal guidance using GLOSNASS, an improved inertial platform, or some combination of these approaches. As of 1999 it appeared that this system had entered operational service with the Russian Army. The launch installation has two missiles with a range of 280 kilometers. Each missile has a 480 kilogram warhead consisting of 54 elements. The system can be used against small and large targets. The Iskander missile can easily overcome air defense systems. It's almost impossible to prevent a launch of an Iskander missile because of the system's mobility. Targets can be found not only by satellite and aircraft but also by a conventional intelligence center and by a soldier who directs artillery fire. Targets can also be found from photos, which will be put into a computer by means of a scanner. The self-direction device functions even in fog or darkness. Only the Iskander system can accomplish such tasks. The United States has tried to reconsider the missile technology control regime and here arises the question whether this may be an obstacle for the sale of the new missile abroad. Such missile systems as Iskander have a special place in the world weapons market. Even a small amount of such missiles drastically changes the balance of force in conflicts.

According to Nikolay Guschin, chief and senior designer of the Machinebuilding Design Office, the complex is meant ' for covertly preparing and launching effective missile strikes at small-size targets of particular importance. A specificity of this complex is the high level of automation in the pre-launch preparations little time required to make it ready, and the high precision of shooting. Research carried out by specialists from the leading Russian military science centers has shown that the lskander-E missile complex is 5 to 8 times better than its foreign analogues in terms of the "effectiveness-cost" criterion. As for its tactical and technical characteristics, it also poses a great improvement on the existing Russian tactical missile complexes. Capable of accomplishing tasks connected with the use of non-nuclear warheads, it's the world's first complex equipped with two-missile launch installation. Weighing 3800 kilos each, controlled throughout the trajectory of their flight, equipped with various systems of correction and self-targeting, its missiles are capable of overcoming the enemy's anti-missile defences and hitting targets at a distance of 280 kilometers. According to military experts, the lskander-E missile complex will serve as "determent weapon" in local conflicts, and as strategic arms for the countries with limited territory. Its great range of shooting making it possible to use it from the depth of one's own positions, and the brief time it can stay in its launch position make the complex virtually invulnerable to ordinary weapons. The composition of the complex makes it possible to ensure the full cycle of its use in combat, including its combat control, information base, technical servicing and the training of its crews, without the involvement of additional remedies.

Specifications DIA Code Name

SS-26

Nato Code Name:

?

Russian Designation:

Iskander

Design Bureau:

KBM Engineering

Inservice:

1999

Range:

300 Km

Stages:

1

Warhead:

480Kg - unitary or 10 Submutitions

Weight:

3,800 Kg

Fuel:

Solid

Guidance:

GPS/GLONASS/Inertial/ Possibly IR Terminal Homing

SS-NX-13 [KY-9] SLBM The SS-NX-13 submarine-launched ballistic missile is a short-range, two-stage, storable liquid-propellant missile apparently designed for an anti-ship role. It is capable of delivering a reentry vehicle in the 2500-lb class, containing a warhead with a yield of 2.0 to 3.5 MT, to a minimum operational range of 80 nm or a maximum operational range of 360 nm. The missile flies a lofted trajectory, and is unique in that it has an impact-point correction capability of up to 30 nm through use of a restartable second-stage. The missile uses an inertial guidance system aided by an onboard passive ELINT target sensor. In a pure ballistic mode the SS-NX-13 is capable of a CEP of about 0.3 nm, and against cooperative targets, i.e., a target emanating radio-frequency transmissions, the SS-NX-13 is capable of a CEP of 0.1 to 0.2 nm.

SS-N-3 SEPAL SSC-1a SHADDOCK The "SHADDOCK/SEPAL" missile is an interesting example of the limits of Western intelligence during the early years of the Cold War, since NATO applied the SHADDOCK designation to six different and unrelated missiles, yet the virtually identical S-35 and P-35 missiles were given two different codenames -- SEPAL and SHADDOCK, respectively. The SS-N-3 is a family of turbojet-powered, cruise missiles with three variants [confusingly, the Western nomenclature designates the initial P-5 variant with the highest number -- SS-N-3c]. The P-5 [SS-N-3c Shaddock], an inertially-guided missile, is launched from Echo II, Whiskey Conversion, and Juliett submarines and flies to a maximum range of 250 nm at a speed of . It is the oldest of the three SS-N-3 missiles and is almost identical to the Soviet Army SSC-1a (Shaddock). The P-5 cruise missile was designed in the 1950's by the Chelomey design bureau. The P-5 had a special system of two unfolding wings "ARK-5", which allowed it to be launched from the relatively low diameter cylindrical submarine launcher. P-5 had a range of 500 km at an altitude of 100-400 meters and a speed of 345 m/s [Mach 0.9]. The later P-7 variant had a range of 1000 km. These characteristics allowed the P-5 to effectively penetrate the US coastal air defense system of the early 1960's. The circular error probable at full range was 3,000m, which was compensated by the 930 Kg "RDS-4" nuclear warhead. As with the US Navy's Regulus, to fire the SS-N-3c the submarine platform had to surface for launch, deploy and activate a tracking radar, and remain on the surface linked to the high altitude cruise missile in flight via datalink, providing guidance commands based on the submarine radar's tracking data. The P-6 [SS-N-3a Shaddock] is a more accurate cruise missile later developed for targeting US Aircraft carriers. This radar-homing missile is launched from Echo II and Juliett submarines and flies to a maximum range of 220 nm at a cruise speed of Mach 1.2. A 2200-lb conventional or nuclear warhead is estimated for the SS-N-3a. In its antiship version, the Echo depended on prior cueing by a radar-equipped maritime patrol aircraft and terminal homing by a radar seeker on the SS-N-3 itself. The high altitude, relatively slow SS-N-3 was vulnerable to air defenses in flight, and its radar seeker was vulnerable to jamming and deception measures. The P-35 SS-N-3b (SEPAL), also a radar-homing missile, is launched from Kynda and Kresta I class guided-missile cruisers and generally flies to a range of 150 nm at a speed of Mach 1.2. It is estimated to carry a 2200-lb warhead. The S-35 SSC-1a "SHADDOCK" missile is transported in and launched from a long cylindrical container mounted on an eight-wheel vehicle of distinctive appearance. For

launching, the crew 'lowers the four hydraulic stabilization jacks, removes the hemispherical end covers to the top-mounted tables, clamps down the blast shields over the windows, and elevates the container to the proper launch angle. The SSC-lb coastal defense version can be distinguished by the longer driver's cab on the transport-launch vehicle.

