Gemini 11 Press Kit

NAIIONAL AERCJNAUTICS AND SPACE ADMlt&'fR4lflON

WASHINGTON. D C

20546

wc) 2-41

FOR RELEASE: FRIDAY P.M. September 2, 1966

Y

RELEASE NO:

66-226

(To be launched no e a r l i e r than Sept. 9, 1966)

GPO PRICE

$

CFSTl PRICE(S) $

8/24/66

Hard copy (HC) Microfiche ff 653 July 65

(MF)

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W O 2-41 5 5 TELS' W O 3-6925

WASHINGTON, D.C. 20546

September 2, 1966 RELEASE NO:

66-226 THREE-DAY GEMINI 11 M I S S I O N SET

The National Aeronautics and Space Administration w i l l launch Gemini 11 and i t s Agena Target Vehicle no e a r l i e r than Sept. 9 from Kennedy Space Center, Fla. The three-day mission w i l l include rendezvous and docking with t h e Agena during t h e s p a c e c r a f t ' s i n i t i a l r e v o l u t i o n , use of a power t o o l t o p e r f o m work tasks during e x t r a v e h i c u l a r a c t i v i t y , and maneuvering the s p a c e c r a f t t o an apogee o f 865 m i l e s . Other a c t i v i t i e s t o be performed as time and p r o p e l l a n t

a l l o w are station-keeping by t e t h e r i n g the s p a c e c r a f t t o the

Agena, completion o f 12 experiments, some o f which w i l l be conducted during a more than two-hour standup EVA, and a d d i t i o n a l docking p r a c t i c e . The c o n t r o l l e d r e e n t r y w i l l be f u l l y automatic.

Reentry

c o n t r o l commands w i l l be computed and executed by t h e onboard systerns.

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11 command p i l o t is Charles ( P e t e ) Conrad.

is Richard F. Gordon.

Pilot

Backup command p i l o t i s N e i l A. Arm-

strong, and W i l l i a m A. Anders I s backup p i l o t . Conrad, a Navy commander, was p i l o t on Gemini eight-day mission of Aug. 21-29, 1965.

has n o t y e t flown i n space.

5, t h e

Navy L t . Cdr. Gordon

Amstrong, a c i v i l i a n , was

command p i l o t on Gemini 8, the first space docking mission. Anders i s an A i r Force c a p t a i n and has n o t y e t made a space flight.

Launch time f o r the Gemini Agena Target Vehicle (GATV) I s 8:48

a.m. EDT.

Gemini 11 is scheduled t o l i f t off a t

10:25 a.m. EDT. The Agena w i l l be launched i n t o a 185-mile c i r c u l a r o r b i t by a n Atlas Standard Launch Vehicle (ASLV). be launched

Gemini 11 w i l l

97 minutes l a t e r i n t o a 100 by 174-mile orbit

fromt which i t w i l l attempt a f i r s t - r e v o l u t i o n rendezvous with the Agena.

Docking i s programmed t o occur over the United

States n e a r t h e end o f the first spacecraft r e v o l u t i o n . J u s t before the start of Gemini 11's second ciay I n space, Astronaut Gordon w i l l begin his u m b i l i c a l EVA over Hawaii

a t 24:08 hours ground elapsed t i m e (GET).

He w i l l be l i n k e d

t o the s p a c e c r a f t by a 3O-fo0t u m b i l i c a l .

H i s extravehicular

a c t i v i t y w i l l include: -more -

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r e t r i e v i n g t h e n u c l e a r emulsion experiment ( S - 9 )

from the o u t s i d e of the s p a c e c r a f t a d a p t e r s e c t i o n

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a t t a c h i n g the Agena t e t h e r t o the s p a c e c r a f t doeking

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performing t h e power t o o l e v a l u a t i o n (D-16)

bar

r e t r i e v i n g t h e hand-held maneuvering u n i t ("MU) and

t h e Apollo camera from i n s i d e the a d a p t e r

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e v a l u a t i n g t h e "Mu.

Following the second s l e e p period, t h e Agena primary p r o p u l s i o n system (PPS) w i l l "kick" t h e s p a c e c r a f t i n t o an 865-mile apogee.

The PPS maneuver, a 943-feet-per-second

posigrade burn, t a k e s p l a c e over t h e Canary I s l a n d s a t 40:32 GET.

The Gemini-Agena combination reaches apogee about 51

minutes l a t e r over Carnarvon. Gemini 11 w i l l remain in t h e 185 by 865-mile o r b i t for t h e n e x t two r e v o l u t i o n s .

At

43:56 GET t h e PPS engine w i l l

f i r e f o r the second time, a 943 f . p . s .

r e t r o g r a d e burn that

r e s t o r e s the o r b i t t o 185 m i l e s c i r c u l a r . A t about 46:00 GET t h e second e x t r a v e h i c u l a r a c t i v i t y ,

a 140-minute standup, begins over Tananarive. H a w a i i i n t h e 30th r e v o l u t i o n a t 48:20 GET. -more -

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It ends over

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In the 3lst revolution a t 49:50 @ET the spacecraft w i l l t r a n s l a t e t o about 30 degrees off the l o c a l v e r t i c a l , the Agena PPS engine polnting toward the Earth.

The spacecraft

w i l l undock and back off t o the limit of the tether (100 feet) above the Agena in a nose-down a t t i t u d e .

The Agena w i l l

be s t a b i l i z e d i n the engine-down position w i t h i t s longitud i n a l center-line pointing toward the center of the Earth.

Gemini 11 w i l l s t a b i l i z e itself with i t s longitudinal axis aimed through the Agena toward the Earth’s center. A t t h i s time the spacecraft o r b i t a l a t t i t u d e and

maneuvering system (OAIVIS) and the Agena a t t i t u d e control system (ACS) w i l l be deactivated.

I f the spacecraft has

been positioned properly and if the r e l a t i v e v e l o c i t i e s between the two vehicles do not exceed .2 feet-per-second,

a s t a t i o n keeping, gravity gradient s t a b i l i z e d position w i l l have been established to r e t a i n both vehicles I n t h e i r relative positions and a t t i t u d e s as they c i r c l e the Earth. I f t h i s procedure proves impractical, a slow r o t a t i o n

o f the tethered Gemini 11 and Agena w i l l be i n i t i a t e d .

Centrifugal force is expected t o maintain the tautness of the t e t h e r , keeping the vehicles a t a controlled distance f’rom each other and minlmizlng the amount of propellant

required f o r the station-keeping maneuvers practiced on previous G e m i n i missions. -more -

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The t e t h e r exercise w i l l be completed a t 53:OO GET i n t h e 33rd revolution. As Gemini 11 passes over the e a s t coast of Africa on i t s

34th revolution a retrograde maneuver w i l l lower the o r b i t perigee i n preparation f o r r e t r o f i r e .

Magnitude of the

maneuver w i l l be determined by the amount of OAMS propellant left.

Scheduled time of r e t r o f i r e i s 70:40 GET. Reentry w i l l be controlled by the spacecraft onboard

computer i n the automatic mode.

The computer and the i n e r t i a l

guidance system ( I G S ) feed bank-angle commands i n t o the a t t i t u d e control and maneuver electronics (ACME) which cont r o l the reentry thrusters. The crew w i l l monitor the f l i g h t d i r e c t o r indicator (PDI) needles during the automatic reentry but w i l l n o t make manual steering maneuvers.

Gemini 11 w i l l be the first

American space f l i g h t t o employ automatic guided reentry. Previous missions have used manual closed-loop guided o r unguided b a l l i s t i c reentry techniques. Splashdown w i l l occur approximately 30 minutes a f t e r r e t r o f i r e and w i l l be i n the West Atlantic recovery area

45-1, some 725 miles east of Cape Kennedy. -more-

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After splashdown and recovery, f l i g h t controllers will command a series of Agena maneuvers to evaluate the vehicle's propulsion system.

The Agena then w i l l be transferred t o

a parking orbit f o r possible use as a passive target on f'uture manned missions.

(END OF GENERAL RELEASE; BACKGROUND INFO€?MATION POLLOWS)

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PREFLIGHT ACTIVITIES AND INTEGRATED COUNTDOWN Gemini f l i g h t s are developed by t h e NASA Manned Spacecraft Cenber (MSC); Houston, Texas, u n d e r t h e d i r e c t i o n of t h e NASA Headquarters Office of Manned Space F l i g h t i n Washington, D.C. The NASA John F. Kennedy Space Center ( K S C ) , Florida, has overa l l r e s p o n s i b i l i t y f o r p r e f l i g h t t e s t i n g , checkout and launching of t h e Gemini and Atlas/Agena' vehicles f o r Gemini missions. After launch, c o n t m l of t h e f l i g h t i s t h e r e s p o n s i b i l i t y of t h e M i s s i o n Control Center, MSC. Gemini 11 t i m e t a b l e a t Kennedy Space Center: The Gemini launch v e h i c l e (GLV) a r r i v e d J u l y 11 ( f i r s t s t a g e ) and the second stage a r r i v e d J u l y 13.

GLV was e r e c t e d a t Launch Complex 19 J u l y 22.

Gemini 11 s p a c e c r a f t a r r i v e d a t KSC J u l y 6 f o r r e c e i v i n g i n s p e c t i o n , ordnance i n s t a l l a t i o n , and assembly checks a t Merritt Island

.

8.

Atlas standard launch vehicle ASLV) a r r i v e d J u l y 19 and was e r e c t e d on Launch Complex 1 4 J u l y 2 Gemini Agena target vehi'cle (GATV) a r r i v e d J u l y 15, t h e t a r get docking adapter p r e c e d i n g it J u l y 13. GATV, docking adapter, and s p a c e c r a f t underwent "timber tower" t e s t s a t KSC Radio Frequency Systems Test F a c i l i t y July 2 5 .

Docking compatability checks conducted J u l y 2 5 . Spacecraft and launch vehicle prernate t e s t s conducted August

5 a t Complex 19 w i t h e l e c t r i c a l mating August 5.

Mechanical mating check took p l a c e on August 24, simultaneous launch demonstration was t o be h e l d August 31, and t h e simulatgd f l i g h t scheduled on September 1. Gemini countdown i s a combination of countdowns involving Gemini 11 and Agena 11 launch vehicles, t h e s p a c e c r a f t and target v e h i c l e , t h e crew, Houston Mission Control and t h e worldwide t r a c k i n g network, t h e Eastern T e s t Range, and t h e Radio-Command Guidance System. L i f t o f f f o r t h e t a r g e t vehicle i s scheduled f o r t h e 95minute mark i n t h e simultaneous count. The Gemini s p a c e c r a f t w i l l be launched approximately 97 minutes and 30 seconds l a t e r , depending on t h e exact l o c a t i o n and performance of t h e o r b i t i n g Agena. A b u i l t - i n hold i s scheduled a t T-3 m i n u t e s t o a d j u s t Gemini l i f t o f f t i m e t o coincide w i t h Agena 11's f i r s t pass over t h e Cape. After t h e launch sequence adjustments are computed, t h e count w i l l resume. -more-

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Launch Vehicle Countdown

Time

Gemini

Atlas -Agena

F-3 days F-1 day T-720 minutes T-615 minutes

S t a r t pre-count S t a r t mid-count GLV p r o p e l l a n t loading

Countdown

T-390 m i n u t e s T-300 minutes

T-255 T-240 T-235 T-195 T-185

minutes minutes minutes minutes minutes

T-135 minutes T-125 minutes T-120 minutes T-119 minutes T-115 minutes T-100 minutes T-95 minutes

"-86 minutes

m$nutes ~inutes minutes min., 1 s e c T-04 seconds T-0 seconds T+2 minutes, 36 seconds

T-70 T-55 T-20 T-13

T4-5 :36

T+5 :56 T+6 :40

Begin terminal count Complete p r o p e l l a n t loading Back-up f l i g h t crew r e p o r t s t o t h e 100-foot l e v e l o f the White Room t o p a r t i c i p a t e i n f i n a l f l i g h t preparation. Beg i n terminal countdown, P i l o t s t ready room, 100-foot l e v e l of White Room and crew quarters manned and made ready f o r prime crew. Medical examination S t a r t tower removal Eat C r e w leaves quarters C r e w a r r i v e s a t ready room on Pad 16.

Purging of s u i t begins Crew leaves ready room F l i g h t crew t o Complex 19 C r e w a r r i v e s a t 100-foot l e v e l C r e w e n t e r s spacecraft Close s p a c e c r a f t hatches

L i f t o rf

Insertion i n t o orbit White Room evacuation Begin e r e c t o r lowering Spacecraft OAMS s t a t i c f i r i n g B u i l t - i n hold GLV i g n i t i o n L i f t off Booster engine cutoff (BECO) Second stage engine c u t o f f (SECO) Spacecraft-launch v e h i c l e separation Insertion into o r b i t -more-

-9Reentry (Elapsed Time from Gemini L i f t - o f f ) Time -

70:@

Retrofire

70 :56 i o :59

Blackout ended Drogue chute deployed (50,000 f e e t ) Main chute f u l l y deployed (9,000 f e e t ) Spacecraft landing

71 :00 71 :05

MISS I ON DESCRIPTION Mission information presented i n t h i s p r e s s k i t is based on a normal mission. Plans may be a l t e r e d p r i o r t o o r during f l i g h t t o meet changing conditions. A l l o r b i t a l parameters i n t h i s s e c t i o n are i n s t a t u t e miles. To convert these f i g u r e s t o n a u t i c a l miles, m u l t i p l y by .87, t o k i l o m e t e r s m u l t i p l y by 1.61.

Launch Launch Times

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Launch Windows

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Atlas/Agena 8:48 a.m. Em, Launch Complex 14 Gemini 11 10:25 a.m. EIYT, Launch Complex 19 (These launch times were e s t a b l i s h e d t o g i v e optimum Lighting conditions f o r rendezvous )

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-- Gemini

.

11 i s scheduled f o r a n "on time" launch t o achieve rendezvous i n t h e f i r s t s p a c e c r a f t revolution. That is, t h e pane i n t h e launch window allows no s i g n i f i c a n t delay beyond the nominal launch t i m e some 97 minutes a f t e r Agena l i f t o f f . A window i s a v a i l a b l e t h e f i r s t day a f t e r Agena l i f t o f f , b u t probably w i l l not be used because of r e c y c l e problems and a g r e a t e r advantage i n second-day o p p o r t u n i t i e s . Two windows are a v a i l a b l e t h e second day a f t e r Agena l i f t o f f . They a r e a t 7:26 a.m. Em and 9:O2 a.m. EDT based on a nominal Agena lifto f f . Single windows are a v a i l a b l e t h e t h i r d and f o u r t h days a f t e r Agena l i f t o f f , a t 7:32 and 7:38 a.m. Em r e s p e c t i v e l y .

