Nasa Gemini 6 Press Kit

NATIONAL

AERONAUTICS AND SPACE ADMINISTRATION WASHINGTON, D.C. 20546

FOR RELEASE:

REUSE

NO:

TELS. WO 2-4155 WO 3-6,925

WEDNESDAY AM, S October 20, 1965

65-327

PROJECT:

6

CONTENTS Title GENERAL

I

T

Pa_e NEWS

RELEASE ........... '..........

1-6

Orbits - Revolutions ...................... Launch Vehicle Countdown .......... -....... Experiments ...............................

7-10 ll-12 13-I_

Radiation ................... Photography _ .......... Synoptic Terrain ....... '.Synoptic Weather Photography ........... Bio-Ch_mical Analysis of Body Fluids--70MMHasselblad Camera .................... 16MMMaurer Movie Camera .................. Gemini 6 Nominal Maneuvers ................ Checks while docked ....................... Laser Beam0bservation .................... Y_mmediate Preflight Crew Activities ....... Mission Description ....................... Manned Space Flight Tracking Network Gemini 6 Mission Requirements ........ Tracking .................................. Network Configuration .....................

15,1b 17 17-18 19 20 21 22 23-24 25-26 27-32 33 34- 43 44

Crew Safety ............................... _-47 Gemini Parachute Landing Sequence ......... 48 Abort Procedures Atlantic Recovery .......................... Area Communications ..... 49 Planned and Contingency Landing Areas ..... 50-51 Weather Requirements ...................... 52 Body Waste Disposal ....................... Gemini 6 Suit ............................. Medical Checks ............................ Food ............. "................ --- .....

5_ 55

Men_s - ..................... Waher ............... Measuring @ystem .......... ,.........

75_-5± 5G

To be launched

no earlier than October - more -

25,

1965.

-2

-

Gemini Spacecraft ........................ Liquid Rocket Systems General

58

Arrangement--........................ Thrust Chamber Arrangement ............... _ Maneuvering Control ...................... 61 Spacecraft Responses to Orbit Attitude Control Thrust ........................ 62

RCSFunct±on ........... _...... _ 6_-64 Electrical Power System _--_ -- ..... "........... 64-65 Rendezvous Radar .......................... Propellant ............................... Static Charge Device ..................... Gemini Launch Vehicle .................... Agena Target Vehicle ..................... Atlas Launch Vehicle ..................... Atlas Agena Launch Sequence ..............

_ 66 66 66-67 68-7@ 71-72 72a

Crew Biographies ......................... Previous Gemini Flights .................. U.S. Manned Space Flights ................ Project Officials ........................ Spacecraft Contractors ................. _Abbreviations and Symbols Frequently Used

_ _ 81 82 83-84 85-86

NOTE TO EDITORS: Supplemental information will be released as rapidly as it develops.

NEWS

NATIONAL

wo2_,,,

AERONAUTICS ANDD.C. SPACE ADMINISTRATION WASHINGTON, _0S46

TELS. WO 3-6925

FOR RELEASE: WEDNESDAY AM:S October 20, 1965 RELEASE NO:

65-327 NASA

GEMINI

SCH_ULES

6

RENDEZVOUS,

DOCKING,

Late

this

Administration

flight

yet

docking to

month

will

linked

necessary

manned

repair

of

fourth

of

the

6,

objectives will

be

are ended

mission two-man

6

were

is

difficult

United

States--a

the

Gemini

6

Space

manned

space

rendezvous

spacecraft

will

and be

flown

vehicle.

ability

to

rendezvous

of

such

resupply

of

earlier

than

and

missions space

dock

as

is

the

stations

and

25,

be

satellites.

manned

Gemini

most

and

the

landing,

scheduled

missions

the

Agena

the

Aeronautics

accomplishment

Moon

Administration's Gemini

an

unmanned

Gemini the

which

with

for

Apollo

by

in

Development

National

attempt

unde_aken

mission

and

the

MISSION

no in

the

space

Oct.

National

will

Aeronautics

and

flight

program.

The

first

two-day

mission.

However,

Space two

unmanned.

planned

accomplished

as

a

by

the

then. -more-

end

of

one

day,

the

if

flight

all

-

Prime command crew

pilot,

ate

and

consists

Gemini Air

crewmen

of

spacecraft,

Force

lieutenant

were

the

backup

Target

for

the

and

space

lock

Cape

Kennedy,

follow

it

The until

its

Gemini more their one

crew orbit

into than

the

relative mile

per

an

be

target. miles speed

the

is

a.m.

hour

that

the

hour time

w.

operations

minutes

maneuver

of

hour.