Specifications Contractor

Chelomey

Entered Service Total length

10.20 meters [SS-N-3a/b] 11.75 meters [SS-N-3c]

Diameter

0.98 meter

Wingspan

5.00 meters

Weight

5,400 kg

Warhead

1000 kg conventional high explosive or 350 kiloton nuclear warhead

Propulsion

2 solid-fuel boosters 1 turbo-jet sustainer

Maximum Speed

Mach 0.9

Maximum effective range

450 km [SS-N-3a/b] 750 km [SS-N-3c]

Guidance mode

inertial with mid-course guidance through data link from launch platform

Single-shot hit probability

P-1 Strela Shchuka-A SS-N-1 Scrubber The SS-N-1 Scrubber [in British usage, a "scrubber" is young lady of dubious integrity] was a cruise missile with a nuclear warhead. With the Russian service designation P-1 [also sometimes referred to as the Strela or Shchuka-A], it was deployed on the Kildinclass and Kanin-class destroyers [Soviet designation Large Rocket Ships]. Between 1966 and 1977 these ships were modernized and redesignated Large Anti-Submarine Ship (Bol'shoy Protivolodochny Korabl' – BPK) in the face of the obsolescence of the SS-N-1 Scrubber.

Specifications Contractor

Chelomey

Entered Service

1957

Total length

7.6 meters

Diameter

0.9 meter

Wingspan

4.6 meters

Weight

3,100 kg

Warhead

nuclear warhead

Propulsion

liquid rocket

Maximum Speed Maximum effective range

40 km

Guidance mode

inertial

Single-shot hit probability

P-70 Ametiste 4K-66 SS-N-7 Starbright The SS-N-7 is a subsonic, solid-propellant, cruise, anti-ship missile launched from a submerged Soviet submarine. It was a scaled down P-5 [SSN-3 Shaddock] designed to arm Project 670A class [Charlie class] submarines. It is believed to be capable of carrying a payload of 1170-lb a distance of about 30 nm. It was intended to replace the high altitude, relatively slow SS-N-3, which was vulnerable to air defenses in flight and used a radar seeker that was vulnerable to jamming and deception measures. The shorter range of the SS-N-7 compared to the SS-N-3 reduced the flight time of the missile and eliminated the need for mid-course guidance. This eliminated the need for a guidance radar on the submarine, which allowed a fire and forget submerged launch.

Specifications Contractor

Chelomey

Entered Service Total length

6.7 meters

Diameter Wingspan Weight

3,375 kg

Warhead

500 kg conventional high explosive or 200 kiloton nuclear warhead

Propulsion

solid rocket engine

Maximum Speed

Mach 0.9

Maximum effective range

50-65 km

Guidance mode

inertial with terminal homing

Single-shot hit probability

P-120 Malakhit 4K-85 SSN-9 Siren The P-50 Malachit was developed as a "universal" anti-ship missiles for submarines and surface ships. It was intended to replace the high altitude, relatively slow SS-N-3, which was vulnerable to air defenses in flight and used a radar seeker that was vulnerable to jamming and deception measures. Intended to replace P-50 missile, development of the P-120 Malakhit [industrial code 4K-85] started 1963. The shorter range of the SS-N-9 compared to the SS-N-3 reduced the flight time of the missile and eliminated the need for mid-course guidance. This eliminated the need for a guidance radar on the submarine, which allowed a fire and forget submerged launch. It was initially deployed on surface ships and subsequently on the Charlie-II submarines. It has been superceded by the longer-range SS-N-22 Sunburn.

Specifications Contractor

Chelomey

Entered Service

1969

Total length

8.84 meters

Diameter Wingspan Weight

3,000 kg

Warhead

500 kg conventional high explosive or 200 kiloton nuclear warhead

Propulsion

solid-fuel booster and sustainer [liquid-fuel rocket engine according to some sources]

Maximum Speed

Mach 0.8 [Mach 1.4 according to some sources]

Maximum effective range

110 km

Guidance mode

inertial terminal homing

Single-shot hit probability

P-350 Bazalt 4K-77 P-500 Bazalt 4K-80 SS-N-12 Sandbox SS-N-12 Sandbox is a Russian supersonic speed cruise missile with a range of 550 km carrying a payload of 1,000 kg. The P-350 Bazalt [industrial code 4K-77] was the successor to the P-35 Bazalt, which was started in 1963 and subsequently cancelled. It evolved into the P-500 Bazalt [industrial code 4K-80] which was the production version of the original P-350 Bazalt. Developed to replace the SS-N-3 Shaddock anti- ship missile, it was initially deployed on Kiev-class aircraft carriers in the mid-1970s. The Slava-class cruisers carry an advanced version with an improved sophisticated guidance system, an autopilot that can be programmed for mid-course maneuvers, and an enhanced engine. The P-700 Granat [SSN-19 Shipwreck] was developed as a more successful turbojet alternative to the SSN-12 Sandbox, from which it was derived.

Specifications Contractor

Chelomey

Entered Service

1973

Total length

11.70 meters

Diameter

0.90 meters

Wingspan

2.60 meters

Weight

5,000 kg

Warhead

1,000 kg high-explosive or 350 kiloton nuclear

Propulsion

liquid-fueled rocket [turbojet according to some sources]

Maximum Speed

Mach 2.5

Maximum effective range

550 km

Guidance mode

mid-course missile guidance radar on lamuch platform active or passive terminal homing

Circular Error Probable (CEP)

300-700 m

P-700 3M-45 Granat SS-N-19 SHIPWRECK The P-700 Granat [SSN-19 Shipwreck] was developed as a more successful turbojet alternative to the SSN-12 Sandbox, from which it was derived. Developed in the 1970's, the Shipwreck's initial employment was on the battle cruiser Kirov (later renamed Admiral Ushakov). The Shipwreck was subsequently deployed on the nuclear powered cruiser Peter the Great. It is also deployed on submarines, which can launch the missile while submerged.