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Each of t h e Gemini launch windows can b e extended to permit rendezvous i n a l a t e r r e v o l u t i o n . Since a rendezvous i n t h e f i r s t r e v o l u t i o n i s d e s i r e d f o r t h i s mission, however, thc windows probably w i l l not be opened beyond t h e f i r s t pane as long as p r a c t i c a l t o t h e success of t h e o v e r a l l mission.

e

Azimuth

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Atlas/Agena w i l l be launched along a n 82.0-degree azimuth east of n o r t h . Gemini 11 w i l l b e launched along a 100.5-degree azimuth e a s t of north. This azimuth w i l l be biased from t h e 96.918-degree p a r a l l e l v a l u e s o t h a t a small amount of Gemini Launch Vehicle (GLV) yaw s t e e r i n g i n t h e second stage w i l l p l a c e t h e s p a c e c r a f t i n t h e Agena p l a n e a t rendezvous and t h u s e l i m i n a t e t h e n e c e s s i t y of a plane change. E q u a t o r i a l i n c l i n a t i o n f o r both v e h i c l e s w i l l b e 28.87 degrees.

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IVAR ( I n s e r t i o n a l Velocity Adjustment Routine) Some 20 seconds a f t e r t h e GLV second stage c u t s off (SECO) t h e s p a c e c r a f t w i l l s e p a r a t e from it by f i r i n g two a f t t h r u s t e r s o f t h e o r b i t a l a t t i t u d e and maneuvering system (OAMS). T h i s normally 30 feet-per-second maneuver w i l l g i v e the s p a c e c r a f t an i n s e r t i o n v e l o c i t y of 25,749 f p s and p l a c e i t i n a n o r b i t 100by-174 miles with p o s i t i o n about 246 miles

behind Agena a t a c l o s i n g r a t e of 858.3 f p s . Rendezvous

Terminal Phase I n i t i a t e ( T P I ) -- Ninety seconds before f i r s t s p a c e c r a f t apogee (00 :49 :43 GET) t h e f i r s t maneuver i n t h e rendezvous sequence occurs. Range t o t h e Agena i s about 20.5 m i l e s and t h e s p a c e c r a f t i s about seven minutes i n t o darkness. It i s p i t c h e d up t o 3.1 degrees above t h e l o c a l h o r i z o n t a l and a d e l t a V o f 131.2 f p s p o s i rade i s i n i t i a t e d by t h e a f t t h r u s t e r s $over Carnarvon). I n t e r m e d i a t e Corrections -- Agena w i l l t r a v e l t h T O U g h a c e n t r a l a n g l e of 120 degrees from T P I t o t e r m i n a l phase f i n a l . Two i n t e r m e d i a t e s p a c e c r a f t maneuvers are scheduled during t h i s period. These c o r r e c t i o n s are nominally a t 12-minute i n t e r v a l s a t c e n t r a l angles of 72 and 24 degrees from TPF. The f i r s t i s nominally z e r o , t h e second 2 f p s posigrade. -more-

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The v e l o c i t y matching maneuver Terminal Phase F i n a l (TPF) t h e o r e t i c a l l y i s 25.5 f p s . However, t h e command p i l o t w i l l c o n t r o l the f i n a l approach by semi-bptical techniques, and a d d i t i o n a l p r o p e l l a n t beyond t h e t h e o r e t i c a l amount may be necessary. T h i s posigrade "braking" maneuver should occur a t 01:19:52 GET (over Hawaii),.

Docking; Docking w i l l be performed by t h e command p i l o t a t about Ol:3O:OO GET i n d a y l i g h t over t h e United States. Subsequent p r a c t i c e dockings w i l l b e executed according t o t h e crew's det e r m i n a t i o n o f time a v a i l a b l e , b u t i n g e n e r a l a t l e a s t one dayt i m e and one nighttime docking w i l l be scheduled. Extravehicular A c t i v i t y The f i r s t e x t r a v e h i c u l a r a c t i v i t y programmed f o r the p i l o t i s scheduled t o begin a t 23:50 GET over H a w a i i . It w i l l be performed on a 3O-foot u m b i l i c a l and i s planned nominally f o r lo7 minutes. Upon opening the hatch, t h e p i l o t w i l l raise the handr a i l on t h e adapter s e c t i o n and w i l l r o u t e t h e " M U p r o p e l l a n t u m b i l i c a l under the h a n d r a i l toward t h e n i t r o g e n valve f i t t i n g . He w i l l i n s t a l l the 16m EVA motion p i c t u r e camera i n i t s b r a c k e t j u s t behind h i s hatch and w i l l a t t a c h t h e EVA Hasselblad camera t o a Velcro p a t c h on the e x t r a v e h i c u l a r l i f e support system (ELSS) c h e s t pack.

Egressing t h e s p a c e c r a f t , he w i l l work h i s way t o t h e Agena Target Docking Adapter, behind which is s t o r e d the 100-foot Dacron t e t h e r t o l i n k Agena and Gemini 11. He w i l l withdraw the spacec r a f t end of t h e tether from t h e s t o r a g e bag and loop it over t h e s p a c e c r a f t docking b a r , t i g h t e n i n g a clamp t o hold t h e t e t h e r i n p l a c e . He w i l l i n s t a l l t h e docking bar m i r r o r , t h e n r e t u r n t o the cabin area t o change f i l m i n t h e 16m camera and remount i t s o t h e l e n s p o i n t s back toward t h e Power Tool Evaluation e x p e r i ment worksite on the adapter. He w i l l move back along t h e handr a i l , plug the quick-disconnect f i t t i n g on one end of the HHMU u m b i l i c a l i n t o t h e n i t r o g e n valve f i t t i n g , and w i l l commence t h e D-16 experiment. The experiment sequence follows: grasp h a n d r a i l r i g h t knee t e t h e r t o h a n d r a i l ; grasp t o o l box handle, lock, and p u l l t o o l box handle upward from well u n t i l l o c k engages; open t o o l box and check o u t power t o o l ;

and a t t a c h

release positive u s i n g power t o o l , t i g h t e n instrumented b o l t f o r five seconds; r e v e r s e power t o o l a c t i o n and loosen b o l t ; uncrew f o u r worksite b o l t s .

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Svow power t o o l , t u r n over works,te and h a n d - s t a r t t h r e e b o l t s ; unstow power t o o l and t i g h t e n b o l t a ; stow power t o o l and remove hand t o o l t o t i g h t e n Instrumented b o l t f o r f i v e seconds, t h e n loosen b o l t and stow hand t o o l ; detach knee t e t h e r and remove and check power t o o l ; unscrew t h r e e b o l t s ; stow power t o o l , t u r n workslte over and hand-start f o u r b o l t s ; unstow power t o o l and t i g h t e n b o l t s ; t i g h t e n instrumented b o l t f o r f i v e seconds, then loosen i t ; r e p e a t instrumented b o l t t i g h t e n i n g and looseni n g with hand t o o l ; stow t o o l s , close l i d , and stow t o o l box i n a d a p t e r well

.

Having completed t h e D-16 Power Tool Evaluation experiment, t h e EVA p i l o t w i l l once again change film i n t h e 16m EVA camera. He w i l l move t o t h e adapter again and e v a l u a t e the h a n d r a i l s , i n sert h i s u m b i l i c a l i n t o t h e a d a p t e r guard, photograph the a d a p t e r and remove any d e b r i s l e f t from apacecraft launch and s e p a r a t i o n . U s i n g "overhsoe" footholds mounted a t t h e i n s i d e rim of t h e adapt e r t o r e s t r a i n him, t h e p i l o t w i l l open a hatchway i n t o the adapter p r o t e c t i v e cover and w i l l reach i n s i d e t o connect a quickdisconnect f i t t i n g on t h e f r e e end of t h e " M U l i n e t o t h e r e c e i v e r f i t t i n g on t h e maneuvering u n i t . He w i l l unstow the " M U and Velcro i t t o the ELSS, t h e n remove the Apollo cameras from i n s i d e t h e a d a p t e r and s i m i l a r l y a t t a c h them t o t h e ELSS. On h i s r e t u r n t o t h e cabin area t o hand t h e r e t r i e v e d cameras t o t h e command p i l o t , the EVA p i l o t w i l l t u r n on t h e n i t r o g e n valve t h a t feeds p r o p e l l a n t i n t o the HHMU umbilical. He w i l l move on t o the nose of the s p a c e c r a f t , j e t t i s o n the docking bar m i r r o r , and go through s t a b i l i z a t i o n and t r a n s l a t i o n evaluat i o n of t h e hand-held maneuvering u n i t . P r i o r t o ingress, he w i l l t u r n o f f the n i t r o g e n valve, bleed the p r o p e l l a n t from the " M U u m b i l i c a l by f i r i n g the u n i t i n s h o r t b u r s t s while he holds on t o t h e h a n d r a i l . He w i l l r e t u r n t o t h e cabin and ingress. During t h e next r e v o l u t i o n b o t h a s t r o n a u t s w i l l load a j e t t i s o n bag with t h e EVA umbilical and u m b i l i c a l bags, t h e HHMU, camera b r a c k e t , d e b r i s c u t t e r s , wrist mirrors, knee t e t h e r and o t h e r no-longer-needed equipment f o r which t h e r e - i s n o t s t o r a g e room i n t h e cabin. The bag w i l l be j e t t i s o n e d through t h e p i l o t ' s h a t c h as was a similar package on Gemini 10. The ELSS w i l l be j e t t i s o n e d a t t h e same time, b u t as a separate u n i t . Docked Agena PPS Maneuvers During t h e 26th r e v o l u t i o n , following t h e second sleep period, a 943 f p s burn of t h e Agena primary propulsion system w i l l change the docked Gemini/Agena o r b i t from t h e 185-mile c i r c u l a r o r b i t t o 185 miles by 865 miles. -more-

-13This posigrade maneuver will occur at about 40:33 GET over the Canary Islands, The spacecraft should reach its new apogee about 55 minutes later over Carnarvon. Time and position of the maneuver and apogee were seilected to minimize the radiation encountered by the spacecraft near apogee during the following two orbits and to provide acceptable retrofire and landing conditions if the flight should be terminated during this period, The last docked PPS burn will be performed at the beginning of the 28th revolution over Bermuda at 43:56 GET. The retrograde 943 fps maneuver will restore the orbit to 185 miles circular, Standup EVA The second extravehicular activity, a 140-minute standup EVA, will begin about Lc6:OO over Tananarive and will end in the 30th revolution over Hawaii. Experiments to be conducted by the standing pilot will be primarily photographic. The pracedure will follow that used by Michael Collins in Gemini 10. The pilot will interconnect his environmental control system (ECS) and electrical hoses with an 18-inch ECS inlet extension, a 24-inch ECS outlet, and a 283-inch electrical umbilical extension carrying communication and bio-medical instrumentation lines. He will tether himself by a strap that he loops around the left arm restraint of the right-hand seat, passing one end of the tether through a loop on the other end to hold it to the arm restraint. The free end clips to his parachute harness with the same type of attachment used on the 30-foot EVA tether. This standup tether is adjustable at 29, 35 and 42s inches. The pilot will select the length that best suits h i s purposes and comfort. One third or less of his body will protrude from the open hatchway during the EVA, Station-Keeping Exercise

In the 3lst revolution at about 49:5O G E T the spacecraft will translate the docked configuration to about 30 degrees off the local vertical, the Agena PPS engine pointing toward the Earth, The spacecraft w i l l separate from the Agena and back off to the end of the tether. The spacecraft will be in a nose-down attitude above the target vehicle. Seven to eight minutes later the Agena will be stable in the engine-down position with its longitudinal center-line pointing toward the center of the Earth. Gemini 11 will stabilize itself in a nose-down attitude with its center-line aimed through the Agena toward the Earth's center. A t this time the Gemini orbital attitude and maneuvering system (OAMS) and the Agena attitude control system (ACS) will

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-14If t h e s p a c e c r a f t has been p o s i t i o n e d p r o p e r l y a t the end of t h e t e t h e r and i f t h e r e l a t i v e v e l o c i t i e s between t h e v e h i c l e s are not i n excess of .2 feet-per-second, a long-term s t a t i o n keeping p o s i t i o n w i l l have been established and w i l l keep t h e v e h i c l e s i n t h e same r e l a t i v e a t t i t u d e and p o s i t i o n as they c i r c l e t h e Earth nose-down Gemini above t h e engine-down Agena, t h e i r l o n g i t u d i n a l c e n t e r - l i n e s continuously p o i n t i n g toward t h e Earth's center.

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rove f e a s i b l e , a slow r o t a t i o n (one degree p e r second o r less of the t e t h e r e d combination w i l l be e s t a b l i s h e d by a s p a c e c r a f t p i t c h maneuver simultaneous w i t h f i r i n g of t h e forward t h r u s t e r s . C e n t r i f u g a l f o r c e i s expected t o m a i n t a i n the t a u t n e s s of the tether, keepi n g t h e v e h i c l e s a t a c o n t r o l l e d d i s t a n c e from each o t h e r and minimizing the p r o p e l l a n t required f o r sta€ion-keeping. If t h a t phase of t h e e x e r c i s e does not

P

The t e t h e r i s two-inch Dacron webbing. It i s s t o r e d i n a bag l o c a t e d a t the back s i d e of the Agena t a r g e t docking a d a p t e r (TDA) docking cone. The bag i s covered by a n aerodynamic shroud a t Agena launch. The Agena end of t h e t e t h e r i s looped and sewn through a D-ring fastened by a metal p l a t e t o t h e docking cone. The s p a c e c r a f t end od t h e t e t h e r i s looped and sewn t o a metal ring-clamp t h a t s l i p s over t h e s p a c e c r a f t docking bar and i s t i g h t e n e d t o t h e bar by a screw-down mechanism. A "break link:' engineered t o part a t 800 pounds of p r e s s u r e , i s b u i l t i n t o t h e t e t h e r . Pyrotechnics a t t h e base of docking bar, a c t i v a t e d from t h e s p a c e c r a f t cabin u s u a l l y j u s t b e f o r e r e e n t r y , blow t h e bar and t e t h e r f r e e a t the completion of t h e experiment.

Separation Maneuver A t completion of t h e t e t h e r e x e r c i s e d u r i n g t h e 33rd revol u t i o n , t h e f i n a l s e p a r a t i o n of 3 f p s r e t r o g r a d e w i l l drop the s p a c e c r a f t below t h e A ena. T h i s maneuver w i l l occur a t 53:lO over H a w a i i . Gemini 1 w i l l p u l l ahead and out of s i g h t of the target v e h i c l e during t h e following r e v o l u t i o n s .

f

R e t r o f i r e O r b i t Maneuver Based on remaining p r o p e l l a n t , a r e t r o g r a d e maneuver may b e made i n t h e 35th r e v o l u t i o n t o lower s p a c e c r a f t perigee. The maxbnum maneuver t h a t w i l l be made i s 134.5 f p s t o r e s u l t i n a perigee of 100 m i l e s . However, t h e maneuver i s not necessary t o s u c c e s s f u l r e t r o f i r e and r e e n t r y and it w i l l be modified o r deleted according t o p r o p e l l a n t remaining.

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R e t r o f i r e and Reentry The Gemini 11 mission w i l l terminate w i t h r e t r o f i r e nominally a t T O : & GET i n the 44th r e v o l u t i o n over the P a c i f i c Ocean n e a r Hawaii. R e t r o f i r e determination w i l l be made through t h e spacec r a f t onboard systems and v e r i f i e d by ground c o n t r o l t o e v a l u a t e t h e accuracy of such onboard determination. Reentry w i l l b e i n t h e automatic mode. The s p a c e c r a f t computer and i n e r t i a l guidance system IGS) w i l l f u r n i s h t h e a t t i t u d e c o n t r o l and maneuver e l e c t r o n i c s ACME) with commands f o r bank a n g l e s o r f i x e d r o l l rates t o s t e e r t h e s p a c e c r a f t t o t h e predetermined landing p o i n t .