-more-

Grissom,

a an

Air

Force

will

be

3 mission.

Plans

Gemini be

call

joln

for

from

Gemini

to

later.

and

spacecraft

then

vehicles

will

kilometers

docking

can

launched

their

Agena

(28,170

in

an

Gemini

both

Earth

Stafford,

to

the

backup

a Navy

schedul_d

41

Jr.,

Young,

the

to of

the

that

and

The

"Gus"

and

EST.

Although per

at

I.

docking

so

Schirra,

orbit

John

and

required

matches

17,500

for

Agena

i0

to

captain,

modified

at

space

will

and

crew

The

Fla.,

into

men

rendezvous

it.

M. pilot.

Virgil

a Navy

vehicle,

onto

two

colonel,

major,

Walter

Stafford,

Astronauts

Schirra,

Agena

P.

first

commander.

an

Astronauts

Thomas

the

2 -

must

guide be per

be

less

the traveling hour), than

- 3

During by

radar

and

during eyes

the and

after

An

The

vehicles

over

At raise

the

the

operation,

they

spacecraft

and

feet,

will

they

scheduled,

during

one

the

on

will

the

be

vehicle

vehicle

will

will

be

aided

ground,

guided

or will

or

high be

low

in

insert

the

point,

point,

of

the

same

6 will of

but

by

their

168

the

Agena

plane,

into

and

an

(161

(270

a The

into

miles

miles

Earth

orbit.

spacecraft i00

launched

revolution.

kilometer)

of

be

the

spacecraft

(298 place

Gemini

revolution

fourth

185-statute-mile

elliptical

kilometers)

kilometers).

following

the

same

path

Earth.

its its

second

faster produce

vehicles

apogee,

perigee

spacecraft

Earth

as

completed

launch

apogee,

the

hundred

a perigee,

an

will

it

Atlas

with

the

in the

goes

has

with

and

to

mission

launch

orbit

of

judgment.

circular

Gemini

part

few

Agena

dock

near

final

the

the

first

computers

their

If

will

the

-

is than a at

to in

and

range third

a

the

134

miles

lower

about

(216

orbit,

catching of

spacecraft

up 161

apogee. -more-

it to

will

maneuvered

kilometers). is

the

miles

be

Because

traveling Agena.

(260

around This

kilometers)

the

maneuver between

- 4

At orbit

third

at

an

and

eleven

the

crew

orbit.

will

initial

39

Each one

and

both

while

18

of

aid

graphy;

research

mass

of

an

the

spacecraft.

(270

the

the

will

They for

about

will 27

the

flight

the

orbiting

two

will

body,

one

several at

the

spacecraft

geology, bodies

and

-more-

in

same

Agena

for

measuring

last

experiments.

terrain

the

the

was launched.

geography and

daylight

time

conducting

photography,

of

The

experiments

the

spent

Agena's

later.

from

be

weather

celestial

Agena.

Gemini

after

fields

the

hours

the

(28 kilometers)

dockings,

conduct seven

minutes

miles

hour

darkness,

into

a half-hour

separate

include: in

will

17

behind

perform

spacecraft's An

enters

spacecraft

be

about

the

kilometers).

spacecraft

transfer

occur

photographing

the

as

will

and

Experiments to

could

They

remainder

circularize

(63 kilometers)

sleep

hours

will

miles

Gemini

darkness.

docked.

time The

miles

will

168

to

astronaut in

crew

later,

time,

docking

and

of

begin

that

and

the

altitude minutes

At

below

apogee,

-

Agena;

radiation

photography

and

oceano-

determining inside

-

Primary and as

objective

docking,

using

required.

Agena

makes

its

span

met,

spacecraft

is

is

window five

known

as

launch

-

mission

spacecraft be

is

and

launched to

the

window,

will

again.

be T_

demonstrate

Agena

propulsion

within

revolution launch

to

2%

achieve

delayed Agena's

hours

rendezvous capabilities after

rendezvous.

and until

if

it

the

This

cannot

next

active

lifetime

it

capability

the

be

day

when

in

flight

days.

maneuvered

engines by

is

must

not

launched

Secondary

1.

on

commands

propulsion

Gemini

the

must

first

"opens"

Rocket

Agena

both

Gemini

time

the

of

5

mission

Conduct

the

Agena

give

the

ground

from be

used

during

to the

objective

rendezvous

effect

and

s

first

the

or

from

the

to

Gemini.

rendezvous

if

the

25

of

the

minutes

be

window.

are:

docking

using

onboard

radar

and

computer.