Specifications Contractor

Chelomey

Entered Service Total length

10 meters

Diameter

0.85 meters

Wingspan Weight

7,000 kg

Warhead

750 kg conventional high explosive or 500 kiloton nuclear warhead

Propulsion

2 solid-fuel boosters 1 turbojet sustainer engine

Maximum Speed

supersonic

Maximum effective range

625 km

Guidance mode

inertial with command update, active radar/IR and anti-radar homing

Single-shot hit probability

Project 651 / Juliett Project 651 (NATO designation - Juliett) was ordered by the Soviet Navy in the late 1950s to provide a nuclear strike capability against the US homeland, particularly East Coast cities. The Juliett had four nuclear armed cruise missiles on board, and ten torpedo tubes with up to 22 torpedoes. The time required for the first missile launch was about 4.5 minutes, with the second after 10 seconds. The missiles were launched from the surface, while the submarine was moving at a speed of up to 4 knots. Initially armed with the P-5 [SS-N-3c Shaddock] inertially-guided missile, it was subsequently equipped with more accurate cruise missiles [the P-6 SS-N-3a Shaddock, and the later P-500 4K-80 Bazalt SS-N-12 SANDBOX] which were deployed on these submarines for targeting American aircraft carriers. The Juliett is about 4 times larger than WWII submarines. The Project 651 is of doublehull construction with an exceptionally large reserve buoyancy. The hull itself contained eight compartments: I. forward torpedo room, II. living accommodations and forward batteries, III. Missile control room and batteries, IV. submarine control room, V. living accommodations and two banks of batteries, VI. Diesels and generators, VII. electric motors and VIII. after torpedo room. The submarine's hull is covered by two inch thick black tiles made of specially profiled sonar/ sound absorbing hard rubber. The silver zinc batteries allow travel submerged with a maximum speed of 17,5 kn. for 1.5 hours, with a maximum underwater range of 810 miles. Another advancement was a low magnetic signature austenitic steel hull. A special 10m2 target guidance radar was built into the forward edge of the sail structure, which opens by rotating. The boats were eventually fitted with the Kasatka satellite downlink for targeting information. It was originally planned to build 35 of these submarines to augment nuclear-powered Project 675 (ECHO II) class submarines which with 8 missile launchers were an enlarged nuclear version of the Juliett. In fact only 16 submarines were actually built from 1962 to 1968, most of them by Krasnoye Sormovo shipyard in Gorky. The Juliett's were in active service through the 80's with the last one decommissioned in 1994.

Specifications Displacement (tons):

3,174 Tons Surfaced 3,636 Tons with additional fuel 4,137 Tons Submerged

Speed (kts):

19 knots Surfaced 14 knots Dived

Operating Depth

775 ft maximum Safe Depth 1,200 ft crush depth

Dimensions (m):

297 ft (90 M) long 32.8 ft (10 M) beam

23 ft (7 M) draft Propulsion

2 Main Diesel (3500 hp each) 2 Electric Motors (3000 hp each) 300 Tons Silver Zinc Batteries 2 Shafts/Propellers 2 Electric "Silent Run" (150 hp) 1 Diesel Generator (3000 hp)

Endurance:

90 days 9000 miles at 8kn Surfaced 18,000 miles at 7kn max. with additional fuel 810 miles submerged at 2,74 kn.

Crew

12 Officers, 16 NCO, 54 Crew

Armament:

4 P-5 (P-6 or P-500) Guided Cruise Missiles 6 Bow torpedo tubes - 21" (533 MM) 4 Stern torpedo tubes - 16" (400 MM)

Electronics

Radar  Sonar 

Class Listing Boat # nu mb er

Chronology Fl Na Ship ee Laid Laun Com me yard t Down ched m.

Stri cke n

Notes

K156

KS

199 11/16 07/31 12/10 1/1960 /1962 /1963 95

K85

KS

199 ------- ------- 12/30 ----/1964 195

K70

KS

199 ------- ------- 12/31 1----/1964 95

redesignated to B-270

K4 24

KS

10/15 03/11 10/31 199 /1961 /1965 /1965 4?

redesignated to B-124 1994 sold to Finland as floating restaurant

K5 77

KS

------- ------- 10/31 199 ----/1965 1-

1

2

3

1987 redesignated to B-156

95 K6 81

KS

11/20 08/07 12/14 199 /1963 /1964 /1965 4

KS

199 ------- ------- 12/28 1----/1965 95

K63

KS

199 ------- ------- 06/12 1----/1966 95

K58

KS

199 ------- ------- 09/23 1----/1966 95

K1 73 0

KS

199 ------- ------- 12/15 ----/1966 195

K1 67 1

KS

199 ------- ------- 09/30 1----/1967 95

K1 78 2

KS

199 ------- ------- 11/01 ----/1967 195

K1 203 3

KS

------- ------- 12/02 199 1----/1967 95

K1 304 4

KS

199 ------- ------- 08/21 1----/1968 95

K1 318 5

KS

------- ------- 09/29 199 1----/1968 95

K1 120 6

KS

199 ------- ------- 12/26 1----/1968 95

7

8

9

K68

1994 sold to Finland as floating restaurant

redesignated to B-478

Project 659 / Echo I Project 675 / Echo II The Project 659 [Echo I] nuclear-powered cruise-missile submarines were designed to launch the land-attack version SS-N-3c Shaddock. They carried 6 Shaddock missiles in erectable launch tubes mounted in pairs above the pressure hull on both sides of the sail. The Echo I boats, which used a reactor and propulsion system similar to the Hotel SSBN and November SSN classes, were converted to attack submarines in the early 1970s. At least one and possibly two were decommissioned in the mid-1980s, while the remaining three or four units were decommissioned in 1990. The Project 675 [Echo II] nuclear-powered cruise-missile submarines were modified to carry the Front series of radars [also featured on the Juliet-class SSG] that enabled them to launch the anti-shipping version of the Shaddock. These were primarily anti-carrier weapons, intended originally as a response to nuclear strikes against the Soviet Union by carrier-based aircraft like the A-3 Skywarrior. As such, their SS-N-3s came in both nuclear and conventional versions. A total of eight missiles were carried, two more than on the Echo-I, and the hull was lengthed five meters to accomodate the extra pair of launchers. According to Western estimates about 20 minutes was required to launch all eight missiles. To fire its missiles the submarine surfaced, deployed and activated a tracking radar, and remained on the surface linked to the high altitude cruise missile in flight via datalink, providing guidance commands based on the submarine radar's tracking data. The submarine itself was highly vulnerable to attack while on the surface operating its radar. A total of 29 Echo IIs were constructed between 1962 and 1968, of which perhaps 10 were converted to carry the improved SS-N-12 by the mid-1980s. All had been de-commissioned by the mid-1990s. At least four Echo submarines have suffered serious accidents. In August 1980 a fire in an Echo II off Japan killed at least nine crewmembers. On 26 June 1989 a fire erupted in of the the two reactor compartments on an Echo II submarine of the Northern Fleet. The reactor had to be shut down, and the submarine surfaced to return to Murmansk under auxiliary diesel power. Several crew members were injured, but none were killed in the incident. There is some confusion over the numbering of the damaged submarines. According to one reasobably authoritative account, the Navy has four damaged submarines, of which three are in the Far East, in the Pavlovski Bay (project 675, serial No. 175 and 541 and project 671, serial No. 610) and one - in the North (project 675, serial No. 533). The cores of submarines No. 541 and 533 are planned to be discharged. These numbers are at variance with those reported by other sources, and certainly reflect at least in part the annoying Russian habit of re-designating their ships.