I

The Gemini s p a c e c r a f t ' s o f f s e t c e n t e r of g r a v i t y has used i n previous missions t o g e n e r a t e l i f t and t o c o r r e c t range e r r o r s , b u t always I n the manual d i r e c t o r t h e r a t e mode. Gemini 11 w i l l b e t h e f i r s t mission i n t h e program which r e e n t r y guidance i s f u l l y automatic.

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been crosscommand in

EXPERIIvlENTS Of t h e 1 2 experiments t h a t w i l l f l y i n Gemini 11, only two are new. They a r e D i m L i g h t Photography (S-30) and EarthMoon L i b r a t i o n Region Photography ( S - 2 9 ) . However, while f o u r

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t h e y e i t h e r were o t h e r s have flown p r e v l o u s l y -- on Gemini 8 not performed o r not r e t r i e v e d because t h a t mission terminated i n t h e seventh r e v o l u t i o n . Those f o u r are Mass Determination ( D - 3 ) , Night Image I n t e n s i f i c a t i o n ( D - l 5 ) , a n d Power Tool Evaluation (D-16), n e i t h e r performed, and Nuclear Emulsion (S-9) which was not r e t r i e v e d . The complete l i s t of G e m i n i 11 experiments is: 1. 2.

3. 4. 5.

6.

7.

8. 9. 10.

11. 12.

D-3 D-15 D-16 S-4

----Mass Determination Night Image I n t e n s i f i c a t i o n

Power Tool Evaluation ----Radiation a n d Zero G E f f e c t s

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S-5 S-6 S-9 S-11 S-13

Synoptic T e r r a i n Photography -Synoptic Weather Photography ----Nuclear Ehulsion Airglow Horizon Photography -U l t r a v i o l e t As%ronomical Camera S-26 I o n Wake Measurement S-29 -- Earth-Moon L i b r a t i o n Region Photography S-30 -- D i m Light Photography/Orthicon --=

D e s c r l p t i o n s of t h e experiments follow:

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D-3 Mass Determination (flown on Gemini 8, n o t Derformedl: To t e s t a techniaue a n d accuracy of a d i r e c t cont a c t m e t h b d of determining t h i mass o f an o r b i t i n g o b j e c t , i n t h i s case t h e Agena Target Vehicle. Experiment sponsor i s the Dept. of Defense, U n i t e d S t a t e s A i r Force. No experiment equipment, o t h e r t h a n t h e normal spacecraft systems, i s involved. S p a c e c r a f t yaw, roll and p i t c h r a t e gyros are i n primary mode. Computer i s on. Platform i s i n o r b i t rate mode. The s p a c e c r a f t i s undocked f o r c a l i b r a t i o n , docked for mass determination. P r o p e l l a n t consumption i s estimated 30 pounds. Data w i l l be t r a n s m i t t e d t o t h e ground f o r p o s t - f l i g h t analysis.

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*

The c a l i b r a t i o n t r a n s l a t i o n w i l l be conducted by the s p a c e c r a f t only. P r o p e l l a n t and cryogenic q u a n t i t i e s are recorded, t h e s p a c e c r a f t i s t r a n s l a t e d a n d the v e l o c i t y change i s recorded as a r e p r o p e l l a n t a n d cryogenic q u a n t i t i e s , The mass determination t r a n s l a t i o n i s done w i t h the s p a c e c r a f t a n d the Agena docked. Q u a n t i t i e s are recorded, Agena a t t i t u d e s a r e c o n t r o l l e d t o 0-30-0 degrees by t h e s p a c e c r a f t thrusters. The s p a c e c r a f t t r a n s l a t e s the docked combination, and v e l o c i t y and q u a n t i t y changes are recorded.

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D-15 Night Image I n t e n s i f i c a t i o n (flown on G e m i n i 8, not performed): To t e s t t h e usefulness ana perr-ormance 01a low-light-level t e l e v i s i o n system as a sumlement t o unaided v i s i o n i n observing suEface f e a t u r e s - p r i m a r i l y when such f e a t u r e s are i n darknessand s p a c e c r a f t p i l o t s a r e not dark-adapted. Sponsor i s U. S. Naval A i r Development C e n t e r . dxperiment eqiiipment i s a n Image-Orthicon t e l e v i s i o n camera, canera c o n t r o l u n i t , p o r t a b l e camera viewing monitor, recording monitor a n d photographic camera, and the monitor e l e c t r o n i c s a n d equipment c o n t r o l u n i t . The TV camera i s mounted i n t h e spacecraft retrograde section. I t s l e n s points i n t o a m i r r o r extending a t a 45-degree angle from the bottom of t h e r e t r o s e c t i o n . The m i r r o r i s t h e only e x t e r n a l u n i t . The camera c o n t r o l u n i t i s mounted i n the adapter equipment s e c t i o n , t h e viewing monitor stowed on t h e l e f t s i d e of t h e r i g h t - h a n d f o o t w e l l and mounted f o r use under t h e right-hand c o n t r o l panel. The recording monitor and photographic camera a n d t h e monitor e l e c t r o n i c s a n d equipment c o n t r o l u n i t are mounted i n the right-hand l a n d i n g g e a r w e l l . The system i s b u i l t by General E l e c t r i c of Utica, N. Y. The 16mm camera f o r r e c o r d i n g p i c t u r e s from t h e monitor i s provided by t h e Dept. o f Defense, experiment sponsor. Spacecraft consumables estimated t o be used a r e 165 watts of power average t o t a l and 0.75 pounds of p r o p e l l a n t p e r t a s k . To conduct t h e experiment, the p i l o t unstows t h e viewing p a n e l a n d a t t a c h e s i t t o t h e underside of h i s c o n t r o l panel. The system i s a c t i v a t e d and a 30-minute warmup period i n i t i a t e d . The e x t e r n a l m i r r o r i s extended. Nighttime targets are acquired and tracked. While t h e photographic camera records t h e monitor images, t h e p i l o t voice-records h i s observations o f t h e image on t h e p o r t a b l e monitor a n d t h e command p i l o t voice-records h i s observ a t i o n s through t h e window. Once t h e m i r r o i s e r c t e f l i g h t , i t cannot be r e t r a c t e d . Since i t i fhe &?g2g p r o f i l e of t h e lower v e r t i c a l t h r u s t e r , t h e mlssron w i sequenced so t h a t t h r u s t e r i s not required t o operate during t h e experiment. Targets w i l l be s e l e c t e d by t h e & p t * of Defense, and r e s u l t s of t h e experiment W i l l be announced by DOD in accordance w i t h that department's P o l i c i e s -

lfks

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D-16 Power Tool Evaluation (flown on Gemini 8, not performed): To e v a l u a t e man's c a p a b i l i t y t o perform work tasks i n space, i n c l u d i n g t h e comparlson of a b i l i t y t o work t e t h e r e d and untethered, a n d t o e v a l u a t e t h e performance of t h e m i n i m u m r e a c t i o n power t o o l . Sponsor i s t h e Dept. of Defense, United S t a t e s A i r Force. Equipment involved i s t h e m i n i m u m r e a c t i o n power t o o l and b a t t e r y , a hand wrench, t h e t o o l r e s t r a i n t box, and t h e a s t r o n a u t ' s knee t e t h e r . The equipment i s s t o r e d i n t h e t o o l box which i s mounted i n a w e l l i n t h e adapter s e c t i o n behind t h e p i l o t ' s hatch. The experiment i s conducted during t h e p i l o t ' s e x t r a v e h i c u l a r a c t i v i t y a n d i s monitored by t h e 16m EVA camera and by torque-vs-time d a t a telemetered from an i n s t r u m e n t e d b o l t on t h e work s i t e . No e l e c t r i c a l power o r p r o p e l l a n t expenditures are programmed f o r t h e experiment. ~

To conduct t h e experiment, t h e EVA a s t r o n a u t moves t o the adapter, p u l l s t h e t o o l box from i t s well, a n d w i t h d r a w s t h e power t o o l . The t o o l box p u l l s s t r a i g h t up and i t s l i d , holding t h e worksite b o l t s , opens about 90-degrees; t h e box remains att'ached t o t h e s p a c e c r a f t and resGows i n t h e w e l l a f t e r t h e experiment. The a s t r o n a u t t i g h t e n s and l o o s e n s b o l t s i n a p r e s c r i b e d p a t t e r n , once w i t h h i s body h e l d t o t h e s p a c e c r a f t by a nine-inch t e t h e r looped around h i s knee a n d through t h e h a n d r a i l , once without t h e t e t h e r . He u s e s b o t h t h e power and t h e hand wrench during t h e experiment.

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S-4 Radiation a n d Z e r o G E f f e c t s on Blood a n d Neurospora (flown on G e m i n i 3) : To determine i f a s y n e r g i s t i c r e l a t i o n s h i p e x i s t s between e f f e c t s of welghtlessness and r a d i a t i o n on white b l o o d c e l l s a n d neurospora. Sponsors are t h e Office of Space Science and Applications ( O S S A ) a n d t h e Oak Ridge National Laboratories. Experiment equipment i s h e r m e t i c a l l y sealed u n i t s containing blood and a r a d i a t i o n source ( i n one) and neurospora and a r a d i a t i o n source ( i n t h e second), a r e f r i g e r a t i o n u n i t f o r t h e blood sample, a n d mounting b r a c k e t s . The blood i s from a human volunteer s e l e c t e d by t h e sponsors; neurospora i s p i n k bread mold; t h e r a d i a t i o n source i s phosphorous 32 beta p a r t i c l e s e m i t t i n g 12.5 m i l l i c u r i e s each u n i t ; t h e h e r m e t i c a l l y sealed u n i t s are aluminum boxes 3k by 3* by 1 i n c h w i t h a 34-inch o p e r a t i n g h a n d l e . The r e f r i g e r a t i o n source, added s i n c e t h e G e m i n i 3 experiment because of t h e l o n g e r duration of f l i g h t , s u s t a i n s a temperature of 39 degrees p l u s or minus f o u r degrees F w i t h i n t h e blood u n i t . The blood u n i t i s mounted on the l e f t - h a n d hatch, t h e neurospora u n i t on t h e l e f t wall of t h e r i g h t f o o t w e l l . S p a c e c r a f t consumables a n t i c i p a t e d a r e 20 w a t t s of power, no propellant. telemetry analog channel monitors t h e blood r e f r i g e r a t i o n u n i t temperature.

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To conduct t h e exseriment, t h e command p i l o t a c t i v a t e s a n d d e a c t i v a t e s i r r a d i a t i o n by means of t h e o p e r a t i n g handle on t h e blood_unit. The p i l o t s i m i l a r l y a c t i v a t e s and d e a c t i v a t d s the neurospora i r r a d i a t i o n , Both voice-record a c t i v a t i o n and d e a c t i v a t i o n .

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S-5 Synoptic Terrain Photography ( f l o w n on Gemini 4- t h r u 7 and 10): To use a e r i a l photdgraphy f o r h i g h q u a l i t y photographs f o r r e s e a r c h i'n geology, geophysics, geography, oceanography, and related f i e l d s . Sponsors a r e OSSA a n d t h e Goddard S p a c e f l i g h t Center. Equipment I s t h e 7Omm Maurer camera w i t h 8Omm l e n s (f2.8) and r i n g s i g h t , E s t i m a t e d p r o p e l l a n t usage f o r t h i s experiment i s 5 pounds,

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S-6 Synoptic Weather Photography (flown on G e m i n i 4- t h r u 7 and 10): To o b t a i n s e l e c t i v e h i g h q u a l i t y c o l o r photographs of t o study the f i n e s t r u c t u r e of t h e e a r t h ' s weather system, Sponraors are OSSA and the National Weather S a t e l l i t e Center. Equipment i s t h e same aa f o r t h e Synoptic T e r r a i n Photography.

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Estimated p r o p e l l a n t use i s 5 pounds.

S-9 Nuclear Emulsion (flown on Gemini 8, not r e t r i e v e d ) : To s t u d s t h e cosmic r a d i a t i o n i n c i d e n t on t h e e a r t h ' s atmosphere, t o o b t a i n d e t a i l e d chemical composition of t h e heavy p r i m a r y n u c l e i , a n d t o s e a r c h f o r r a r e p a r t i c l e s . Sponsors are OSSA and t h e U. S. Naval Research Laboratories. Equipment i s a r e c t a n g u l a r package 84 by 6 by 3 inches weighing 1 5 pounds, and i n c l u d i n g the n u c l e a r emulsion f i l m s t a c k , a motor t o advance t h e emulsion, and a t i m e r t o r e g u l a t e t h e motor, The package i s mounted a t o p the s p a c e c r a f t r e t r o a d a p t e r s e c t i o n p r i o r t o launch, i s a c t i v a t e d a t i n s e r t i o n , and i s r e t r i e v e d by t h e EVA p i l o t . The experiment i s conducted w i t h the s p a c e c r a f t i n p l u s o r minus 15 de4rees of t h e e a r t h ' s average magnetic f i e l d v e c t o r . However, no p r o p e l l a n t expenditure i s p r e d i c t e d ; power expenditure i s 38 m i l l i a m p s (MA) f o r 0,6 seconds every 60 seconds a n d 0.54MA f o r t h e remaining time i n Mode 1, 38m f o r 4 seconds and 2.5MA t h e r e a f t e r i n Mode 2. The package W i l l be r e t r i e v e d during EVA a n d w i l l be stowed on t h e c e n t e r - l i n e box i n t h e cabin.

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S-11 Airglow Horizon Photography ( flown on Gemini 9 ) : To measure b d i r e c t photograph the h e i g h t s a t which atomic oxygen (557A and sodium (5893A airglow l a y e r s occur i n the upper atmosphere. Sponsors are OSSA and the U. S. Naval Research Laboratory. Equipment i s 7Omm Maurer camera w i t h 5Omm lens (f0.95) a n d i n t e r f e r e n c e f i l t e r , film magazine w i t h f o c a l plane f i l t e r s , extended a c t u a t o r , i l l u m i n a t e d camera s i g h t , a n d a d j u s t a b l e p i t c h mounting bracket a n d bracket adapter. The o p t i c a l s i g h t i s i n s t a l l e d i n t h e left-hand window, t h e mounting b r a c k e t i n t h e right-hand window. E s t i m a t e d p r o p e l l a n t usage i s 24 pounds i n docked configuration o r 1 2 pounds i n undocked.