2.

Have

both

crewmen

conduct

conditions.

-more-

dockings

under

various

lighting

-6

3. docked

Evaluate

point

Demonstrate

5.

Evaluate

6.

Determine

reentry

guidance

capability

the

Conduct

After

recovery

the

of

lifetime

sent

of

the

and

landing

and

Agena

while

ground

undocked.

control

capability

the

The

by

space

effort

areas

as

into

has

landed

is

Agena

Agena

under

in-flight

in

will

the

be

orbits.

Control

Program

and

the

various

Center

experiments.

West

Atlantic

expended

by

Maneuver

commands

at

NASA's

maneuvering

Manned

will Space-

Tex.

is

NASA

Manned

launch

and

various

Mission

Flight, the

tests

the

Houston,

Gemini

Space

in

of

ranges.

systems

fuel

Center,

managed

and

vehicle

from

visibility

spacecraft

area,

target

Manned

command

useful

conditions

8.

craft

spacecraft

Evaluate

lighting

and

capability

Agena.

7.

be

translation

control.

the

the

and

vehicles. 4.

of

attitude

under

the

Headquarters,

Space supported

Flight by

direction

Washington,

Center. the

vehicle

development,

(BACKGROUND

INFORMATION -more-

of

Gemini

Department launch

recovery. FOLLOWS)

of

the

Office

D.C., is

and

is

a national

Defense

operations,

of

in

tracking

such

-- 7

Mission

information

presented

based

on

a normal

mission.

prior

to

or

flight

during

ORBITS

The around

spacecraft's

the

spacecraft Gemini

Orbits 90

A

passes

over

altitudes

space

in

80

this

Plans to

press

kit

be

altered

may

meet

changing

is

conditions.

REVOLUTIONS

is

measured

revolution

about

are

-

course

Earth.

-

is

west

every

referenced

revolutions

completed

degrees

once

in

96

each

time

longitude,

or

the

at

minutes.

and

in

Gemini

take

is

caused

by

about

minutes.

The

longer

rotation. moves

As

about

spacecraft another west

time the

22.5

six

Gemini the

degrees

revolutions

and

for

16

meridian

the

orbit the

complete

completes

per

circles

in

an

minutes

80th

revolutions

spacecraft

completes

longitude

crosses

for

in

the

same

Earth,

the

direction.

about

spacecraft

the

Earth's

Earth

Although

90

minutes,

to

reach

it

the

takes

80

degrees

24

hours

--

hence

a revolution.

orbits of

per

longitude

day. -more-

day,

but 15

in

times

15

-8

NASA's

John

F.

responsibility of

the

for

Gemini

and

The

Gemini

with

the

first

day

later.

Kennedy from

St.

building,

section

of

pilot

The as Cape

vehicle

Aug.

reentry the

were

December

Aug.

2 and

erected

at

and

the

to the

launching

Gemini

KSC

by

second

launch

6 mission.

aircraft stage

complex

6 spacecraft

was

4.

It

taken

pyrotechnic

"premate

was

for

receiving

checks.

buildup" seat

Atlas

booster

launch

vehicle

last

year.

-more-

of

was

the

rendevous the

completed

the

(SLV),

target first

to

Cape KSC installation

ordl%ance and

recovery

spacecraft

pyrotechnics

for

flown

inspection,

The

section

seats,

to

a

19,

Gemini

control

of

shipped

overall

The

ejection

modified

was

arriving

stages

30-31.

a standarized in

for

assembly

and

the

vehicles

and

mated,

the

Atlas/Agena

Island,

and

has checkout

Merritt

installation

Center

testing,

stage

Louis,

Space

pre-flight

launch

The

Aug.

Kennedy

with and

were installation parachutes.

vehicle, arrived

known at

the

i

•

- 9

The Center

Agena

July were

Radio

Frequency

crew

to

and

also

6 and were

made

rocket

the Sept.

The and

that

spacecraft

remated

crew

tests all was

for

of

final

Atlas

the

tower between checks

hoisted

premate

flight

to

verify

booster

vehicle.

both

for

in

to

and

and

the

joint On

Oct.

were

was

above verifications

spacecraft its

Titan

flight

suits.

Agena

was

II

7 a major

to The

batteries

and

testing.

Mechanical

were

individual

flight.

performed

tests

_

for

of

vehicle

of _esh

space

systems

weeks

launch

ready

simulated

-more

two

and

installation

their

and

some

spacecraft

of

systems

interface

complete

Gemini

spacecraft

of

mated

space-

Tests

a series

conducted

the

removed

of

the

The 9 and

mechanically

then

systems

participated

Combined

prime on

Kennedy

KSC's

compatibility

Sept.

a simulated 6 was

Gemini

Capability

vehicles. 19

The

the

16.

pilots the

complex

to

at

spacecraft

Docking

two

the

Tower"

25.