Specifications Project 659 / Echo I

Project 675 / Echo II

Displacement (tons):

4,500 tons surfaced 5,500 tons submerged

5,000 tons surfaced 6,000 tons submerged

Speed (kts):

20 kts surfaced 25 kts submerged

20 kts surfaced 23 kts submerged

Dimensions (m):

110.0 meters long 9.0 meters beam 7.5 meters draft

115.0 meters long 9.0 meters beam 7.5 meters draft

Propulsion

2 pressurized-water nuclear reactors steam turbines; 25,000 shp 2 shafts 5-bladed propellers

2 pressurized-water nuclear reactors steam turbines; 30,000 shp 2 shafts 5-bladed propellers

about 75

about 90

6 - SS-N-3 6 21-in (533-mm) torpedo tubes (fwd) 4 16-in (406-mm) torpedo tubes (aft)

8 - SS-N-3 or 8 - SS-N-12 6 21-in (533-mm) torpedo tubes (fwd) 4 16-in (406-mm) torpedo tubes (aft)

Radar Front Door or Front Piece targeting Snoop Tray Surface Search Sonar Herkules Fez

Radar Snoop Tray Surface Search Sonar Feniks low-frequency

Endurance: Crew

Armament:

Electronics

Class Listing Boat NO Name .

Chronology Ship Launc Com yard Laid Down hed m.

Stric ken

Notes

Project 659, NATO code "Echo I" K45

KM

12/28/ 05/12/ 09/18/ 1957 1959 1960

199 06/1961 operational 0 1965-69 project 659T converted to SSN under SALT-1

K59

KM

-------- -------- 12/10/ --1961

199 1965-69 project 659T converted 0 to SSN under SALT-1

K66

KM

-------- -------- 12/10/ --1961

199 1965-69 project 659T converted 0 to SSN under SALT-1 '04/23/1980 fire (mutiny?) in reserve

K122

KM

-------- -------- 04/13/ --1962

198 1965-69 project 659T converted 1 to SSN under SALT-1 '08/21/1981 reactor accident,stricken

K259

KM

-------- -------- 12/**/ --1962

199 NO. possibly K-151 0 1965-69 project 659T converted to SSN under SALT-1

Project 675, NATO code "Echo II" K1

SV

-------- -------- 1962--68

---------

1987 project 675MK converted (satellite targeting)

K7

KM

-------- -------- 1962--68

---------

1968 redesignated to K-127

K10

KM

-------- -------- 1962--68

K22

Krasnov SV ardeets

198 lead ship built at KM 2 1980 collided with Chinese submarine

-------- -------- 1962--68

---------

1993 project 675MK converted (satellite targeting)

K23

KM

-------- -------- 1962--68

---------

K28

SV

-------- -------- 1962--68

---------

redesignated to K-428

K31

KM

-------- -------- 1962--68

---------

04/29/1969 redesignated to K431 01/13/1986 reactor accident,in reserve

KM

-------- -------- 1962--68

---------

redesignated to K-134

K35

SV

-------- -------- 1962--68

---------

1991 project 675MK converted (satellite targeting)

K47

SV

-------- -------- 1962--68

---------

09/26/1976 fire

K34

Kefal

K48

KM

-------- -------- 1962--68

---------

project 675K converted (SLEP)

K56

SV

-------- -------- 1962--68

----- 06/13/1973 collided with ----- research ship

K57

KM

-------- -------- 1962--68

---------

K74

SV

-------- -------- 1962--68

---------

K86

SV

-------- -------- 1962--68

---------

K90

KM

-------- -------- 1962--68

---------

K94

KM

-------- -------- 1962--68

---------

K104

SV

-------- -------- 1962--68

---------

K108

KM

-------- -------- 1962--68

---------

K116

KM

-------- -------- 1962--68

---------

K125

SV

-------- -------- 1962--68

---------

K128

KM

-------- -------- 1962--68

---------

K135

KM

-------- -------- 1962--68

---------

K166

SV

-------- -------- 1962--68

---------

K172

KM

-------- -------- 1962--68

---------

K175

KM

-------- -------- 1962--68

---------

K184

KM

-------- -------- 1962--68

---------

K189

KM

-------- -------- 1962--68

---------

redesignated to K-557

diver tranport converted

redesignated to K-144

08/19/1978 reactor accident

lead ship built at SV

hull NO. possibly K-131

K192

SV

-------- -------- 1962--68

---------

06/25/1989 reactor accident,in reserve in storage at Polyarny

Project 670 Skat / Charlie I Project 670M Skat-M / Charlie II The CHARLIE was originally planned as a small, "mass-production" submarine that would be the lower-cost complement to the more expensive PAPA design, which clearly could not be built in sufficient numbers [in fact, only a single PAPA was built]. The Charlie SSGN was the first Soviet submarine to deploy submerged launch antiship missiles. In common with American submarines, and unique among Soviet combat nuclear submarines, the Charlie class had a single reactor and a single propeller shaft -all other Soviet submarine classes feature two reactors and two propellers. With only a single reactor (VM-4 type water-cooled), the Charlie-class was limited to a top speed of 24 knots, which was insufficient to keep pace with a 30-knot carrier battle group. The Charlie seemed to eliminate many of the problems inherent in the Echo design and concept of operations. It used targeting data from the first Soviet ocean surveillance satellites, which were intended to substitute for the vulnerable and range-limited maritime surveillance aircraft. In practice, the space-based ocean surveillance system did not live up to initial expectations, and the Charlie remained dependent on surveillance for target acquisition support. Although the shorter range of the SS-N-7 compared to the SS-N-3 required a closer approach to the target, it also reduced the flight time of the missile and eliminated the need for mid-course guidance. This eliminated the need for a guidance radar on the submarine, which allowed a fire and forget submerged launch. The Charlie-I was originally designed to carry the SS-N-9 anti-shipping cruise missile, which had been planned for the PAPA class. When the SS-N-9 missile was not ready in time for the Charlie-I class, the SS-N-7 [a modified version of the SS-N-2 Styx], was substituted. A total of 11 or 12 Charlie I submarines, carrying 8 SS-N-7s of approximately 30 mile range, were built between 1967 and 1972 at a rate of about two a year. The Charlie II provided the SS-N-9 armament originally planned for the Charlie I class, along with an improved fire control system. Six Charlie II submarines, each with 8 SS-N-9s of 60 mile range, followed between 1972 and 1980. The slower construction rate of the Charlie II suggested that the design was deemed less than satisfactory. Indeed, the Charlie SSGNs were by far the smallest class of the second generation of Soviet nuclear submarines which, also included 49 Victor SSNs and 76 Yankee/Delta SSBNs. All submarines of both classes had been discarded by 1994. Contrary to some expectations, there was no Charlie III class. K429 (a Charlie I class submarine) sank on 23 June 1983 in the Savannaya Bay in the Bering Sea. The boat was raised and returned to service. Unluckily, she sank again alongside the jetty on 13 September 1985. The incident led to the loss 16 lives and the imprisonment of the submarine commander. In January 1988 the Soviets leased a Charlie I to India, where she served until January 1991 as the Chakra. Some reports suggesting a that a second Charlie-class unit would be leased to India [possibly to be named the Chitra] were erroneous.