3

'3

S-13 U l t r a v i o l e t Astronomical Camera (flown on Gemini 10): To t e s t t h e techniques of u l t r a v i o l e t photography under vacuum c o n d i t i o n s a n d t o o b t a i n u l t r a v i o l e t r a d i a t i o n o b s e r v a t i o n s of s t a r s i n wave l e n g t h region of 2000 t o 4000 Angstroms by sgect r a l means. Sponsors are OSSA and Northwestern University. Equipment is t h e Maurer 7Omm camera w i t h W lens (f3.3) and magazine, o b j e c t i v e g r a t i n g and o b j e c t i v e prism, extended s h u t t e r a c t u a t o r , a n d mounting bracket. For the experiment, t h e camera i s mounted on the c e n t e r l i n e torque box t o p o i n t through t h e opened right-hand hatch. P r o p e l l a n t expenditure i s estimated a t 4.5 pounds p e r night pass. Two night p a s s e s w i l l be used t o photograph probably s i x star f i e l d s . -0

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s-26 Ion Wake Measurement (flown on Gemini 10) : To determine a n d measure the i o n a n d e l e c t r o n w a k e s t r u c t u r e and p e r t u r b a t i o n of t h e ambient medium produced by a n o r b i t i n g vehicle, a n d t o study the changes i n the i o n f l u x a n d w a k e caused by t h r u s t e r f k r i n g s . Sponsors are OSSA a n d Electro-Optical Systems Inc. Equipment i s a n inboard i o n d e t e c t o r , l o c a t e d i n the t h r o a t of the Agena target docking adapter (TDA), a n outboard i o n d e t e c t o r and a n e l e c t r o n d e t e c t o r l o c a t e d on t h e o u t s i d e back of t h e TDA, the former about 1 5 degrees above t h e h o r i z o n t a l c e n t e r l i n e , the l a t t e r 15 degrees below on t h e right-hand sdde, a n d a programmer l o c a t e d a t t h e t o p i n s i d e of the TDA. P r o p e l l a n t usage i s estimated 29 pounds.

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- 21The experiment i s conducted w i t h the Agena s t a b i l i z a t i o n c o n t r o l system on t h e Agena o r i e n t e d e i t h e r TDA east o r south. The s p a c e c r a f t platform i s a l i g n e d a n d i n orb rate, radar i s o f f w i t h i n 20 f e e t of t h e Agena, a t t i t u d e c o n t r o l is i n p u l s e mode, a n d t h e 16mm camera i s i n s t a l l e d i n the l e f t - h a n d window. Both t r a n s v e r s e a n d linear mapping w i l l be accomplished. Data w i l l b e telemetered from t h e Agena.

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S-29 Earth-Moon L i b r a t i o n Region Photography (new): To i n v e s t i g a t e t h e regions of the L4 a n d L5 l i b r a t i o n p o i n t s of t h e earth-moon system t o determine t h e p o s s i b l e e x i s t e n c e o f clouds of p a r t i c u l a t e m a t t e r o r b i t i n g t h e earth i n these regions. Sponsors a r e OSSA and the U. S. Geological Survey, Center of Astro eolog Equipment i s the Maurer 7Omm camera w i t h 50m l e n s Tf0.957, extended s h u t t e r a c t u a t o r , a n d t h e P r o p e l l a n t usage i s estimated a t 8 S-11 mounting bracket. pounds i n docked configuration, 4 pounds undocked. The camera i s mounted i n t h e r i g h t - h a n d window, t h e o p t i c a l s i g h t i n t h e l e f t . Two n i g h t passes w i l l be used f o r t h e experiment, one e a r l y i n the mission, one l a t e i n t h e mission.

.

The L4 and L 5 l i b r a t i o n regions are t h e LaGrangian p o i n t s o f s t a b l e equilibrium where c e n t r i f u g a l f o r c e s balance g r a v i t a t i o n a l f o r c e s ; they a r e l o c a t e d 60 degrees ahead of and

60 degrees b e h i n d , r e s p e c t i v e l y , t h e moon i n i t s o r b i t a l Theory holds that these regions s h i f t p o s i t i o n some 1 2 t o 15 degrees i n a 24-hour period and t h a t the balance of c e n t r i f u g a l w i t h g r a v i t a t i o n a l f o r c e may hold c a p t i v e clouds of p a r t i c l e s . Comparison of t h e photographs i n r e l a t i o n t o the t h e o r e t i c a l s h i f t of t h e l i b r a t i o n regions may determine t h e e x i s t e n c e of such clouds. path.

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S-30 Dim Light Photography/Orthicon (new) : To o b t a i n photograohs of various f a i n t a n d d i f f u s e astronomical phenomena such as airglow l a y e r i n p r o f i l e , b r i g h t e s t Milky Way, zodiacal l i g h t a t 60-degree elongation, gegenschein ( counterglow), and the LaGrangian l i b r a t i o n p o i n t s of t h e earth-moon system. Sponsors a r e OSSA, Dudley Observatory, a n d t h e U n i v e r s i t y of Minnesota. Equipment w i l l be t h e D-15 low-light TV system p l u s t h e s p a c e c r a f t o p t i c a l s i g h t . P r o p e l l a n t consumption i s estimated 0.75 pounds p e r mode. Command p i l o t a n d p i l o t voice-recordings of window a n d monitor observations w i l l be made as i n D-15.

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CREW PROVISIONS AND TRAINING

C r e w T r a i n i n g Background

I n a d d i t i o n t o the e x t e n s i v e g e n e r a l t r a i n i n g received p r i o r t o f l i g h t assignment, t h e following preparat i o n s have o r w i l l be accomplished p r i o r t o launch: Launch a b o r t t r a i n i n g i n t h e Gemini Mission Simul a t o r and the Dynamic C r e w Procedures Simulator. 1.

2. Egress and recovery a c t i v i t i e s u s i n g a crew procedures development t r a i n e r , s p a c e c r a f t b o i l e r p l a t e model and a c t u a l recovery equipment and personnel, Pad emergency egress t r a i n i n g u s i n g e l e v a t o r and s l i d e wire, and breathing apparatus.

3. Celestial p a t t e r n r e c o g n i t i o n i n t h e U n i v e r s i t y of North C a r o l i n a ' s Morehead Planetarium a t Chapel H i l l . 4. Zero g r a v i t y t r a i n i n g i n KC-135 aircraft t o pract i c e EVA. Stowage and donning of EVA equipment i s done i n a i r c r a f t and crew procedures t r a i n e r . Additional EVA t r a i n i n g i s performed i n 20-foot chamber a t vacuum conditions.

5.

S u i t , seat and harness f i t t i n g s .

6.

T r a i n i n g s e s s i o n s t o t a l i n g approximately 15 hours

per crew member on the Gemini t r a n s l a t i o n and docking simu-

lator.

7. Detailed Agena and Gemini systems b r i e f i n g ; detailed experiment b r i e f i n g s ; f l i g h t p l a n s and mission r u l e s reviews

.

8. P a r t i c i p a t i o n i n mock-up reviews, systems review, subsystem tests, and s p a c e c r a f t acceptance review. 9.

E j e c t i o n seat t r a i n i n g . -more-

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During f i n a l p r e p a r a t i o n f o r f l i g h t , t h e crew part i c i p a t e s i n network launch a b o r t simulations, j o i n t combined systems test, and t h e f i n a l s i m u l a t e d f l i g h t tests. A t T-2 days, t h e major f l i g h t crew medical examinations w i l l be administered t o confirm r e a d i n e s s f o r f l i g h t and o b t a i n data f o r comparison with p o s t f l i g h t medical examination results. Gemini 11 S u i t s The p r e s s u r e s u i t worn by t h e command p i l o t w i l l be similar t o s u i t s worn on Gemini 4, 5, 6, 8, 9, and 10. The p i l o t w i l l wear a s u i t w i t h s p e c i a l thermal p r o t e c t s v e cover layers f o r EVA a c t i v i t i e s .

Command Pilot S u i t

The Gemini command p i l o t ' s s u i t has f i v e l a y e r s and weighs 23 pounds. The l a y e r s are, s t a r t i n g i n s i d e t h e suit:

1. White c o t t o n constant wear undergarment w i t h pockets around the w a i s t . t o hold biomedical i n s t r u m e n t a t i o n equipment. 2.

Blue nylon comfort layer.

3. Black neoprene-coated nylon p r e s s u r e garment. 4. R e s t r a i n t layer of nylon l i n k n o t t o r e s t r a i n pressure garment and maintain i t s shape.

5.

White HI-1 nylon o u t e r layer. Pilot s u i t

The p r e s s u r e s u i t worn by t h e Gemini 11 p i l o t i s i d e n t i c a l t o t h e Gemini 4 and Gemini 8 p i l o t s u i t w i t h t h e following two exceptions: 1. No e x t r a v e h i c u l a r thermal over-gloves w i l l be worn. Thermal p r o t e c t i o n f o r t h e hands i s now i n t e g r a t e d i n a basic s u i t glove. 2. The material i s now a layer-up of neoprene-coated nylon, t h e same material as t h e p r e s s u r e r e t e n t i o n layer.

The Gemini e x t r a v e h i c u l a r s u i t has seven layers: and 7 are i d e n t i c a l t o t h e command p i l o t ' s s u i t .

5. Thermal p r o t e c t i v e l a y e r of seven layers of aluminized m y l a r w i t h spacers between each layer. -more-

1-4

-24 -

6.

Micrometeoroid p r o t e c t i v e layer.

For e x t r a v e h i c u l a r a c t i v i t y , t h e p i l o t w i l l wear a detachable o v e r v i s o r which has a t t a c h p o i n t s on both sides of the helmet and can be swiveled i n t o p o s i t i o n over t h e face-plate. The i n n e r v i s o r i s a polycarbonate material which provides impact and micrometeoroid p r o t e c t i o n . The o u t e r v i s o r i s gold-coated and provides p r o t e c t i o n f o r t h e eyes from s o l a r glare. When the cabin i s depressurized, the s u i t s a u t o m a t i c a l l y p r e s s u r i z e t o 3.7 pounds p e r square inch t o provide pressure and b r e a t h i n g oxygen f o r both crew members. The extraveh i c u l a r s u i t weighs 33 pounds

.

E x t r a v e h i c u l a r L i f e Support System (ELSS) It i s a 42-pound r e c t a n g u l a r box which i s worn on t h e c h e s t . It provides e l e c t r i c a l , mechanical and l i f e support connections between t h e E V A a s t r o n a u t and the s p a c e c r a f t . System i s 18 inches high, 10 inches wide and 6 inches deep. It c o n t a i n s a n e j e c t o r pump f o r c i r c u l a t i o n , a heat exchanger f o r cooling a i r , and a 30-minute emergency oxygen supply. Cont r o l s and a warning system f o r t h e emergency oxygen supply a r e mounted on t h e t o p of t h e u n i t . The ELSS f u n c t i o n s as a s u i t p r e s s u r i z a t i o n and a i r s u p p l y system during EVA.

Hand-Held Maneuvering Unit ("Mu\ T h i s u n i t i s similar t o t h e u n i t u s e d on Gemini 4 and Gemini 10. The u n i t provides t h e e x t r a v e h i c u l a r astronaut w i t h p o s i t i v e c o n t r o l of h i s a t t i t u d e and p r o p e l s h i m from p o i n t t o p o i n t i n space. Nitrogen f u e l b o t t l e s are l o c a t e d i n t h e adapter s e c t i o n . The f u e l i s fed t o t h e " M U through t h e u m b i l i c a l

.

Major components of t h e gun include forward and rev e r s e handles, two s p r i n g loaded poppet valves, f o l d a b l e t u b e s , two one-pound nozzles, and one two-pound nozzle. It weighs about three and half pounds and i s s t o r e d i n the a a p t e r during launch. The u n i t i s 12 inches long by 43 inches, and 15 inches r e t r a c t e d . T r a c t o r and braking t h r u s t ranges u p t o two pounds, and t h e t o t a l d e l t a v e l o c i t y c a p a b i l i t y of t h e gun i s 84 f e e t p e r second. -more-

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-25Umbilical

The umbilical f o r G e m i n i 11 includes two f l u i d t r a n s mission hoses, one f o r oxygen and one f o r the nitrogen "MU f u e l . When snubbed i n t o the r e s t r a i n t eye a t the nose of the spacecraft, the 3O-fo0t umbilical w i l l permit movement t o above 20 feet from the spacecraft. E l e c t r i c power, communications, and bio-instrumentation hardlines a l s o are contained i n the umbilical. The hoses are protected from temperature extremes by a wrapping of aluminized Mylar. The umbilical i s encased i n a sleeve of white nylon.

Medical Checks A t least one medical check w i l l be made each day by each crew member. Performed over a convenient ground s t a t i o n , a check w i l l c o n s i s t of: o r a l temperature and food and water intake evaluation.

Body Waste Disposal

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P l a s t i c bag w i t h adhesive l i p t o proSolid Wastes vide secure attachment t o body. Contains germicide which prevents formation of b a c t e r i a and gas. Adhesive l i p a l s o used t o form s e a l f o r bag a f t e r use and bag i s stowed i n empty food container box and brought back f o r analysis.

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Urine Voided i n t o f i t t e d receptacle connected by hose t o either a c o l l e c t i o n device o r overboard dump. Water Measuring System A mechanical measuring system has been added t o water gun. It c o n s i s t s of a neoprene bellows housed i n a small metal cylinder mounted a t base of gun. The bellows holds onehalf ounce of water. When plunger o_f gun is depressed, a s p r i n g pushes water out o f bellows through gun. A counter i n r i g h t side of gun r e g i s t e r s number of times bellows is a c t i v a t e d . Each crewman w i l l record how much he drinks by noting numbers a t beginning and end of each use of gun.

Food Number of Meals

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10 per astronaut f o r mission.

Type -- Bite-sized and rehydratable. Water i s placed i n rehydratables with s p e c i a l gun. Bite-sized items need no rehydration. Storage -- Meals Individually wrapped i n aluminum f o i l and polythelene, polyamide laminate. A l l meals are s t o r e d in the r i g h t a f t food box over the p i l o t ' s right shoulder. -more -

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Gemini 11 Food Menu (Three -Day Menu Cycle)

lhv1: M e a l A (R) Fruit cocktail (R) Toasted o a t c e r e a l (B) Bacon s q u a r e s ( d o u b l e ) ( R ) Ham and a p p l e s a u c e (B) Cinnamon t o a s t (R) Orange d r i n k (R) Pineapple g r a p e f r u i t d r i n k

D a y 1: Me& (R) (R)

(B) (B) (R) (B)

(R)

(B) (R) (B) (R)

Meal C Beef p o t r o a s t Potato salad Cinnamon t o a s t C h o c o l a t e pudding Brownies Tea

Bacon s q u a r e s ( d o u b l e ) Cinnamon t o a s t Cocoa Orange d r i n k

DAY 2: Meal B (R) Pea Soup (R) Tuna s a l a d

(B) (B) (R)

(B) (R)

(B) (R)

Cinnamon t o a s t Fruitcake (date) Pineapple g r a p e f r u i t drink

Cheese s a n d w i c h e s A p r i c o t pudding Gingerbread cubes Grapefruit drink

DAY 3: Meal A (R) Peaches

119 92 161 253 83 175 883

Shrimp c o c k t a i l Chicken and g r a v y Toasted bread cubes Fruitcake (Pineapple) Orange g r a p e f r u i t d r i n k Coconut c u b e s

DAY 2: Meal A (R) Applesauce (R) Sugar coated f l a k e s

(B) (B) (R) (R)

91 180 127 56 83 83 7 07

B

DAY 1:

(R)

DAY 2 : Meal C (R) Beef and v e -g e t a b l e s ( R ) Meat and s p a g h e t t i

CaLories 87

(B) (R) (B) (R) (R)

-

Strawberry cereal cubes Sausage p a t t i e s ( 2 ) Cinnamon t o a s t Orange d r i n k Grapefruit drink

Calories

9 8 70 158 3 00 183 83 892

98 171 223 56 83 83 714

(R) Hehydratable ( B) Bite-size

Calories 1 1 9 143 56 3 07 2 41 32 898

DAY 3: Meal B (R) Shrimp c o c k t a i l (R) Beef and g r a v y (R) Corn

(B) (B) (R)

139 139 180 56 190 83 787

Toasted bread cubes Fruitcake (Pineapple) Orange g r a p e f r u i t d r i n k

DAY 3: Meal C (R) P o t a t o soup (R) Chicken s a l a d (B) Beef sandwiches (R) B u t t e r s c o t c h pudding (R) Tea

220 214 56 26 2 83 83 5

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Calories T 160 105 161 253 83 88 1

220 237 268 311 32 1068

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MANNED SPACE FLIGHT TRACKING NETWORK GEMINI 1'1 MISSION REQ,UIREMENTS NASA operates the Manned Space Flight Tracking Network by usihg its own facilities and those of the Department of Defense for mission information and control. For Gemini 11, the network.wil1 provide flight controllers:

(1) Radar tracking, command control, voice and telemetry data are available from launch through Gemini spacecraft splashdown in recovery area. Except for voice communications, the network provides the same functions for the Agena as long as electrical power is available. ( 2 ) Verification of the proper operation of the systems onboard the Gemini and Agena target.