Frequency

Following

Gemini

launch

combined

insure

launch

included

the

target. the

vehicle.

that

systems,

Agena

between

to

launch

tests,

the

boarded

Aug.

shipped

and

"Timber

site

Radio

were

components

a 50-foot

backups of

adapter

two

Systems

a series

transported the

atop

Test

their

docking

These

mounted

conduct

Gemini

its

26-27.

craft

6

and

-

mating

Oct. conducted

milestone

The

was

2. with passed

- i0

when

a

simulataneous

Rehersal"

--

The

Gemini

countdowns, are

Eastern

rendezvous.

day

the

the

Atlas

at

mark

in

the

launched exact

a built-in

adjust

Gemini

--

.

240

are .

at

in

different

different

counts

the

two

order

T-530

to

network, System.

complete on

minutes,

launch

(all

spacecraft,

Guidance

countdown

Gemini

minutes

ii

tracking

final

the

target

vehicle

count. i01

launch

the

vehicle

these

over

computed, --

of

will time the

be

times

scheduled

Gemini

later, the

spacejoins

are

called coincide

Cape.

After will

for

set

the

spacecraft depending

orbitin

to

the count -more....

is

The

minutes

hold

liftoff

pass

count

of

The

Radio-Command

this

performance

necessary,

adjustments

"Dress

in

liftoff).

the

and

first

complete

a combination

worldwide

starts

simultaneous

location

target's

__

at

the

and

approximately

the

the

count

GLV

for

a

vehicles,

so-called

minutes,

the

Liftoff

and

in

count

to

launch

critical the

is

two

and

Agena

combined

--

simultaneously.

Range

In

T-360

relation

the

Control

is

the

actually

running

with

Test

Timing

craft

count

mostly

Mission

countdown

completed.

6

associated

Houston the

was

launch

-

at

with the

will on

9 Agena. T-3

launch

resume.

the If

minutes the

95-minute

to

Agena sequence

be

LAUNCH

VEHICLE

TIME

COUNTDOWN

GEMINI

ATLAS-AGENA

F-3

days

Start

pre-count

F-I

day

Start

mid-count

T-12

hours

GLV

Countdown

propellant

T-530

minutes

T-390

minutes

Complete

T-300

minutes

Begin

T-235

minutes

T-120

minutes

Flight

T-II5

minutes

Crew

loading

propellant terminal

Crew

terminal

Start

tower

loading

Complex

spacecraft

minutes

Lift

T-83

minutes

insertion

T-75

_inutes

Close

spacecraft

T-50

minutes

White

room

T-35

minutes

Begin

erector

T-15

minutes

Spacecraft

T-04

seconds

GLV

seconds

T+2

minutes

36

seconds

hatches

evacuation lowering

OAMS

static

firing

ignition

Lift

off

Booster

removal

19

T-95

T-0

count

countdown

to

enters

Begin

engine

T+5:41

Second

stage

T+5:57

Spacecraft-launch

cutoff engine

separation -more-

(BECO) cutoff

vehicle

(SECO)

off into

orbit

- 12 -

T+6:07

Insertion

into

orbit

REENTRY (Elapsed 46

hours: 20

i0

seconds

Time

from

Gemini

lift-off)

minutes Retrofire

46:11:05

Jettison

retrograde

46:30:39

400,000

46:33:13

Communications

46:38:05

Blackout

46:39:41

Drogue

46:40:39

Pilot

46:41:22

Main

46:45:45

Spacecraft

feet

section

altitude blackout

ended

chute chute chute

deployed deployed fully landing

-more-

(50,000 (10,600

deployed

feet) feet)

(9,800

feet)

13 -

EXPERIMENTS Mass

The by

object

which

the

This

and

thrusting knowing craft

this

Gemini

the mass,

Method

and

--

mass

The

forward

incremental

divided

by

accelerating by

propellant total

the

can the

using can

Gemini

the

velocity

be

Agena

the then

and

Gemini be

determined

Agena

to

of

will

space-

calculating

calibrate the

the

velocity

indicator

and

determine

adding

the by burn

-more-

pilot

measure

by

multiplied time

by

will

spacecraft

is

command

thrusters He

propellant

Gemini

a technique

vehicle

docked

the

docking,

exert.

the

develop

orbiting

while of

to

level.

firing

they

remaining

an

involves

mass

thrust

of

is

acceleration,

Before

force

in

spacecraft

resultant

the

the

mass

technique

system.

the

experiment

propellant

determined. vehicle

of

Determination

the

weight

spacecraft. the to

change obtain

of

The in the

on the the

mass

velocity exact

of and thrust.