Specifications Project 670 / Charlie I

Project 670M / Charlie II

Displacement (tons):

4,000 surfaced 5,000 submerged

4,500 surfaced 5,400 submerged

Speed (kts):

23 knots dived 16 kts surfaced

Dimensions (m):

94.0 meters long 10.0 meters beam 8.0 meters draft

Propulsion

1 VM-5 pressurized-water nuclear reactor 1 steam turbine 20,000 shp 1 5-bladed propeller

102.0 meters long 10.0 meters beam 8.0 meters draft

Endurance: Crew

about 100

Armament:

8 SS-N-7 Starbright 6 21-in (533-mm) torpedo tubes (fwd) 12 torpedoes or 12 SS-N-15 Starfish

Electronics

8 SS-N-9 Siren 6 21-in (533-mm) torpedo tubes (fwd) 12 torpedoes or 12 SS-N-15 Starfish

Radar Snoop Tray Surface Search Sonar Shark Teeth bow-mounted periscopes

Class Listing Boat NO. Na me

Shipy ard Laid Down

Chronology Launc Comm. Stric hed ken

Notes

Project 670A("Skat" type), NATO code "Charlie I" K43

KS

--------- ---------

1968

------ 01/1988-01/1991 project 06709, ---to India (Chakra) 1991 in reserve

K87

KS

--------- ---------

1969

------ 1972 redesignated to K-212 ---1992 in reserve

K-

KS

--------- -------

1969

------ 1993 in reserve

25

-

---

----

K121

KS

--------- ---------

1969

------ 1993 in reserve ----

K313

KS

--------- ---------

1970

------ 12/1985 primary coolant leak, ---probably in reserve

K308

KS

--------- ---------

09/20/ 1970

------ 1993 in reserve ----

K320

KS

--------- ---------

09/15/ 1971

------ 01/18/1970 reactor accident ---under construction 1994 in reserve

K303

KS

--------- ---------

1971

------ 1995 in reserve ----

K325

KS

--------- ---------

1971

------ 1995 in reserve ----

K429

KS

--------- ---------

1972

1987 06/24/1983 sunk (later recovered) 09/13/1985 sunk again

K201

KS

--------- ---------

12/26/ 1972

------ 1994 in reserve ----

Project 670M("Skat-M" type), NATO code "Charlie II" K- Ber 452 kut

KS

--------- 1973 -

1974

------ 1989 named ---project P-670 converted 1994 in reserve

K458

KS

--------- 1975 -

1976

------ 1992 in reserve ----

K479

KS

--------- 1977 -

1978

------ 1993 in reserve ---in storage in Nerpa naval shipyard

K503

KS

--------- 1978 -

1979

------ 1994 in reserve ----

K508

KS

--------- 1979 -

1980

------ 1994 in reserve ----

K209

KS

--------- 1980 -

1982

------ 1994 in reserve ----

Project 661 Anchar / Papa A predecessor to the famous ALFA-class attack submarine, the Project 661 Anchar [Papa] was designed as an extremely fast anti-shipping cruise missile submarine. The Papa design included 10 SS-N-9 missiles in individual tubes forward of the sail, between the inner (pressure) hull and the outer hull. The US Navy was surprised in 1970 by the deployment of the Alfa-class attack submarine, whose 45 knot speed and 2000-2500 foot operating depth greatly surpased previous Soviet or American submarines. The Alfa used a high power density, liquid metal reactor plant which greatly increased her power-toweight and volume ratios. It also featured a titanium pressure hull which reduced the hull weight needed for extreme operating depths. The Papa SSGN appeared to incorporate similar design technologies for the antiship cruise missile mission. The K-162 was the world's fastest submarine, reportedly reaching a record speed of 44.7 knots on trials [causing signficant damage to topside equipment in the process]. The high speed of the design came at the price of excessive noisy and high construction costs. The Alfa did not enter production until the late 1970s, with only six units built, while only a single PAPA was ever deployed. Instead, the Soviets focused on building the more traditional submarines.

Specifications Displacement (tons):

5,200 surfaced 7,000 submerged

Speed (kts):

44.7 knots dived

Operating Depth

400 meters

Dimensions (m):

106.7 meters long 11.6 meters beam 8.0 meters draft

Propulsion

2 VM-5m pressurized-water nuclear reactors, 177.4 MWt 2 steam turbines; ??,000 shp 2 ?-bladed propellers

Endurance: Crew

82

Armament:

10 - SS-N-9 torpedo tubes

Electronics

Radar  Sonar  2 periscopes

Class Listing Boat N O.

K16 2

Shipya Nam Laid rd e Down

SV

12/28/19 63

Chronology Launche d

Comm.