Real Time Computer Complex (RTCC) The RTCC at the Manned Spacecraft Center, Houston, will be the computer center responsible for the control of the entire mission. The RTCC collects, stores, processes, sends, and displays the necessary computer support information required by the flight controllers at the Mission Control Center (MCC) During the launch (powered flight) phase, the RTCC receives launch trajectory data from Bermuda and the Air Force Eastern Test Range (AFETR) radars via the Cape Kennedy CDC-3600 Real Time Computing Facility (RTCF)

.

During all phases of the mission, the RTCC receives trajectory and telemetry data from the various sites and stores and processes this information for command and control of the mission. This telemetered Information consists of bio-medical, environmental, electrical, command maneuvering, and other spacecraft systems parameters. This information is displayed at the various flight controllers consoles in the MCC where the necessary decisions are made. The flight controllers use the displayed information to generate the necessary voice messages or computer commands the RTCC must transmit to the spacecraft.

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Systems C-Band Radar

S-Band Radar Telemetry Receive & Record Telemetry Real Time Display Low Speed (Tpy) Telemetry Data Transmission Wide Band Data High Speed Data

On S i t e Data Process & Summry Gemlni Launch Veh i c l e Telemetry Gemini Launch Veh i c l e Coxnand Digital Conmitnd System

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~

Voice Transmit & Receive Transmit Teletype & Receive

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Flight Control Team Manned Spacecraft Acquis i t i o n Aid System Skin Track

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. Tracking The Gemini mission w i l l r e q u i r e separate t r a c k i n g of f o u r space v e h i c l e s t h e Gemini s p a c e c r a f t , and t h e Agena Target Vehicle ( A T V ) , T i t a n I1 which is the Gemini Launch Vehicle (QLV), and as required, the Atlas Booster (SLV-3) The Gemini Target Vehicle w i l l c a r r y one C-band and one S-band beacon, Skin t r a c k i n g (radar s i g n a l bounce) of t h e s p a c e c r a f t , Agena target v e h i c l e s , and Gemini launch vehic l e throughout o r b i t a l l i f e t i m e i s a mission requirement. The MSFN Wallops S t a t i o n (WLP) Space Range Radar (SPANDAR) and v a r i o u s f a c i l i t i e s of the North American A i r Defense Command (NORAD) w i l l be used f o r t h i s mission, However, NORAD w i l l not t r a c k during t h e rendezvous phase,

Various combinations o f s p a c e c r a f t t r a c k i n g a s s i g n ments w i l l be c a r r i e d out according t o i n d i v i d u a l s t a t i o n c a p a b i l i t y , Some sites have radar systems capable of prov i d i n g space p o s i t i o n information on both .the Gemini and Agena v e h i c l e simultaneous1 through t h e i r V e r l o r t (S-band) and FPS-16 o r FPQ-6 (C-bandy antennas. Data transmission links, however, have only a single system c a p a b i l i t y ; therefore, p r i o r i t y w i l l be established by the F l i g h t D i r e c t o r o r F l i g h t Dynamics O f f i c e r according t o t h e i r needs. During the f i r s t revolution of t h e Agena ( p r i o r t o Gemini spacecraft l i f t - o f f ) , a l l s t a t i o n s w i l l t r a c k t h i s v e h i c l e i n o r d e r t o e s t a b l i s h i t s ephemeris ( p o s i t i o n ) as a c c u r a t e l y a s p o s s i b l e . After Gemini spacecraft l i f t - o f f , as a general rule, t h e C-band radars w i l l t r a c k t h e Gemini spacecraft w h i l e t h e S-band r a d a r s w i l l t r a c k the Agena T a r g e t Vehicle. The s i t e s w i t h dual-tracking c a p a b i l i t y w i l l t r a c k b o t h v e h i c l e s simultaneously. Goddard Space F l i g h t Center Computer S u p p o r t

N A S A ' s Goddard Space F l i g h t Center, Greenbelt, Md., r e a l - t i m e computing s u p p o r t f o r Gemini i n c l u d e s the processing of real-time t r a c k i n g information obtained from t h e T i t a n I1 and Agena s y s t e m s beginning w i t h mission simulations through Gemini spacecraft r e c o v e r y and Agena l i f e t i m e .

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Goddard's computer a l s o w i l l c e r t i f y t h e worldwide network's r e a d i n e s s t o support Gemini through a system-bysystem, s t a t i o n - b y - s t a t i o n , computer-programmed check-out method c a l l e d CADFISS (Computation and Data Flow I n t e g r a t e d Subsystem). Checkout o f network f a c i l i t i e s a l s o will be performed by Coddard during post-launch p e r i o d s when t h e spacec r a f t s are not e l e c t r o n i c a l l y " v i s i b l e " by some s t a t i o n s and continue u n t i l t h e v e h i c l e s are a g a i n w i t h i n a c q u i s i t i o n range. Gemini Spacecraft The s p a c e c r a f t has two C-band t r a c k i n g beacons. The model ACF beacon ( s p a c e c r a f t ) w i l l be i n s t a l l e d i n t h e ree n t r y module and t h e DPN-66 module beacon (adapter) i n t h e adapter s e c t i o n . The ACF beacon w i l l be prime f o r launch, i n s e r t i o n , and r e e n t r y phase, u s i n g t h e DPN-66 a s a backup f o r these periods.

Agena Target Vehicle The Agena target v e h i c l e w i l l c o n t a i n one C-band and one S-band beacon. The C-band beacon w i l l be a modified The C-band beacon w i l l be prime f o r Agena Target DPN-66. Vehicle p r i o r t o t h e Gemini launch. The Gemini s p a c e c r a f t w i l l be t h e prime target f o r C-band t r a c k i n g following launch. Acauisition Svstems A l l t h e s i t e s i n the network w i l l r e c e i v e real-time a c q u i s i t i o n messages ( p o i n t i n g d a t a ) from t h e Real Time Computing Center a t MSC, Houston. T h i s information w i l l be u s e d t o p o s i t i o n t h e telemetry and radar antennas a t t h e proper azimuth f o r a c q u i s i t i o n of t h e R F s i g n a l s from t h e two s p a c e c r a f t a t t h e time t h e y appear over t h e horizon. Most s i t e s a r e a l s o e q u i p p e d w i t h an a c q u i s i t i o n a i d system which permits " s l a v i n g " the r a d a r antennas t o t h e t e l e m e t r y antennas o r v i c e versa. S i n c e t h e t e l e m e t r y antennas have a much broader beamwidth t h a n t h e radar antennas, they may a c q u i r e t h e s p a c e c r a f t FU? s i g n a l f i r s t , making it p o s s i b l e t o p o i n t t h e radar antennas i n t h e g e n e r a l v i c i n i t y of t h e s p a c e c r a f t t o i n s u r e a r a p i d radar a c q u i s i t i o n .

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-Mission Message Requ irement s Low speed telemetry data ( o n - s i t e t e l e t y p e summaries) from f l i g h t c o n t r o l l e r manned s t a t i o n s w i l l be s e n t t o t h e Houston Mission Control Center.

Bermuda and Corpus C h r i s t i t r a n s m i t Gemini s p a c e c r a f t o r Agena t a r g e t v e h i c l e PCM telemetry v i a high-speed d i g i t a l data t o Houston Mission Control Center i n computer f o r m a t . MCC-K/TEL 111, Grand Bahama I s l a n d , Grand Turk I s l a n d , and Antigua w i l l remote Gemini s p a c e c r a f t and Agena wideband data t o t h e Houston Mission Control Center i n t h e same manner

.

Spacecraft Command System The prime ground system i n e f f e c t i n g rendezvous i s t h e D i g i t a l Command System ( D C S ) l o c a t e d a t key s t a t i o n s

throughout t h e worldwide network. Command c o n t r o l of t h e mission from launch through recovery w i l l as always be provided by t h e F l i g h t D i r e c t o r a t Houston Mission Control Cent e r . Maximum command coverage i s required throughout the mission. Grand Canary- I s l a n d ; Carnarvon, Australia; H a w a i i , and t h e two s h i p s , USNS Coastal Sentry and USNS Rose Knot, are DCS equipped and manned by f l i g h t c o n t r o l l e r s who w i l l i n i t i a t e a l l u p l i n k data command transmissions.

Following a s t r o n a u t recovery, f u r t h e r commands, w i l l

Network D i g i t a l be r e q u i r e d f o r t h e Agena target v e h i c l e . Command System support w i l l be continued throughout t h e Agena

target v e h i c l e b a t t e r y lifetime. The Texas, Cape Kennedy, Grand Bahama, Grand Turk, Antigua, and Bermuda s i t e s will not be manned by f l i g h t cont r o l l e r s . A l l u p l i n k data command t r a n s m i s s i o n s through these s i t e s w i l l be remoted i n r e a l time from Houston Cont r o l Center. I n a d d i t i o n t o real-time commands and onboard clock update commands, t h e following d i g i t a l i n s t r u c t i o n s may be sent:

a.

Gemini s p a c e c r a f t 1. 2.

b.

P r e r e t r o w i t h maneuver P r e r e t r o without maneuver -more

-

Agena Target Vehicle

.

1. 2

Maneuver Ephemeris

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3. 4.

5. 6.

-

O r b i t a l navigation 3. Engine burn time Maneuver Rendezvous Accelerometer e r r o r c o r r e c t i o n s

Spacecraft Communications A l l MSFN s t a t i o n s having both HF and UHF spacecraft communications can be c o n t r o l l e d e i t h e r by the s t a t i o n or by remote ( t o n e ) keying from Houston Mission Control Cent e r and from Goddard.

The following s i t e s a r e not scheduled t o have a command communicator (Cap Com) and w i l l be remoted t o Houston Mission Control Center: Cape Kennedy; Grand Bahama I s l a n d ; Tananarive, Malagasy Republic; Kano, Nigeria; Bermuda; Grand Turk I s l a n d ; P t . Arguello, Calif.; Antigua I s l a n d ; Ascension I s l a n d ; Canton I s l a n d ; USNS Range Tracker, and the voice r e l a y aircraft

Spacecraft Systems Support The Gemini s p a c e c r a f t communications systems (antennas, beacons, voice communications, telemetry t r a n s m i t t e r s , recovery l i g h t , and d i g i t a l command) allows radar t r a c k i n g of t h e s p a c e c r a f t , two-way voice communications between t h e ground and t h e s p a c e c r a f t and from a s t r o n a u t t o a s t r o n a u t ; ground command of the s p a c e c r a f t ; TM systems data transmiss i o n , and postlanding and recovery data transmission. The s o l e link between the ground and t h e Gemini s p a c e c r a f t i s provided by these systems. The Agena target v e h i c l e communications systems (ant e n n a s beacons, telemetry transmitters, and d i g i t a l command system) allows radar t r a c k i n g of t h e v e h i c l e from both the ground and t h e Gemini s p a c e c r a f t . Ground s t a t i o n and Gemini s p a c e c r a f t command t o t h e Agena a l s o are accomplished through t h i s system.

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. Agena Target Vehicle On-Board Systems supported by Network Stations.

Gemini Spacecraft On-Board Systems Support by Network Stations

Telemetry Real T i m e ) Telemetry [Dump) L-Band Transponder S-Band Transponder C-Band Transponder Command Receiver (Range S a f e t y ) Command Receiver (Command Control)

Reentry Module UHF ( v o i c e ) xmit -Rcv Reentry Module HF ( v o i c e ) xmit -Rcv Reentry Module Telemetry (Real Time) Reentry Module Telemetry Dump) Reentry Module Telemetry [Backup) Adapter Package L-Band Radar (Telemetry Readouts) Reentry Module C-Band Transponder Adapter Package C-Band Transponder Adapter Package Acquisition Aid Beacon Adapter Package D i g i t a l Cnmmarrd Syte!?!

Reentry Module UHF Recovery Beacon Ground Communications The NASA Communications Network (NASCOM) used f o r Gemini10 w i l l be used f o r Gemini 11. Shore s t a t i o n s f o r USNS Rose Knot and USNS Coastal Sentry Ship support w i l l be based upon t h e mission-designated s h i p p o s i t i o n s and p r e d i c t e d KF radio propagation conditions.

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.

-

Network R e s p o n s i b i l i t y Manned S p a c e c r a f t Center (MSC). The d i r e c t i o n and mission c o n t r o l o f the Network immediately preceding and d u r i n g a mission s i m u l a t i o n o r an a c t u a l mission i s r e s p o n s i b i l i t y o f the MSC. Goddard Space P l i g h t Center. The NASA Office o f Tracking and Data A c q u i s i t i o n has c e n t r a l i z e d the r e s p o n s i b i l i t y f o r the planning, Implementation, and t e c h n i c a l o p e r a t i o n s o f Goddard Space F l i g h t Center. Technical o p e r a t i o n i s d e f i n e d as the o p e r a t i o n , maintenance, modification, and augmentation o f t r a c k i n g and data a c q u i s i t i o n f a c i l i t i e s t o f u n c t i o n as a n i n s t r u m e n t a t i o n network i n response t o mission requirements. About 370 persons d i r e c t l y support t h e network a t Goddard; c o n t r a c t o r personnel bring the t o t a l network l e v e l t o some 1500. Department o f Supply, A u s t r a l i a . The Department o f Supply, Commonwealth o f A u s t r a l i a , is r e s p o n s i b l e f o r t h e maintenance and o p e r a t i o n of t h e NASA s t a t i o n a t Carnarvon, A u s t r a l i a . C o n t r a c t u a l arrangements and agreements d e f i n e t h i s cooperative effort. Department of Defense (DOD). The DOD i s r e s p o n s i b l e f o r the maintenance and o p e r a t i o n a l c o n t r o l of those DOD assets and f a c i l i t i e s r e q u i r e d t o support P r o j e c t Gemini. These i n clude network s t a t i o n s a t t h e Eastern Test Range, Western T e s t Range, White Sands Range, the A i r Proving Ground Center, and t h e t r a c k i n g and t e l e m e t r y ships.