- 14 -

When

the

thrusters formula since

will will

the

produce,

be

be

of

the

mass

obtained

from

the mass

of

the

the

docked

again

to the

mass

total

The

is

fired

used

force

and

experiment. in

spacecraft

for

25

the

Agena,

seconds.

the

mass

thrusters,

the

acceleration

from

the

spacecraft

this

calculation

spacecraft

to

spacecraft

of

is

same

the

Agena, they

known. can

obtain

the

The

determine

of

following

with

the

equipment

The

be

subtracted

mass

will

be

of

the

Agena.

involved

experiment:

Gemini

Computer

Manual

Data

Event

Insertion

Unit

Timer

Orbital

Attitude

Instrumentation On-Board

voice

WEIGHT:

None

LOCATION:

Part craft

Maneuver

System

System recorder

VOLUME: of

the

space-

POWER

None .REQUIREMENTS:

Electrical

-

systems Fuel

-

20

ibs

a.

Translations 17 ibs

b.

Attitude Control

-more-

3]ks.

- 15 -

OPERATIONS: are

Communications

used

to

ground

The

provide

communications

Gemini

either

data

stored

or

acquisition

system

will

transmitted

signals

be

for

analyses. VOICE:

All

tape

parameters

SUPPORT:

PERFORMED: inflight performed

shall

be

recorded

on

the

Gemini

recorder.

GROUND

take

special

required. TELEMETRY:

voice

- No

No

The

prior

to

while

additional

calibration

docking.

in

the

approximately

five

support

translation

This

docked

ground

rigidized

position.

is

will

be

performed

translation Both

required.

will

maneuvers

be

will

minutes.

Radiation Purpose

--

To

inside Equipment the

the

the --

of

beneath

sensors

the

One

amount

the

radiation

level

and

distribution

spacecraft.

Seven

wall

cabin.

measure

of of

their

in

pressure the

the vessel

sensors

radiation

spacecraft.

crew

skin.

-more-

is

and

two

shielded members

Five are to

are

are

inside

simulate receiving

on the

16-

Method

--

Shield

South belt

will

Atlantic dips

be

anomoly,

closest

experiment

was

to

--

To

surface geography, flown Equipment lens; Areas

of of

in

of

flight

--

70

Hasselblad

two

packs

Interest

the

of --

in

compare

Hurricane

also with

since

the

radiation This

geology,

be

pictures

of

Earth's

geophysics,

experiment

with

with

Mexico,

Amazon,

parts

has

been

MA-8.

film

Southern

will

the

surface.

camera

color

Mississippi,

through

4.

This

every

where

selected

research

on

pass

Photoqraphy

oceanography.

mm

area

Gemini

photos

use

Photographs to

on

during

Earth's

Terrain

obtain

for

the

the

flown

Synoptic

Purpose

removed

Congo

65

80

mm

Zeiss

exposures

Africa,

and

and

Nile Bahama

taken

of

the

taken

on

Gemini

F2.8 each.

the

deltas

Rivers. Islands

5 before

Betsy. Scientists for

will

evidence

coral,

reefs,

of

compare

the

changes

to

etc. -more-

photographs underwater

ridges,

- I? -

Synoptic

Purpose

--

To

obtain

photographs weather

Equipment

Areas

to

3, --

4,

70

study

two

of

Interest

fronts,

of

Gulf

in

by

islands

the

trade

or

--

To

collect

after

flight

amino

acids

for and

cloud

the

Earth's

performed

lines,

enzymes

Zeiss

on

F2.8

exposures

typical

and

morning

tropical

wave

each. activit_

clouds

and

convergence

ranges,

broad

banding

Body

Fluids*

stratus

extra-

zone,

clouds

views

cellular

induced of

clouds

in

regions.

fluids

analysis

65

f_ontal

clouds,

Analysis

body

mm

thunderstorm

phenomenon,

other

Bio-Chemical Purpose

clouds,

intertropical

mountain

winds

line

80

with

cloudiness,

subtropical and

film

cirrus

coastal

patterns

of was

with

color

squall

jetstream

cyclones,

also

camera

of

with

tropical

color

structure

experiment

Squall

states,

quality,

5.

magazines

associated

of

fine

Hasselblad

--

PhotoqraDhv

high

the

This

and

mm

lens;

not

selective,

system.