Strick en

Notes

redesignated to K-222 09/30/1980 reactor 12/21/19 12/31/19 -------- accident 68 69 -1988 in reserve in storage in Severodvinsk

Project 949 Granit / Oscar I Project 949A Antey / Oscar II The Oscar-class nuclear-powered cruise missile attack submarine, which displaces more than 18,000 tons when under water, is one of Russia's largest and most capable submarines. As with earlier cruise-missile submarine, the Oscar was designed primarily to attack American aircraft carrier battle groups. As with other Russian submarines, the Oscar features a double hull -- and inner pressure hull and an outer hydrodynamic hull, with eight inches of rubber between them to muffle sounds. American submarines have a single pressure hull, with additional hydrodynamic fairings, such as the cap that encloses the bow sonar dome. The 3.5 meter separation between the inner and outter hulls on the Oscar provides significant reserve buoyancy, and improved survivability against conventional torpedoes. These large submarines are said to be slow to dive and maneuver, though they are credited with a submerged speed of about 30 knots - sufficient to keep pace with their targets. The improved Oscar II is about 10 meters longer than the Oscar I, possibly making room for a quieter propulsion system, and feature upgraded electronic systems. The Oscar II is also characterized by a substantially enlarged fin, which should improve underwater manueverability, as well as the substitution of the Oscar-I's four-bladed propeller with a [presumably] quiter sevenblade propeller. The Oscars are rather poorly characterized in the open literature, with substantial discrepancies in reported submerged displacement [the upper estimates are probably closer to the mark] and maximum submerged speed [reportedly classified intelligence estimates have tended upward over time. Considerable confusion also exists as to the names of some units. During the Cold War essentially no information was publicly available concerning the names of Soviet submarines, and with the end of the Cold War the Russian Navy has exibited an annoying tendency to rename ships [a very unAmerican practice]. And unlike the American practice, in which hull numbers are generally assigned in a consecutive numerical sequence which corresponds to the chronological sequence of construction, the pennant numbers assigned Russian submarines [eg, K-141] do not conform to an apparent set pattern. The submarine is equipped with two dozen SS-N-19 missiles with a range of 550kilometers -- three times as many anti-ship cruise missiles as earlier Charlie and Echo II class submarines. The missiles, which are launched while the submarine is submerged, are fired from tubes fixed at an angle of approximately 40 degrees. The tubes, arranged in two rows of twelve each, are covered by six hatches on each side of the sail, with each hatch covering a pair of tubes. The launchers are placed between the inner pressure hull and the outer hydrodynamic hull. The torpedo tubes fire both torpedoes and shorter range anti-ship missiles, and a combination of some two dozen weapons are carried.

The Project 949A submarines have a total of at least ten separate compartments, which can be sealed off from each other in the event of accidents. The compartments are numbered sequentially from fore to aft, with the two separate reactor compartments numbered V and V-bis [which is accounts for the fact that there are ten compartments, though the numbers only run through nine]. I - Torpedo room II - Control Room III - Combat stations and radio room IV - Living Quarters V and V-bis - Reactors VI - propulsion engineering VII - main propulsion turbines VIII - main propulsion turbines IX - electric motors Access hatches are believed to be located in the 4th and 9th compartments. In common with the larger Typhoon-class ballistic missile submarine, the Oscar-class boats are reported to have an emergency crew escape capsule located in the sail. In the 1980s the Rubin Design Bureau was responsible for developing a number of third generation nuclear submarines with cruise missiles, including Projects 949 ("Granit", "Oscar I") and 949A ("Antey", "Oscar II"). The Bureau took the lead in using naval cruise missiles, designing the first cruise missile nuclear submarine -- Project 659 ("Echo I"), then Project 675 ("Echo II") and related modifications. To manage the impact of its resource problems, the Russian Navy, in the early 1990’s, made a series of hard choices aimed at preserving its core submarine force capabilities. These included early retirements of older and less capable units, strict controls on operating tempo, and focused maintenance on its best submarines. The first Oscar I units were decommissioned in 1996, though the Russian Navy continued to invest in new construction. In the late 1990s it completed several new submarines of the larger third generation Oscar II SSGN. Considering the importance of the Oscar II submarines for the Russian Navy, the level of confusion concerning the designations and status of the units of this class verges on the astonishing. There is almost complete disagreement among all authoritative sources concerning the correlation between pennant number, name, construction sequence and current status. Allowing for the unavoidable uncertainties inherent in assigning "commissioning" dates, most sources are in general agreement as to the unit chronology and pennant number chronological sequence of the first ten units, through K-141 Kursk. There is however, rather general disagreement among sources as to the names associated with these units, and the status of particular units. All sources agree that at least eleven of the Oscar II submarines were built between 1985 and 1999 at the Sevmash yard in Severodvinsk. The status of a twelfth Oscar-II is somewhat uncertain, as some sources suggest it was comissioned in late 1999, while most agree that outfitting was suspended after it was launched [sometime in the 1998-1999

timeframe]. Some Western sources suggest that construction was suspended on a thirteenth unit, and that as many as 15 units of the Oscar II class were planned, but Russian sources maintain that the Oscar-II class was never intended to consist of more than twelve vessels. A fourth-generation follow-on to the Oscar was planned, but reduced defense spending forced the cancellation of the project. Sources generally agree that at least two and possibly as many as three of the initial nine Oscar II units were inactivated in the late 1990s, and as of mid-2000 were laid up awaiting disposal. Considerable confusion surrounds the identity of the third and fourth units -- Krasnoyarsk] was reportedly deactivated in 1998, but sources differ as to whether this name was assigned to K-119 or K-173. The active Northern Fleet units are homeported at the Zapadnaya Litsa base (Bolshaya Lopatka). The disposition of units between the Northern and Pacific Fleets is uncertain. As of September 1997 Bellona placed six units in the Northern Fleet, four in the Pacific. As of September 2000 the warships1.com analysis also placed 4 units in the Pacific Fleet, and the remaining 6 in the Northern Fleet. However, World Navies Today reports that ten active units [as of late 2000] are evenly divided between the two fleets [but the unit list seems rather unreliable, casting doubt on this assessment]. The two sources appear to disagree on the location of K-119 Voronezh. On 26 January 1998 a moored nuclear-powered Oscar II submarine suffered a cooling system accident. During routine tests aboard a cooling system pipe broke, releasing ammonia and nitrogen gas into the compartment. A total of 5 crew members were injured, one of whom, a Captain of the 3rd Rank, died two days later. The Oscar II submarine was reportedly the K-512 St.Georgy Pobeditel [formerly named Tomsk]. This eleventh unit of the 'Oscar II' SSGN class had been launched in July 1995 despite irregular materiel and component delivery problems. In 1994 an Oscar submarine conducted operations off the East Coast of the United States. In July 1997 when the Oscar II submarine K-442 Chelyabinsk [aka Pskov] shadowed several US aircraft carriers off Washington state. The Tomsk transitted to the Pacific under ice after being commissioned on 28 February 1997, and arrived at PetropavlovskKamchatskiy on 24 September 1998. This brought the Pacific Fleet class inventory to seven, with four others in the Northern Fleet. In February 1999 an Oscar-class submarine was observed monitoring a NATO exercise off the coast of Norway. In August 1999 NATO sonar detected the presence in Western Atlantic waters of a Russian Oscar class submarine belonging to the northern fleet, based in the Arctic ports. In the mid-1999 an Oscar II-class submarine sailed from northern Russia to the Mediterranean, the first Russian SSGN patrol in the Mediterranean in a decade. It then sailed on to areas off the eastern United States. In early September 1999 the crew of the Jose Maria Pastor, a fishing trawler registered in Almeria [southeastern Spain] reportedly snagged an Oscar submarine in its nets. The incident occured some 27 miles (50 kilometers) from the Tarifa coast (Cadiz Province), and continued for over half an hour before the submarine broke