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-35ABORT AND RECOVERY

Crew Safety Every Gemini System a f f e c t i n g crew safety has a backup f e a t u r e . The Malfunction Detection System aboard the launch v e h i c l e warns the crew of a malfunction i n time f o r escape. There a r e three modes of escape: MODE I

E j e c t i o n seats and p e r s o n a l parachutes, used a t ground l e v e l and during first 50 seconds of powered f l i g h t , o r during d e s c e n t a f t e r reentry.

MODE I1

Retrorocket9 salvo f i r e d a f t e r engine s h u t down i s commanded.

MODE I11

Normal s e p a r a t i o n from launch v e h i c l e u s i n g OAMS t h r u s t e r s , then normal r e e n t r y u s i n g computer

.

Except f o r Mode I, s p a c e c r a f t s e p a r a t e s from Gemini Launch Vehicle, t u r n s blunt-end forward, then completes r e e n t r y and landing with crew aboard. S u r v i v a l Package S u r v i v a l gear, mounted on each e j e c t i o n s e a t and a t t a c h e d t o the a s t r o n a u t ' s parachute harnesses by nylon l i n e , weighs 23 pounds. Each a s t r o n a u t has:

3.5 pounds of d r i n k i n g water; Machete; One-man l i f e raft, 3 by 5* f e e t , with C02 b o t t l e f o r i n f l a t i o n , s e a anchor,

dye markers, nylon sun bonnet; S u r v i v a l l i g h t ( s t r o b e ) , w i t h flashlight, s i g n a l mirror, compass, sewing k i t , 14 f e e t of nylon l i n e , c o t t o n balls and s t r i k e r , halazone tablets, a w h i s t l e , and b a t t e r i e s f o r power; S u r v i v a l r a d i o , w i t h homing beacon and voice transmission and r e c e p t i o n ; Sunglasses; D e s a l t e r k i t , with b r i c k e t t e s enough t o d e s a l t e i g h t p i n t s of seawater; Medical k i t , c o n t a i n i n g s t i m u l a n t , pain, motion s i c k n e s s and a n t i b i o t i c tablets and a s p i r i n , p l u s i n j e c t o r s f o r p a i n and motion s i c k n e s s . Planned and Contingency Landing Areas

There are two types of landing a r e a s f o r Gemini, planned where recovery f o r c e s are pre-positioned t o recover s p a c e c r a f t and crew w i t h i n a s h o r t time - and contingency, r e q u i r i n g s p e c i a l s e a r c h and r e s c u e techniques ahd a longer recovery period. -more -

-36Planned Landing Areas PRIMARY

West Atlantic where the primary recovery a i r c r a f t c a r r i e r is pre-positioned.

SECONDARY

E a s t Atlantic, West Pacific and Mid-Pacific areas where ships are deployed.

LAUNCH SITE

Off-the-pad abort o r abort during early phase o f f l i g h t , Includes an area about 41 miles seaward from Cape Kennedy, 3 miles toward Banana River f r o m Complex 19.

LAUNCH ABORT

Abort during powered f l i g h t , extending from 41 miles a t sea from Cape Kennedy t o west coast o f Africa.

Contingency Landing Areas All the areas beneath the spacecraft's ground track except those designated Planned Landing Areas are Contingency Landing Areas, requiring aircraft and pararescue support f o r recovery

within 18 hours from splashdown.

Recovery forces are provided by the m i l i t a r y services under t h e operational control o f the Department of Defense Manager f o r Manned Space Flight Support Operations.

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-37 SPACECRAFT AND LAUNCH VEHICLES

Gemini Spacecraft The Gemini s p a c e c r a f t is c o n i c a l , 18 f e e t , 5 inches long, 10 f e e t i n diameter a t i t s base and 39 inches i n diameter a t the top. I t s two major s e c t i o n s a r e the r e e n t r y module and the a d a p t e r s e c t i o n . Reentry Module

f

The r e e n t r y module is 11 f e e t high and 7 f e e t i n diameter a t i t s base. It has t h r e e main s e c t i o n s : (1 rendezvous and recovery (R&R), ( 2 ) r e e n t r y c o n t r o l (RCS), and ( 3 ) cabin. 'Rendezvous and recovery s e c t i o n i s t h e forward (small) end of t h e s p a c e c r a f t , containing- drogue, p i l o t and main parac h u t e s and radar. Reentry c o n t r o l s e c t i o n i s between R&R and c a b i n s e c t i o n s and c o n t a i n s f u e l and o x i d i z e r tanks, valves, tubing and two r i n g s o f e i g h t a t t i t u d e c o n t r o l t h r u s t e r s each f o r c o n t r o l d u r i n g r e e n t r y . A parachute a d a p t e r assembly is Included f o r main parachute attachmeht. Cabin s e c t i o n between RCS and adapter s e c t i o n , houses t h e crew s e a t e d side-by-side, their instruments and c o n t r o l s . Above each s e a t i s the hatch. Crew compartment i s p r e s s u r i z e d t i t a n i u m h u l l . Equipment n o t r e q u i r i n g p r e s s u r i z e d environment i s l o c a t e d between p r e s s u r e h u l l and o u t e r beryllium s h e l l which i s corrugated and shingled t o provide aerodynamic and h e a t p r o t e c t i o n . Dish-shaped h e a t s h i e l d forms the large end of cabin section. Adapter Section. The a d a p t e r is 7+$f e e t high and 10 feet i n d i a m e t e r a t i t s base, containing r e t r o g r a d e and equipment sections.

Retrograde s e c t i o n c o n t a i n s f o u r s o l i d r e t r o g r a d e r o c k e t s and part o f t he r a d i a t o r f o r the c o o l i n g system. Equipment Section contains f u e l c e l l s f o r e l e c t r i c a l power, fuel f o r the o r b i t a t t i t u d e and maneuver system ( O M S ) , primary oxygen f o r t h e environmental c o n t r o l system (ECS) , crogenlc oxygen and hydrogen for f u e l c e l l system. It a l s o s e r v e s as a r a d i a t o r f o r the cooling system, a l s o contained in the equipment s e c t i o n . NOTE: The equipment s e c t i o n i s j e t t i s o n e d Immediately b e f o r c t r o r o c k e t a are f i r e d f o r r e e n t r y . The r e t r o g r a d e s e c t i o n i s j e t t i s o n e d after r e t r o s a r e f i r e d .

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-38 E l e c t r i c Power System *

Gemini 10 will c a r r y two h e 1 c e l l s f o r the primary power supply during launch and o r b i t , The c e l l s c o n s i s t o f t h r e e s t a c k s of 32 I n d i v i d u a l c e l l a . Cryogenic l i q u i d oxygen and hydrogen r e a c t t o product e l e c t r i c a l energy.

Four 45-amp-hour b a t t e r i e s w i l l also be c a r r i e d I n t h e s p a c e c r a f t t o I n s u r e a continuous power supply durlng r e e n t r y and landing. They will a l s o be used during prelaunch and launch, i n conjunction with t h e h e 1 c e l l s ,

Three 15-amp-hour squib b a t t e r i e s w i l l be used I n the r e e n t r y s e c t i o n t o r a l l squib-actuated pyrotechnic S e p a r a t i n g d u r i n g the mlsslon. Propellant Usable: pounds

940 pounds,

Budgeted, no d i s p e r s i o n s :

808

Rendezvous Radar

--

Purpoae t o measure range, range r a t e , and b e a r i n g a n g l e t o Agena so crew can determine maneuvers necessary f o r rendezvous ,

--

Location small end of s p a c e c r a f t on forward f a c e o f rendezvous and recovery s e c t i o n , S i z e -- less than two cubic f e e t . Weight -- l e s s than 70 pounds. Power Requirement

--

l e s s than 80 watts.

--

A u x i l i a r y Tape Memory ( Am) The Auxiliary Tape Memory i s a &track magnetic tape r e c o r d e r which s t o r e s l2,5OO,OOO b i t s . Data p a r i t y , clocking, and computer processing b i t s are recorded i n t r i p l i c a t e . The ATM provides t r i p l e redundant storage f o r approximately l,l7O,OOO b i t s f o r e x t e r n a l s t o r a g e of computer programs. The computer has onboard program capability f o r launch, rendezvous, and r e e n t r y and has 156,000 b i t s of program storage. The ATPI is a hermetically-sealed u n i t which c o n t a i n s a mechanical t r a n s p o r t assembly mounted on v i b r a t i o n I s o l a t o r s , and an e l e c t r o n i c assembly containing t h e power supply, c o n t r o l l o g i c , r e c o r d l o g i c , and playback l o g i c .

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-39The tape t r a n s p o r t i s a f l a n g e l e s s r e e l , p e r i p h e r a l d r i v e u n i t which c o n t a i n s 525 f e e t of one-inch magnetic tape. The magnetic t a p e is driven by a n e n d l e s s , seamless 3/4-inch wide rqylar b e l t . The p e r i p h e r a l d r i v e b e l t i s i n t u r n d r i v e n by two capstans coupled by rqylar b e l t s . By n o t exposing t h e magnetic t a p e t o d r i v e s t r e s s e s , i t s u s e f u l l i f e i s extended. The u n i t weighs 26 pounds, c o n t a i n s 700 cubic Inches, and u s e s approximately 18 watts. The ATM i s b u i l t by Raymond Engineering L a b o r a t o r i e s , Middletown, C o n n . , under c o n t r a c t t o t h e I n t e r n a t i o n a l Business Machines, E l e c t r o n i c s Systems Division, Owego, N.Y., f o r t h e prime Gemini c o n t r a c t o r , McDonnell A i r c r a f t Corp.

Gemini Launch Vehicle The Gemini Launch Vehicle is a modified U.S. A i r Force T i t a n IS i n t e r c o n t i n e n t a l b a l l i s t i c m i s s i l e c o n s i s t i n g o f two s t a g e s , i d e n t i c a l t o the launch v e h i c l e s used i n previous Gemini f l i g h t s

.

FIRST STAGE

SECOND STAGE

HEIGHT

63 f e e t

27 f e e t

DIAMETER

10 feet

10 f e e t

THRUST

4 30,000 pounds (two engines)

100,000 pounds

FUEL

50-50 blend o f monomethyl hydrazine and unsymmetrical-dimethyl hydrazine

OXIDIZER

Nitrogen t e t r o x i d e (Fuel i s hypergolic, i g n i t e s s ontaneously upon c o n t a c t w i t h oxidizer

(one engine)

.P

feet.

O v e r a l l height o f launch v e h i c l e and s p a c e c r a f t I s 109 Combined weight is about 340,000 pounds.

Modifications t o T i t a n I1 f o r use as the Gemini Launch Vehicle include: 1. Malfunction d e t e c t i o n system added t o d e t e c t and t r a n s m i t b o o s t e r performance Information t o the crew. 2. Back-up f l i g h t c o n t r o l system added t o provide a secondary system i f primary system fails.

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-J+O-

added

3.

Radio guidance s u b s t i t u t e d f o r i n e r t i a l guidance.

4.

Retro and v e r n i e r r o c k e t s d e l e t e d .

5.

New second s t a g e equipment t r u s s added.

6.

.

New second s t a g e forward o x i d i z e r s k i r t assembly

7.

T r a j e c t o r y t r a c k i n g requirements s i m p l i f i e d .

8.

E l e c t r i c a l h y d r a u l i c and instrument systems modified.

Gemini Launch Vehicle program management f o r NASA i s under the d i r e c t i o n of t h e Space Systems Division of t h e A i r Force Systems Command. Agena Target Vehicle The Agena t a r g e t v e h i c l e f o r Gemini 11 i s a m o d i f i c a t i o n o f the U.S. A i r Force Agena D upper s t a g e , similar t o the space v e h i c l e s which helped p r o p e l Ranger and Mariner s p a c e c r a f t t o the Moon and p l a n e t s .

It a c t s as a s e p a r a t e s t a g e of the.Atlas/Agena launch v e h i c l e , p l a c i n g itself i n t o o r b i t with i t s main propulsion, and can be maneuvered e i t h e r by ground c o n t r o l o r the G e m i n i crew. Height ( L i f t o f f )

36.3 f e e t

I n c l u d i n g shroud

Length ( o r b i t )

26 f e e t

Minus shroud and adapter

Diameter

5 feet

Weight

7,000 pounds

I n o r b i t , fueled

Thrust

16,000 pounds 400 pounds

Primary propulsion

32 pounds

Secondary Engines, Unit I1 Secondary Engines, Unit I

Fuel

UDMH (Unsymmetrical Dimethyl Hydrazine)

Oxidizer

I R F N A ( I n h i b i t e d Red Fuming N i t r i c Acid) in primary propulsion system; MON (Mixed Oxides of Nitrogen) I n secondary propuls i o n system

Combustion

IRFNA and UDMH a r e hypergolic, i g n i t e on c o n t a c t .

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P r i m a r y and secondary propulsion systems a r e r e s t a r t a b l e , Main engine p l a c e s Agena i n t o o r b i t and i s used for l a r g e o r b i t changes, Secondary system, two 200-pound-thrust, a f t - f i r i n g engines, are f o r small v e l o c i t y changes. Two 16-pound-thrust, a f t - f i r i n g t h r u s t e r s are f o r u l l a g e o r i e n t a t i o n and v e r n i e r adjustments, A t t i t u d e c o n t r o l ( r o l l , p i t c h , yaw) i s accomplished by six n i t r o g e n j e t s mounted on Agena a f t end,

Modifications t o Agena for use as Gemini rendezvous spacec r a f t include: 1. Docking c o l l a r and equipment t o permit mechanical conn e c t i o n with Gemini during f l i g h t ,

2,

Radar transponder compatible w i t h Gemini radar,

3. Displays and instrumentation, p l u s s t r o b e l i g h t s f o r v i s u a l l y l o c a t i n g and i n s p e c t i n g Agena before docking, 4,

Secondary propulsion system f o r small o r b i t a l changes,

5. A u x i l i a r y equipment rack for s p e c i a l rendezvous equipment and telemetry,

6, Command c o n t r o l equipment t o allow c o n t r o l by Gemini 11 crew o r ground c o n t r o l l e r s , 7. M u l t i - r e s t a r t a b l e engine t o provide i n - o r b l t maneuver capability, Agena program management f o r NASA is under the d i r e c t i o n of t h e Space Systems Division o f the A i r Force Systems Command.

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-42-

S t a t i c Charge Device 7

Three p r o t r u d i n g f l e x i b l e copper f i n g e r s a r e i n s t a l l e d on t h e Agena docking cone t o make first c o n t a c t w i t h the s p a c e c r a f t . Any charge w i l l be c a r r i e d t o a ground i n t h e Agena and d i s s i p a t e d a t t h e c o n t r o l l e d r a t e . An e l e c t r o s t a t i c charge monitoring device i s a l s o i n s t a l l e d i n the t a r g e t docking a d a p t e r t o measure the p o t e n t i a l o r d i f f e r e n c e i n charge between t h e two v e h i c l e s . Atlas Launch Vehicle

The Atlas Standard modified U.S. A i r Force missile, similar t o t h e Mercury Astronauts i n t o

Launch Vehicle i s a refinement of the A t l a s intercontinental b a l l i s t i c launch v e h i c l e which placed P r o j e c t

orbit.