Gemini

Weather

of which

-more-

of

before, hormones, might

during

and

immediately

electrolytes, result

from

space

proteins, flight.

18 -

Method

--

Urine

will

elimination. be

added

A

the

it, cc

sample

capacity

Purposes the

with

for

of

each into

this

equipment

experiment

can

sample

transfered

*

specified

for on

in

By the

comparing

known

measure bags

the

urine

later

Gemini

the

amount

dump

are

missions.

6. -more-

of

system

to

of

flight It

of

will

sample

the

75

will will

be be

spacecraft.

qualify not

in

Sixteen

urine

of

tritium

placed

volume. A

will

amount

tritium

remaining

each

water

a tracer

carried.

The

for

has

total

be

bag

tritiated

amount

will

experiment

of

water

elimination. the

a special

amount The

tritium.

biochemists

drawn

collected

automatically.

radioactive in

be

be

and

evaluate

a complete

- 19 -

70MM

I.

A.

Equipment

B.

i. Camera 2. 80 MM lens 3. 250 MM lens _. Photo event 5. Ring Sight 6. DV filter 7. Film backs Characteristics

indicator

80 mm focal length f2.8 to f22.0 aperture Time exposures and speeds up to 1/500 second Resolution: approximately 125 lines/mm. Approximately I.SX magnification

Film A.

Ill.

CAMERA

Camera

i. 2. 3. 4. 5.

II.

HASSELBLAD

Three film magazines ASA-64 color emulsion

of Kodak S.0. 217, MS, Ektachrome on 2.5 mil Estar Polyester base

Purpose Weather General

and Terrain Purpose

-more-

- 19 -

70MM _ASSELBI_D

I.

Camera A.

Equipment

B.

i. Camera 2. 80 MM lens 3. 250 MM lens 4° Photo event indicator 5. Ring Sight 6. DV filter 7. Film backs Characteristics i. 2. 3. 4. 5.

II.

CAMERA

80 mm focal length f2.8 to f22.0 aperture Time exposures and speeds up to 1/500 second Resolution: approximately 125 lines/mm Approximately 1.5X magnification

Film A.

Three fiimmagazines of Kodak S.O. 217, MS, Ektachrome ASA-64 color emulsion on 2.5 mil Estar Polyester base

llI. Purpose Weather and Terrain General Purpose

-more-

- 20 -

16MM MAURER

I.

Camera A.

Equipment i. 2. 3.

B.

two cameras 75 mm lens (one camera) 75 mm, 25 mm, 18 mm lens set (second camera)

Characteristics 1. 2. 3. 4.

II.

MOVIE CAMERA

Six frames/second f-ll aperture 1/200 second shutter speed 40 lines/mm resolution

Film A.

Twenty magazines

B.

Kodak

each containing

S.0. 217 color film

III. Purpose Agena and rendezvous General Purpose

photographs

-more-

113 feet of film

21

GEMINI

6 NOMINAL

-

MANEUVERS

Ground Rev.

Elapsed

Apoqee

Conditions

_o.

_eparation

1

00:06:00

Aft

100/168

Day

_eight

2

1:35:23

Aft

100/168

Day

2

2:19:14

Aft

134/168

Night

Co-elliptical Maneuver

3

3:48:34

Aft

168/168

Night

Terminal Phase Initiation

4

4:59:58

Aft

168/185

Night

Ist

4

5:12:19

As

168/185

Night

168/185

Night

Phase

Adjustment

Correction

Thruster

Lighting

_aneuver

Adjustment

Time

Perigee/

re-

quired 2nd

Correction

4

5:24:21

As

re-

quired Velocity

Match

4

5:32:40

Forward

185/185

Night

S/C Agena Separation

12

18:26:56

Forward

179/185

Day

Retrofire

29

46:10:20

Retros

-more-

Night

- 22

CHECKS

These

are

information in

Gemini

Lateral

and

10-second

firing

Agena

of

designed

crew

and

to

gather

vehicles

for

use

flights.

maneuver

thruster.

It

control

system

to

Purpose

of

maneuver

the

will Will

be

performed

require

control

use

attitude is

to

of

using of

the

combined

determine

Gemini/

dynamics.

Attitude

Control

Roll,

The

are

Check

spacecraft

attitude

Agena

performance

Apollo

DOCKED

but

out-of-plane

Gemini/Agena.

will

the

Translation

A

WHILE

experiments,

about

later

left

not

-

pitch,

also

be

crew

will

Gemini/Agena

Platform

yaw

will in

at

a

maneuver

90

degrees

rate

of in

using

about

three

all

Gemini

OAMS

degrees/second.

attitudes

tO

determine

use

Check both

maneuvering

performance

maneuvering

maneuvers,

performed

Parallelism

indicator

(attitude)

dynamics.