free. Another Oscar II deployed from the Russian Far East, sailing to the area around Hawaii before arriving in waters off San Diego by October 1999. It reportedly spent a week following the aircraft carrier USS John C. Stennis and the amphibious landing ship Essex.

K-141 Kursk On or about 12 August 2000, the tenth unit of the Oscar-II class, the K-141 Kursk, sank about 100 miles from the Russian port of Murmansk. At the time the boat was participating in the fleet's major summer exercises, involving about 30 other vessels. The Kursk apparently sank quickly, and did not launch distress buoys. The submarine was not carrying any nuclear weapons at the time, and there was apparently no immediate danger of radiation leaks. Considerable confusion surrounded initial reports, though apparently the Kursk shut down its two nuclear reactors after it was crippled. Although Russian Navy commander Adm. Vladimir Kuroyodev stated that there were "signs of a big and serious collision," subsequent reports cast doubt that the sub was damaged in a collision. The US Department of Defense stated that there was " no indication that a US vessel was involved in this accident." By 15 August it was generally believed that the Kursk had been damaged by an explosion on board, probably in the torpedo room. Initial reports suggested that at least some of the crew were alive and communicating through rhythmic tapping on the hull. Rescue submarines that rushed to the Kursk reportedly found it damaged but resting upright on the seabed, at a depth variously reported as between 350 feet and 500 feet of water. Subsequent reports suggested that the submarine was listing, perhaps as much as sixty degrees. According to initial reports, as of Monday 14 August 2000 at least one rescue craft, the Kolokol, was said to be feeding power and oxygen to the Kursk. Communication links with the boat's captain, Gennady Lyachin, were reportedly restored after a day of radio silence. However, subsequent reports indicated that these initial reports were incorrect, and overly optimistic. Admiral Kuroyedov initially expressed doubts about the possiblity of rescuing the crew, stating "the chances for a positive outcome are not very high." The Russians had two India-class rescue submarines, each of which carried a pair of small rescue submarines which could reach a depth of 2,275 feet. However, these submarines and their rescue capabilities were apparently discarded by the Russians in 1995 as a cost-savings measure. Rescue efforts centered on attempts to attach equipment to provide oxygen and restore electric power to the submarine. As of 15 August a first attempt to lower a diving bell to the submarine had failed, and a second attempt was launched soon thereafter. The two attempts on Tuesday to reach the Kursk were frustrated by of poor underwater visibility and 12-foot high waves. Rescue workers failed in efforts to maneuver a robotic remotedly operated vehicle onto an emergency hatch on the submarine. By Wednesday, while Russian experts were still optimistic about the rescue operation, Russian President Putin termed the situation with wrecked sub "critical". The weather had worsened in the Barents Sea, while the Bester capsule with divers aboard was used for the first time Rrescue ships tried twice more to lower a diving bell to dock with the

Kursk, but each time the operations had to be aborted because of rough seas, strong currents, and poor underwater visibility. Rescue efforts continued despite the fact that one of the three rescue capsules used to reach the stranded sub was damaged in the storm. The Russian military consulted NATO experts on submarine rescue, and Russia asked Britain and Norway to help the rescue effort. Britain sent three aircraft with crew and equipment, and the first plane loaded with a British rescue vessel landed in Norway late Wednesday [Moscow time]. The British mini-submarine may be transported to Russia by Saturday. On Thursday 17 August it was reported that US surveillance ships in the area at the time of the accident heard two explosions on 12 August, the second much stronger than the first. The Russian navy was reported to be studying video footage showing massive damage to the first and second compartments in the submarine's bow. A Navy spokesman said the video showed extensive damage from the top to the back fin. The periscope was also still up, indicating the ship sank so fast the crew did not have time to react. Russia's Deputy Prime Minister Ilya Klebanov said films taken of the Kursk indicated extensive damage to the ship's bow that he said was caused by a collision with an unknown object. By Friday it was reported that the submarine was lying at an angle of no more than 20 degrees from vertical, rather than the 60 degress previously reported, and at a depth of a little more than 100 meters. The depth and the angle are were said to be well within the operating limits of th British LR5 rescue craft. It was initially estimated that the air on the K-141 Kursk submarine would run out by Friday 18 August 2000. As of Friday it was officially estimated it could last another five days. Contrary to most news reports, the problem was not a lack of oxygen for the crew to breath in, but rather the buildup of the carbon dioxide that they would breath out. Over time, this carbon dioxide would build up to a level that would kill any crew members who survived the initial accident. The oxygen limit is about 0.1 atm and the Carbon dioxide limit is time dependent, but somewhere between 0.03 and 0.06 atm. Respiration produces (roughly) 1 molecule of carbon dioxide for each molecule of oxygen consumed. This suggests that, starting with 0.21 atm of oxygen, the oxygen partial pressure will still be 0.15 atm even when 0.06 atm of carbon dioxide is present. [see the NOAA Diving Manual for details]. While some Russian Navy officials maintained that some crew members remained alive and were sending an SOS message by banging against the submarine's hull, other officials said there had been no communication and that the crew might already be dead. On 21 August Chief of staff of the Russian Northern Fleet Mikhail Motsak pronounced the Kursk flooded and its whole crew dead. Admiral Motsak said a Norwegian-led team of divers was videotaping the interior of the rear compartment after successfully breaking in through damaged escape hatches. On 01 September 2000 an agreement was reached on the technical and organizational aspects of the international effort to lift to the surface the bodies of the crewmen of the Kursk. The Norwegian Stolt Offshore company received blueprints representatives of the