Atlas 1s a 13 -stage Standard Launch Vehicle, i g n i t i n g all t h r e e main engines on the pad, then dropping o f f t h e two outboard b o o s t e r engines a t s t a g i n g , allowing t h e s i n g l e s u s t a i n e r engine t o continue t h r u s t i n g a t a l t i t u d e , aided by two small v e r n i e r engines. Height

77 f e e t

Minus Agena Payload

Diameter

16 f e e t

Lower Booster S e c t i o n

10 f e e t

Tank S e c t i o n s

5 f e e t , 10 inches Tapered Upper End Weight

260 ,000 pounds

Fully fueled, minus Agena payload

Thrust

390,000 pounds

Total a t l i f t o f f TWO b o o s t e r ( o u t e r ) engines

330J000 57,000 pounds

One S u s t a i n e r ( c e n t e r ) engine

Two small v e r n i e r engines f o r t r a J e c t o r y and f i n a l v e l o c i t y c o n t r o l

Balance

a hydrocarbon resembling kerosene

Fuel

RP-1,

Oxidizer

Liquid oxygen a t

Combustion

Unlike T i t a n ' s hypergolic, spontaneous i g n i t i o n , Atlas combustion i s achieved by f o r c i n g p r o p e l l a n t s t o chambers under p r e s sure, burning them i n gas g e n e r a t o r s which d r i v e p r o p e l l a n t pump t u r b i n e s . -more-

+297 degrees F.

-43Modifications t o the A t l a s Standard Launch Vehicle f o r the Gemini 11 mission include: 1,

Speclal autopilot system f o r rendezvous mission.

,2. Improved propellant u t i l i z a t i o n system t o assure simultaneous depletion of both fuel and oxidizers.

3. Increased thickness of Atlas structure f o r support of Agena upper stage. 4.

Simplified pneumatic system.

5. Retrorockets moved from e x t e r i o r equipment pods t o upper interstage adapter section. 6. Uprated MA-5 propulsion system (used on later Mercury flights. ) 7.

Modular telemetry kit tailored f o r each mission.

Atlas Standard Launch Vehicle program management f o r NASA i s under the direction of the Space Systems Division of the A i r Force Systems Command,

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CREW BIOGRAPHIES NAME:

Charles Conrad, Jr.

BIRTHPLACE AND DATE : Philadelphia, Penn., June 2, 1930. EDUCATION:

Bachelor of Science degree, a e r o n a u t i c a l engineering, Princeton University.

MARITAL STATUS: CHILDREN:

Married t h e former Jane DuBose of Uvalde, Tex.

Peter, Dec. 25, 1954; Thomas, May 3, 1957; Andrew, 1959; Christopher, Nov. 26, 1960.

Apr. 30,

SPECIAL AWARDS :

NASA Exceptional Service Medal and Navy

Astronaut l;/ings.

PROFESSIONAL ORGANIZATIONS:

Member, American I n s t i t u t e of Aeronautics and Astronautics; Member, S o c i e t y of Experimental

Test P i l o t s .

EXPERIENCE:

He e n t e r e d t h e Navy following h i s graduation from P r l n c e t o n Unlveralty and became a naval a v i a t o r , He l a now a Navy commander, Conrad attended t h e Navy Test P i l o t School a t Patuxent River, Md., and following completion of t h a t course was a p r o j e c t t e s t p i l o t i n t h e armaments t e s t d i v i s i o n there. He a l s o served a t Patuxent as a f l i g h t i n s t r u c t o r and perfonmance engineer a t t h e T e s t P i l o t School. He served a s a F4H f l i g h t i n s t r u c t o r and as a s a f e t y o f f i c e r f o r F i g h t e r Squadron 96 a t the Miramar, Cal. Naval A i r S t a t i o n . H e was p i l o t on Gemini 5 f l i g h t which took p l a c e

i n August 1965.

He has logged more t h a n 3,200 f l y i n g hours, i n cluding more than 2,500 hours i n j e t a i r c r a f t . CURRENT ASSIGNMENT: Conrad was i n t h e second group of a s t r o n a u t s s e l e c t e d by NASA i n September 1962. I n a d d i t i o n t o part i c i p a t i n g i n t h e o v e r a l l a s t r o n a u t t r a i n i n g program, Conrad was command p i l o t f o r backup crew on Gemini 8.

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-45-

NAME:

Richard F. Gordon, Jr.

BIRTHPLACE AND DATE: EDUCATION:

Bachelor of Science degree i n chemistry, U n i v e r s i t y of Washington.

MARITAL STATUS:

CHILDREN:

EXPERIENCE:

Seattle, Wash., Oct. 5, 1929.

Married t o the former Barbara J. F i e l d of Freeland, Wash.

Carleen, July 8, 1954; Richard, Oct. 6 , 1955. Lawrence, December 18, 1957; Thomas, Mar. 25, 1959; James, Apr, 26, 1960; Diane, Apr. 23, 1961. Gordon, a United S t a t e s Navy l i e u t e n a n t commander, e n t e r e d a v i a t i o n t r a i n i n g i n 1951. After r e c e i v i n g h i s wings as a Naval Aviator i n 1953, he a t t e n d e d All-Weather F l i g h t School and received jet t r a n s i t i o n a l t r a i n i n g before r e p o r t i n g t o an a l l weather squadron a t the J a c k s o n v i l l e , Fla., Naval A i r S t a t i o n . He a t t e n d e d t h e Navy’s Test P i l o t School a t Patuxent River, Md., i n 1957, and served as a f l i g h t t e s t p i l o t u n t i l 1960. During t h i s t o u r of duty, he performed f l i g h t t e s t work on t h e F8U Crusader, F l l F T i g e r c a t , FJ Fury, A4D Skyhawk, and was t h e f i r s t p r o j e c t t e s t p i l o t f o r the F4H Phantom 11. H e served w i t h F i g h t e r Squadron 121 a t the Miramar, C a l . , Naval A i r S t a t i o n as a f l i g h t i n s t r u c t o r i n t h e F4H and p a r t i c i p a t e d i n t h e I n t r o d u c t i o n of t h a t a i r c r a f t t o t h e A t l a n t i c and P a c i f i c f l e e t s . H e was f l i g h t s a f e t y o f f i c e r , a s s i s t a n t o p e r a t i o n s o f f i c e r , and ground t r a i n i n g o f f i c e r f o r F i g h t e r Squadron 96 a t Miramar.

I n May 1961, Gordon won t h e Bendix Trophy Race from Los Angeles t o N e w York, e s t a b l i s h i n g a new speed record of 869.74 miles p e r hour and a t r a n s c o n t i n e n t a l speed r e c o r d of 2 hours 47 minutes. H e was a s t u d e n t a t t h e U.S. Naval Postgraduate School a t Monterey, Cal. H e has logged more t h a n 3,000 hours f l y i n g t i m e , more than 2,500 h o u r s i n j e t a i r c r a f t .

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-46 CURRENT ASSIGNMENT: In October 1963, Gordon was named one of the third group of astronauts chosen by NASA. In addition to the regular astronaut training, he is responsible for monitoring cockpit layouts, instrument displays and pilot controls to insure that systems displays are appropriately integrated into cockpit panels. He was selected as the pilot f o r the backup crew on the Gemini 8 flight.

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NAME:

Neil A. Armstrong

BIRIXPLACE AND DATE: EDUCATION:

Bachelor of Science degree i n Aeronautical Engineeri n g from Purdue University.

MARITAL STATUS: CHILDREN:

Wapakoneta, Ohio, August 5, 1930.

Married former Janet Shearon of Evanston, I l l i n o i s .

Eric, June 30, 1957; Mark, April 8, 1963.

SPECIAL AWARDS:

Recipient of the 1962 I n s t i t u t e of Aerospace Sciences Octave Chanute Award, NASA Except i o n a l Service Medal,

PROFESSIONAL ORGANIZATIONS:

EXPERIENCE:

Charter member of t h e Society of Experimental Test P i l o t s ; assoc i a t e fellow of t h e American Ins t i t u t e of Aeronautics and Astronautics; member of t h e Soaring Society of America.

Armstrong was a naval a v i a t o r from 1949 t o 1952 and flew 78 combat missions during t h e Korean a c t i o n . He joined NASA's L e w i s Research Center i n 1955 (then NACA L e w i s F l i g h t Propulsion Laboratory) and l a t e r t r a n s f e r r e d t o the NASA High Speed F l i g h t S t a t i o n a t Edwards AFB, California, as an aeron a u t i c a l research p i l o t f o r NACA and NASA. A s an a e r o n a u t i c a l research p i l o t , he was an X-15 p r o j e c t p i l o t , f l y i n g t h a t a i r c r a f t t o over 200,000 f t . and approximately 4,000 mph. Other f l i g h t t e s t work included p i l o t i n g t h e X - 1 rocket a i r plane, the F-100, F-101, F-102, F5D, B-47, and paraglider.

He has logged more than 3,400 hours f l y i n g time, including 1,900 h o u r s i n j e t a i r c r a f t .

CURRENT ASSIGNMENT: Armstrong was s e l e c t e d as an astronaut by NASA i n September 1962. I n a d d i t i o n t o p a r t i c i p a t i n g i n a l l phases of t h e a s t r o n a u t t r a i n i n g program, he served as command p i l o t of t h e backup crew f o r the GT-5 f l i g h t . He was command p i l o t f o r t h e Gemini 8 mission, March 16, 1960.

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-48 -

NAME: W i l l i a m A. Anders BIRTHPLACE AND DATE: EDUCATION:

Bachelor o f Science degree from the U n i t e d S t a t e s Naval Academy; Master of Science degree i n Nuclear Engineering from the A i r Force I n s t i t u t e o f Technology, Wright-Patterson AFB, Ohio; a d d i t i o n a l graduate work a t Ohio S t a t e University.

MARITAL STATUS: CHILDREN:

Hong Kong, October 17, 1933.

Married t o the former V a l e r i e E. Hoard of Lemon Grove, C a l ,

Alan, February 1957; Glen, J u l y 1958; Gayle, December 1960; Gregory, December 1962; E r i c , J u l y 1964.

PROFESSIONAL ORGANIZATIONS:

EXPERIENCE:

Member, Tau Beta P i , the American Nuclear Society, and t h e American Geophysical Union.

Anders, a n A i r Force Captain, was commissioned i n the A i r Force on graduation from t h e 'Naval Academy, then received h i s f l i g h t t r a i n i n g . He served as a nuclear engineer and i n s t r u c t o r p i l o t a t the A i r Force Weapons Laboratory, K i r t l a n d A i r Force Base, New Mexico. He a l s o had t e c h n i c a l management r e s p o n s i b i l i t y f o r r a d i a t i o n s h i e l d i n g and r a d i a t i o n e f f e c t s programs.

Anders has logged more than 2,500 hours f l y i n g time, i n c l u d i n g 2,200 hours i n j e t a i r c r a f t . CURRENT ASSIGNMENT: Anders was s e l e c t e d as an a s t r o n a u t by NASA i n t h e group i n t e g r a t e d i n t o the program i n October 1963. I n a d d i t i o n t o p a r t i c i p a t i n g i n the a s t r o n a u t t r a i n i n g program, he has s p e c i f i c r e s p o n s i b i l i t i e s i n envlronmental systems, r a d i a t i o n and thermal p r o t e c t i o n .

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-49PREVIOUS GEMINI FLIGHTS

Gemini 1, Apr. 8, 1964 Unmanned o r b i t a l f l i g h t , using f i r s t production spacec r a f t , t o test Gemini launch v e h i c l e performance and a b i l i t y of launch v e h i c l e and s p a c e c r a f t t o withstand launch environment. S p a c e c r a f t and second s t a g e launch v e h i c l e o r b i t e d f o r about f o u r days. No recovery attempted. Gemini 2, Jan. 19, 1965 Unmanned b a l l i s t i c f l i g h t t o q u a l i f y s p a c e c r a f t reentry h e a t p r o t e c t i o n and s p a c e c r a f t systems. Delayed three times by adverse weather, i n c l u d i n g hurricanes Cleo and Dora. December launch attempt terminated a f t e r malfunction detect i o n ' s y s t e m shut e n g i n e s down because of h y d r a u l i c component f a i l u r e . Spacecraft recovered a f t e r b a l l i s t i c r e e n t r y over A t l a n t i c Ocean. Gemini 3, Mar. 23, 1965 F i r s t manned f l i g h t , with Astronauts V i r g i l I. Grissom and John W. Young as crew. Orbited E a r t h t h r e e times i n f o u r hours, 53 minutes. Landed about 50 m i l e s s h o r t of planned l a n d i n g a r e a i n A t l a n t i c because s p a c e c r a f t d i d not provide expected l i f t during r e e n t r y . F i r s t manned s p a c e c r a f t t o maneuver o u t of plane, a l t e r i t s own o r b i t . Grissom, who made s u b o r b i t a l Mercury f l i g h t , i s t h e first rr,an t o f l y i n t o space twice.

Gemini 4, June 3-7, 1965 Second manned Gemini f l i g h t completed 62 r e v o l u t i o n s and landed i n primary A t l a n t i c recovery a r e a a f t e r 97 hours, 56 minutes of f l i g h t . Astronaut James A. McDivitt was command p i l o t . Astronaut Edward H. White I1 was p i l o t , accomplished 21 minutes of E x t r a - S h i c u l a r A c t i v i t y (EVA), using a hand-held maneuveri n g u n i t f o r t h e f i r s t t i m e i n space. Near-rendezvous w i t h GLV second s t a g e was not accomplished a f t e r use of pre-planned amount of f u e l f o r the maneuver. Malfunction i n I n e r t i a l Guidance System required crew t o perform z e r o - l i f t r e e n t r y . Gemini 5, Aug. 21-29,

1965

Astronauts L. Gordon Cooper and Charles ( P e t e ) Conrad, Jr., c i r c l e d the Earth 120 times i n seven days, 22 hours a n d 56 minutes. Cooper was f i r s t t o make two o r b i t a l space f l i g h t s . F a i l u r e of oxygen h e a t i n g system i n f u e l c e l l supply system t h r e a t e n e d m i s s i o n during f i r s t day of f l i g h t , but c a r e f u l use of e l e c t r i c a l power, and e x c e l l e n t o p e r a t i o n a l management of f u e l c e l l s by b o t h crew a n d ground personnel, permitted crew t o complete f l i g h t s u c c e s s f u l l y . Spacecraft landed about 100 m i l e s from primary A t l a n t i c recovery v e s s e l because of -more-

-50-

erroneous base-line information programmed i n t o onboard comp u t e r , although computer i t s e l f performed as planned. Plan t o rendezvous with a transponder-bearing pod c a r r i e d a l o f t by Gemini 5 was cancelled because of problem with f u e l c e l l oxygen supply. G e m i n i 7, Dec. 4-18,

1965

H o l d s c u r r e n t world record for manned space f l i g h t as Command P i l o t Frank Borman and P i l o t James Love11 completed 206 r e v o l u t i o n s of t h e Earth i n 13 days, 18 hours, and 35 minutes. On the 12th day of t h e i r f l i g h t , the Gemini 7 served as target for the Gemini 6 s p a c e c r a f t on the first succ e s s f u l rendezvous i n space. I n proving man's a b i l i t y t o o p e r a t e i n space f o r a period of up t o two weeks, the crew of Gemini 7 c a r r i e d out an ambitious l i s t of 20 experiments i n c l u d i n g a l l medical experiments i n the G e m i n i program, a t e s t of laser communications from space, and visual acuity. The Gemini 7 experienced continuous d i f f i c u l t y with the d e l t a p l i g h t on the f u e l c e l l system. However, the system performed for t h e e n t i r e mission. The only o t h e r problem encountered was the temporary malfunction of a yaw thruster on t h e s p a c e c r a f t . G e m i n i 7 l a n d e d i n the A t l a n t i c on Dec. 18, making a cont r o l l e d reentry which brought i t w i t h i n 10 miles of the recovery carrier.