Crew systems

Check

visually to

determine

Agena to

and

and

various record

spacecraft

attitude

attitudes. data

alignment

together. -more-

of

from the

They incremental

two

vehicles

control

will

observe

velocity while

LASER

At

an

elapsed

time

to

acquire

visually

them

from

attempt toward

preliminary

to

experiment their for

to

pinpoint

be

of

to

Gemini

flight

in

attitude

I. and

the

3.

and

model

egress

Celestial Chapel

The

beacon

Range.

aimed

This

is

communications

crew

White

will

will

Sands,

orient

then

look

light.

extensive

- GEMINI

general the

following

laser

laser

7.

BACKGROUND

and

crew

Missile

toward

6

training

training

received

received

preparations

have

for

or

will

the be

launch: in

Procedures recovery

and

argon

Gemini

training

Crew

Egress

Planetarium,

to

abort

Dynamic

emergency

the

the

prior

boilerplate Pad

TRAINING

minutes,

Center

laser

assignment

Launch

2.

an

30

Sands

Spacecraft aboard

3 mission,

accomplished

White

flown

to

hours,

a two-watt

blue-green

addition

OBSERVATION

25

at

a Manned

CREW In

of

ground

spacecraft

prior

BEAM

the

activities recovery

training

using

Hill,

Mission

Simulator

Simulator.

actual

pattern

Gemini

recognition N.C. -more-

using

a

equipment elevator in

and and

the

spacecraft personnel.

slide

Moorehead

wire.

-

4. towed

Parachute

parachute

crew

Zero

6.

Suit,

7.

Training

8. crew

on

i0. system

network

wet

mock

the

administered for

Gemini

translation

in

abort

majo_ to

comparison

hours

per

20

hours

per

simulator.

experiment

briefings;

reviews. reviews,

acceptance

for

and

the crew

flight

-more-

systems

review,

sub-

regiew.

flight,

readiness post

docking

detailed

mock-up

flight

confirm with

and

simulations,

launch,

the

approximately

briefing; rules

90

simulators.

totaling

preparation

simulated

be

a

aircraft.

approximately

sessions

spacecraft

launch

days,

using

fittings.

mission

mission

final

T-2

water

KC-135

totaling

systems

and

At

over

in

harness

Gemini

Participation

During

data

the

and

tests,

in

and

sessions

Detailed plans

training

seat,

Training

9. flight

gravity

on

member

training

technique.

5.

member

descent

21-.L -

the

joint final

participates

combined simulated

medical for

crew

systems flight

examinations flight

medical

and

test, tests.

will obtain

examination

results.

- ?5

Immediate T-7

T-5

Preflight

Crew

Activities

hours

Back-up to the

hours

flight 100-foot

White

Room

final

flight

T-4

hours,

T-4

hours

T-3

hours,

40

minutes

BreaMfast

T-3

hours,

15

minutes

Crew

T-3

hours,

5 minutes

underwear

30

the and

minutes

participate

next

signal

hour,

the

conditioners

and

gloves

are

put

helmets

and

gloves

are

then

systems

biomedical

are

T-2

hours,

15

T-2

hours,

4 minutes

T-I

hour,

59

T-I

hour,

55

on

are and

crew

Medical

examination

attached

and

made

ready

awakened

leaves

quarters at

are

flight

pressure

100-foot and crew

and

Primary

donned,

blood

room, Room

manned crew.

sensors

in

preparations.

Crew arrives on Pad 16

helmets

temperatures

to

Pilots' ready level of White quarters for prime

During

crew reports level of the

ready

placed, suits

is

room

minus

checked.

communications

The

and

oral

checked.

minutes

Purging

of

suit

Crew

leaves

ready

minutes

Crew

arrives

at

minutes

Crew

enters

-more-

begins room 100-foot

spacecraft.

level

26

From

entry

monitors

Fliqh

systems

and

the

system

seconds

after

thrusting selects

insertion

and

the

crew

_articipates

in

or

preparations.

by

and

completion

forward of

crew

begins

the

status

and

detecting

SECO,

the

command

the

pilot

con_nand

velocity

made

is

and rate

are

plan

checks

ignition

assessing

Twenty ward

ignition,

t Activities

At of

until

actuates

attitude

corrections or the

aft

are

begun.