naval design center which designed the sunken submarine that showed where deep water frogmen may enter the boat. A team of international and Russian divers planned to cut holes in the Kursk’s hull to pull out the remains of the 118 seamen who died. The operation was scheduled to begin in October 2000. There was no chance of quickly salvaging the Kursk submarine, since September is the month when storms start raging in the Barents Sea, which would make such impossible. At best the salvaging operation could be carried in 2001. Neither the Russian submarine base at Vidyaevo, nor any western base have hoists capable of salvaging such a large vessel the Kursk submarine, or even moving it to a shallow place closer to the coast. It would take several months only to build such a device. Another priority on the agenda is the salvaging of the submarine and taking it to shallow waters. The Norwegian Stalled Offshore Company has given its consent to participate in the salvage effort. On 06 September 2000 Russian President Vladimir Putin was reported to have said that the 118 sailors aboard the submarine Kursk probably died quickly after it sank, and that they never sent any signals from the distressed sub after it went down. At the time of the accident, conflicting reports from some Russian naval officials indicated that survivors were tapping on the ship's hull. But Putin said that the signals came from "a mechanical device on board" that went off automatically. There are several versions of the reasons for the disaster. According to Vice-premier Ilya Klebanov, the first version is that of an underwater collision with a foreign vessel. Ilya Klebanov who heads the commission to investigate the case described as the second version a possibility that the submarine hit a German mine left over from the time of the Second World War. The third version, the Vice-premier believed, could be an emergency situation in the submarine's torpedo compartment. According to Ilya Klebanov, the majority of the crew died during the first seconds of the disaster.

Specifications Displacement (tons):

949 (Oscar-I)

949A (Oscar-II)

12,500 surfaced

13,400 - 14,700 surfaced

15,500 - 22,500 submerged

16,400 - 24,000 submerged

Speed (kts):

32 knots dived 16 kts surfaced

32 knots dived 16 kts surfaced

Dimensions (m):

143.0 meters long 18.2 meters beam (20.1 with stabilizers) 9.0 meters draft

154.0 meters long 18.2 meters beam 9.0 meters draft

Propulsion

2 VM-5 190 MWt pressurized-water nuclear reactors (OK-650b) 2 steam turbines - 90,000 shp

Propulsion

2 4-bladed propellers

Endurance:

50 days

Diving depth:

300-600 meters [by various estimates]

Crew :

94 total

Armament:

24 - SS-N-19 / P-700 Granit

2 7-bladed propellers

24 - torpedoes/tube-launched weapons 4 - 533 mm tubes - SS-N-15 Starfish / 82-P missiles or torpedoes 4 - 650 mm tubes - SS-N-16 Stallion / 85-P missiles or torpedoes Electronics

Radar Snoop Pair or Snoop Half Surface Search Rim Hat intercept array Sonar Shark Gill (MGK-503) hull mounted Shark Rib flank array Mouse Roar MG-519 Hull mounted Pelamida towed array 2 periscopes

Class Listing Boat NO Name .

Chronology Ship Fle yard et Laid Launc Com Down hed m.

Stric ken

Notes

Project 949 ("Granit" type), NATO code "Oscar I" 1 K52 5

Arkhangels SY k 402

NO 1978 R

04/**/ 1982 1980

1996

12/30/80 named "Minsky Komsomolets" 1991 renamed 1996 deactivated 2000 to be dismantled at Sevmash

2 K20 6

Murmansk

NO 1980? 12/**/ 1983 R 1982

1996

1991 named 1996 deactivated 2000 to be dismantled at Sevmash

SY 402

Project 949A ("Antey" type), NATO code "Oscar II" 1 K14 8

Orenburg

SY 402

NO ------R ---

08/**/ 07/**/ ?? 1985 1986 1998 12/**/ 1986

ex-Krasnodar [name as of 1995] ex-Vologda 2000 probably active 2000 laid up awaiting disposal ??

2 K13 2

Irkutsk

SY 402

PA ------C ---

**/**/ 1986 03/**/ 1986

**/**/ ? 1987 1998 01/**/ 1987

(name also reported as "Belgorod") 2000 in reserve 2000 laid up awaiting disposal ?

3 K11 9

Voronezh

SY 402

NO ------R --PA C?

**/**/ 1986 12/**/ 1987

**/**/ 1988 12/**/ 1988

(name also reported as "Krasnoyarsk" "Tambov" or "Chel'yabinsk") 2000 active

4 K17 3

Krasnoyars SY k 402

NO ------R ---

**/**/ 1987 01/**/ 1989

**/**/ ? 1988 1997 12/**/ -8 1989

(name also reported as "Veronesh") (name mis-reported as "Chelyabinsk") 1997-8 deactivated 2000 laid up awaiting disposal ?

5 K41 0

Smolensk

NO ------R ---

**/**/ 1988 12/**/ 1989

**/**/ 1990 12/**/ 1990

2000 active

SY 402

6 K44 2

Chelyabins SY k 402

PA ------C ---

**/**/ 1989 01/**/ 1990

12/29/ 1990 01/**/ 1991

(name also reported as "Pskov") (name mis-reported as "Tomsk") 2000 active

7 K45 6

Viliuczinsk SY 402

PA ------C ---

**/**/ 1990 12/**/ 1991

**/**/ 1991 11/**/ 1992

(ex-"Kasatka", possibly "Tambov") 09/**/1993 to Pacific Fleet 2000 active

8 K26 6

Orel

SY 402

NO ------R ---

01/**/ 1992 05/22/ 1992

12/**/ 1992 01/**/ 1993

(ex-"Severodvinsk") 2000 active

9 K18 6

Omsk

SY 402

NO ------R ---

05/08/ 10/27/ 1993 1993 12/15/ 1993

1 K0 14 1

Kursk

SY 402

NO 1992 R

05/**/ 10/**/ 8/12/ 1994 1994 2000 12/30/ 1994 01/20/ 1995

1 K1 51 2

St.Georgy Pobeditel

SY 402

PA ------C ---

07/18/ 1995 07/18/ 1996

1 K2 53 0

Belgorod

SY 402

---------

05/**/ ???? 1998 08/**/ 1999

(name also reported as "Pskov") 2000 construction suspended??

1 K3 13 9

Pskov?

SY 402

????

????

[?? construction suspended ??]

1 K4 __ _

SY 402

????

------- -----------

[?? cancelled ??]

1 K-

SY

????

------- -------

[?? cancelled ??]

02/28/ 1997 12/31/ 1997

---------

(possibly renamed "Petropavlosk Kamchatsky") 2000 active

(ex-"Tomsk") 08/1997 operational 01/26/1998 cooling system accident 2000 active

5 __ _

402

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