Gemini 6, Dec. 15-16, 1965 The f i r s t s p a c e c r a f t t o rendezvous with a n o t h e r spacec r a f t i n o r b i t . Command p i l o t Walter S c h i r r a and P i l o t Thomas S t a f f o r d flew t h e i r s p a c e c r a f t from a 100-by-167 m i l e o r b i t i n t o a 185-mile c i r c u l a r o r b i t , rendezvousing w i t h Gemini 7 over t h e P a c i f i c Ocean a t 5 hrs. 47 min. a f t e r l i f t o f f . It demonstrated one of t h e major o b j e c t i v e s of the program, and a l s o paved t h e way for Apollo Lunar O r b i t Rendezvous i n the accomplishment of t h e f i r s t manned l a n d i n g on the Moon.

Gemini 6 was launched on i t s h i s t o r i c rendezvous m i s s i o n on the t h i r d attempt. On the f i r s t try, Oct. 25, the Agena Target Vehicle was destroyed by a hard s t a r t of i t s primary propulsion system. On Dec. 12, t h e Gemini Launch Vehicle f a i l e d to achieve l i f t o f f when an e l e c t r i c a l plug connecting t h e rocket w i t h the pad e l e c t r i c a l system dropped o u t prematurely.

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-51Gemini 8. March 16. 1966 Astronaut Neil AImStrongJ command p i l o t , and David S c o t t , p i l o t , completed t h e f i r s t rendezvous a n d docking w i t h an Agena s p a c e c r a f t launched i n t o o r b i t approximately 100 minutes e a r l i e r , The planned three-day f l i g h t was terminated near the end of t h e s i x t h revolution a f t e r an e l e c t r i c a l s h o r t c i r c u i t i n the Gemini spacecraft caused continuous f i r i n g of a roll t h r u s t e r . The crew undocked from the Agena and a c t i v a t e d the r e e n t r y r e a c t i o n c o n t r o l system t o r e g a i n c o n t r o l of the s p a c e c r a f t . The crew made a guided r e e n t r y and l a n d e d i n the P a c i f i c Ocean 500 miles east of t h e i s l a n d of Okinawa a n d only approximately f i v e miles from the aiming p o i n t . A recovery a i r c r a f t was on the scene before splashdown t o parachute a recovery team t o t h e s p a c e c r a f t . The crew and s p a c e c r a f t were picked up by a Navy d e s t r o y e r approximately three hours a f t e r splashdown.

Qemini 9, June 3-6, 1966 Three s e p a r a t e rendezvous with t h e Augmented Target Docking Adapter and a 2-hour 10-minute extra-vehicular a c t i v i t y were t h e primary accomplishments of t h e lgeventh manned Gemini f l i g h t . Col. Thomas P. Stafford, a v e t e r a n of the f i r s t U.S. rendezvous mission i n Gemini 6, was command p i l o t f o r t h e +day f l i g h t . Eugene Cernan was p i l o t and performed t h e EVA. The f l i g h t , o r i g i n a l l y scheduled f o r May 17, was postponed two weeks when the Atlas b o o s t e r which was launching the Agena Target Vehicle developed a n e l e c t r i c a l s h o r t c i r c u i t which caused i t s e n g i n e s t o gimbal hard over a n d a b o r t t h e f l i g h t . The ATDA was s u b s t i t u t e d f o r the Agena and was launched on June 1. Gemini 9 d i d not launch when a malfunction i n the Data T r a n s m i t t i n g System, s e n d i n g data t o t h e s p a c e c r a f t caused a n automatic hold a t T-3 minutes. G e m i n i 9 was launched two days l a t e r , and although the shroud h a d f a i l e d t o separate from t h e ATDA which p r e v e n t e d any docking e x e r c i s e s , a n i n i t i a l t h i r d o r b i t rendezvous was achieved, followed by a n equip e r i o d rendezvous, a n d a l u n a r a b o r t o r rendezvous from above on the following day. The EVA was postponed t o the following d a y when Cernan s p e n t more than one o r b i t o u t s i d e the spacec r a f t before v i s o r fogging i n h i s helmet forced t e r m i n a t i o n of t h e EVA before t h e Astronaut Maneuvering U n i t experiment cpuld be performed. G e m i n i 9 l a n d e d approximate1 t h r e e and-one-half miles from t h e recovery c a r r i e r i n t e West A t l a n t i c a f t e r 44 r e v o l u t i o n s of t h e Earth.

z

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-52

-

Gemini 10, J u l y 18-21 Rendezvous a n d docking, two e x t r a - v e h i c u l a r a c t i v i t i e s , docked maneuvers, a dual rendezvous, and a new a l t i t u d e record were t h e prime accomplishments of G e m i n i 10, the e i g h t h manned Gemini f l i g h t . Astronauts John W. Young and Michael C o l l i n s maneuvered t h e docked Gemini-Agena 10 t o 475 miles a l t i t u d e i n t h e course of achieving a dual rendezvous w i t h Agena 8. C o l l i n s conducted a standup EVA and an u m b i l i c a l EVA. During t h e m i b i l i c a l EVA, C o l l i n s used t h e Hand-Held Maneuvering U n i t ("MU) t o maneuver t o Agena 8 and retrieve t h e a t t a c h e d meteroid experiment package. I n the 38 hours 47 minutes w h i l e Gemini was docked with Agena 10, s i x maneuv e r s of t h e docked configuration using t h e Agena 10 propuls i o n system were s u c c e s s f u l l y completed. Gemini 10 splashed down i n the A t l a n t i c a f t e r completing 43 r e v o l u t i o n s , 70 hours 47 minutes a f t e r l i f t o f f . L a n d i n g was w i t h i n t h r e e miles of the p l a n n e d l a n d i n g p o i n t .

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. -53MANNED SPACE FLIGHTS MANNED HOURS SPACECRAFT RRS. REVS. I N MISSION

U.S.

MISSION

Gemini 10 (Young 70 Collins)

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TOTALMANNED HRS. CUMULATIVE

-54 PROJECT OFFICIALS

D r . George E. Mueller

Associate Administrator, O f f i c e of Manned Space F l i g h t , NASA Headquarters; Acting Director, G e m i n i Program

John Edwards

Deputy Director, G e m i n i Program, Office of Manned Space F l i g h t , NASA Headquarters

W i l l i a m C. Schneider

G e m i n i 11 Mission Director, Deputy Director, Mission Operations, O f f i c e of Manned Space F l i g h t , NASA Headquarters

Dr. Robert R. G i l r u t h

Director, N.ASA Manned Spacecraft Center, Houston, Tex.

Charles W. Mathews

G e m i n i Program Manager, Manned Spacecraft C e n t e r , Houston

Christbpfier C. Kraft

A s s i s t a n t Director f o r Flight Operations, Manned Spacecraft Center, Houston

Dr. Kurt H. Debus

Director, John F. Kennedy Space Center, NASA, Kennedy Space Center, Fla.

G. Merritt Preston

Deputy Mission D i r e c t o r f o r Launch Operations, John F. Kennedy Space Center, NASA, Kennedy Space Center

L t . Gen. Leighton I.

USAF, National Range Division, Command a n d DOD Manager of Manned Space F l i g h t Support Operations

Davi s Maj. Gen. V. G. Huston

USAF, Deputy EOD Manager o f Nanned Space F l i g h t Support Operations; Comxmder of A i r Force Eastern T e s t Range

Col. Robert R. Hull

USAF, Director, Gemini Launch Vehicles Directorate, Space Systems Division, A i r Force S y s t e m Command

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-55Col. A l f r e d J. Gardner-

USAF, D i r e c t o r , G e m i n i T a r g e t V e h i c l e D i r e c t o r a t e and Agena D i r e c t o r a t e Space Systems D i v i s i o n , Air F o r c e Systems Command

Col. O t t o C. Ledford

USAF, Comnander 6555th Aerospace T e s t Wing, Space Systems D i v i s i o n a t Air Force E a s t e r n T e s t Range

Col. John G. Albert

USAF, C h i e f , Gemini Launch D i v i s i o n , 6555th Aerospack T e s t Wing, Space Systems D i v i s i o n a t A i r Force E a s t e r n T e s t Range

Lt. C O ~ . L o E.

USAF, Chief, Atlas E i v i s i o n , 6555th

A l l e n , Jr.

Aerospace T e s t Wing, Space Systems D i v i s i o n a t A i r Force E a s t e r n T e s t

Range R. Adm. W i l l i a m C. Abhau

USN, Commander Task F o r c e 140 Primary Recovem Area

R. Adm. R. G. Anderson

USN, Commander Task Force 140.3

R.

Adm. Henry S. P e r s o n s

USN, Commander Task F o r c e 130 P a h i f i c Recovery Area

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-56-

. I

~

I I

SPACECRAFT CONTRACTORS McDonnell A i r c r a f t Corp., St. Louis, Mo., i s prime cont r a c t o r f o r t h e Gemini s p a c e c r a f t . Others include: AIReseaTch E4anufacturing Co. L o s Angeles

Environmental Control System

IBIJI Federal Systems Division

Onkoard Computer

General E l e c t r i c Co. West Lynn, Mass. The Eagle P i t c n e r Co. J o p l i n , Mo.

Fuel C e l l s

E l e c t r o n i c Systems Center Owego, N. Y.

Batteries

N o r t h r o p Corp.

Parachutes

Rocketdyne Division, North American Aviation, Inc. Canoga Park, Cal.

OAMS, RCS

Thiokol Chemical Corp Elkton, Md.

Retrorocket System

Newbury Park, Cal. I I I

.

Ejection Seats

Weber A i r c r a f t Corp, Burbank, C a l

.

Westing,house E l e c t r i c Corp Ealtimore, Md.

.

Rendezvous R a d a r System

Atlas c o n t r a c t o r s include: G e n e r a l Dynamics, C o n v a i r Div. San Diego, C a l .

Airframe a n d Systems Integration

Rocketdyne Div., North American Aviation, Inc., Canoga Park, Cal.

Propulsion Systems

General E l e c t r i c Co. Syracuse, N. Y.

Guidance

Burroughs Corp. P a o l i , Pa.

Ground Guidance Computer

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T i t a n I1 c o n t r a c t o r s _i.nclude:

M a r t i n Co., Baltimore Div., Baltimore

Integration

Aero jet-General Corp. Sacramento, Cal

Propulsion System

General E l e c t r i c Go. Syracuse, N. Y.

Radio Command Guidance System

.

Burroughs Corp P a o l i , Pa.

.

A i T f r a m e and Systems

Ground Guidance Computer

Aerospace Corp. E l Segundo, C a l .

Systems Engineering and Te chni c a l D i r e c t i o n

Agena D c o n t r a c t o r s i n c i u u e : Uckheed M i s s i l e s and Space Go. Sunnyvale, Gal

Airframe and Systems Integration

B e l l Aerosystems Go. Niagara F a l l s , N. Y.

Propulsion Systems

McOonnell A i r c r a f t Corp. S t . Louis

Target Docking Adapter

.

Food c o n t r a c t o r s : U. S. Army L a b o r a t o r i e s N a t i c k , Mass.

.

Whirlpool Corp. S t Joseph, Mich. S w i f t a n d Go., P i l l s b u r y Co., ’

Procurement, Processing, P a ckag ing

Chicago Minneapolis

Suit contractor:

The David R. Clark Worcester, Mass.

Food Formulation Concept

CO.

P r i n c i p a l Food C o n t r a c t o r s

-58Approximate Times of Major E v e n t s I n Nominal Gemini 11 Mission

.,

.

GET Hours

Event

13

00 - L i f t o f f

Acquire Target ( r a d a r ) _Out-of plane c o r r e c t i o n TPI Burn 01 -1st Midcourse 2nd Midcourse TPF-fly f o r m a t i o n -Dock-(S-9 e x p e r i m e n t ) 02 (D-3 e x p e r i m e n t ) -Undock (S-26 experiment)

-

03 -

,Out-of-plane

0

0

06

07

-- (S-29

PPS c a l i b r a t i o n

experiment)

--Docking p r a c t i c e ,Eat p e r i o d -

08 - S l e e p -

-0

15

period

-17 .. e x p e r i m e n t ) docked -18 - ( A p o l l o sump t a n k p h o t o s ) -19 0

(S-11

04 ,Dock

-

P

14

16 -Eat p e r i o d

-Dock ,Undock ( f l y f o r m a t i o n )

05

-

,

0

-

Event

GET Hours

-,EVA

-

20

-

22

-

23

-

Preparation

21 -

..

fl

-

24 - U m b i l i c a l EVA, I n s t a l l t e t h e r , (D-16 power 0

tool), HHMU e v a l u a t i o n

-End EVA

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c

-594

Event GET Hours 26 - Post ingress procedures --

-

-

GET Hours

39

Event

0

-Eat period (S-4 experiment)

-. -Agena PPS burn (750 NM), - experiments) 41 -- (S-11 experiment) b42 I

27 -Equip jettison (S-11 exper.) 40

-- (S-29 experiment) -30 29

0

0

-Agena PPS burn ( 1 6 0 NM)

Eat period

--

32 -

-

0

43

0

31

(S-5,

0

44 Sleep period

EVA preparations

0

--0

45

46

- Stand-up EVA, --

(S-13 experiment)

0

47

48

--

--

-

-End EVA

49

-- Tether evaluation

-Post ingress Procedures 0

-

50 -Undock 0

0

51

0

-more

-

S-6, S-26

-60GET Hours

Event -

GET

Hours

Event

52

-

Eat period

-- Final Jettison tether separation from -Agena 54 - Orbit ad just burn (D-3 experiment) -55 53

( S - 4 experiment) (S-30 experiment)

-- Eat period

I

56

- (D-15 experiment) 57 -.Sleep period 58 -

Pre-retro checks

Retrofire Splashdown

-

59

--

-

I

60

61

62

63

64

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-

-611

LOCAL TIM2

LOCAL TIME A.M.

?.>i.

--

:2:00

12:OG

01

-

NOTE:

Clip the time s c a l e s a t l e f t and s l i d e them along the s c a l e s showing the approximate ground elapsed t i m e of a nominal mission. Place the l o c a l time of l i f t o f f opposite the 00 on the GET s c a l e and you w i l l be able t o read o f f the approximate l o c a l times of major events

.

_ . A L

-.. -end-