-more-

pilot

After list,

phase

task

situations. initiates

spacecraft

received

check

launch

abort

control.

thrusting.

insertion

primary

separation

Ground and

computations

velocity

successful the

for-

detailed

of

adjustments insertion flight

27 MISSION DESCRIPTION (all miles are statute)

Simultaneous

Countdown

are

coordinated

the

others

Launch

Times

so that

may

be

6

held

- 11:40:52

Window

and

extends

during

the

first

can

achieved

be

launch craft A

occurs

A delay

i00

sixth

window

because

be

planned

If

the

window, will is

for

the

spacecraft launch

that

Launch

in one,

Complex

Complex

19.

minutes

after

the

launch

period,

Agena

14.

Agena

occurs

rendezvous

propulsion

beginning

part slips

of the

only.

as well

tracking

If as

space-

the

fourth

in

200

the

to the

the

fifth

rendezvous

seconds

15th

limitations

permits

revolution.

rendezvous moves

window

into

the

revolution.

rendezvous

would

revolution.

cannot

be

launched

delayed

again.

the

past

rendezvous

be

of

seconds

A delay

!6th

must

If

window,

of 200

the of

be available

five z

latter

revolution.

However,

lO1

of

the

seconds

put

involved

be used.

at

A delay

would

Launch

hours.

the

must

during

vehicles

is encountered

EST,

spacecraft in

launch

revolution.

EST,

2¼

using

propulsion

of

a.m.

25 minutes

rendezvous

to

for

later

spacecraft

- lO

approximately

launch

all

also.

a.m.

-- Begins

of

if a hold

-- Atlas-Agena

Gemini Launch

-- Countdowns

for

AgenaTs

days.

-more-

within one

active

day,

the

2¼-hour

when

the

window

lifetime

in

flight

- 28

Azj_muth -- Atlas-Agena provide

biased

from 83.7 to about 85.7 to

for yaw steering

to shift orbital

during Atlas

equatorial

sustainer

nodes or crossings

grees

to east.

This shift equals about

Earth

rotation,

therefore

which

to use Gemini

spacecraft

allows

into Agena's

plane.

4.2 de-

17 minutes

17 additional

launch vehicle

burn

capability

of

minutes

in

to launch

The launch azimuth

places

the Agena back over launch site after one revolution. Because

of the Earth's

if the azimuth

rotation

was fixed.

will be 92.8 degrees,

Gemini

of yaw steering

the spacecraft

in Agenats

Capability

burn one-half if booster plane.

-- Fuel budget

yaw steering

by the Agena,

in second

slightly

azimuth so that

stage will place

plane.

of one degree

Corrections

launch vehicle

but will be biased

a small amount

0ut-of-Plane

this would not be possible

allows

out-of-plane

spacecraft

if necessary

does not place Gemini

of greater magnitude

capable of lO degrees

to

in Agena's

must be performed

out-of-plane

maneuvering. Inclination Vehicle

-- 28.87 degrees

for both Agena and Gemini

(GLV).

-more-

Launch

29 Orbits

-- Agena Gemini

at

near-circular

initially

185 miles

in elliptic

(298

100-168

kilometers).

miles

(161-270

kilometers). Height

Adjustment orbit, at

-- Because

a one

first

(270 Phase

perigee

Insertion

Adjustment

19 minutes,

Poslgrade

horizontal

4.51

reduce

degrees

relation

3:48:34, (270

third

-- Near

the

will

crew

this

(259

time,

Terminal puter

Phase

and

Maneuver

to rendezvous

checkout after

fps

and

entering

rate

Agena

orbit.

at an time

ground

of

53.5

miles

about

a

168-mile

apogee

from

provide

the

will

with

spacecraft

kilometers)

a

below

134

(.93

necessitate

addition

6.68

of

elapsed feet

(198

necessary

third

circularize

This

52.4

.58 miles

time.

per

kilometers).

degrees

to

phase

apogee.

Maneuver

of

scheduled

is

(2:19:14)

to about

and

burn

achieve

second

seconds

catchup

spacecraft

may

17 miles

velocity

orbit

kilometers).

maneuver

14

perigee

the per

at

Co-elliptical

At

raise

or

initial

about

is to

spacecraft

2 hours,

It will

object

apogee,

-- Near

will

apogee

dispersions

The

kilometers)

during

posigrade

to raise

maneuver.

second

drag

foot-per-second

kilometers). larger

of

mode

procedures.

be achieved

trails have

and

crew

-more-

crew

by

will

168

at

miles

4.5

degrees.

161 miles

radar

lock-on.

will

about

perform

up

about

terminal

4:59:58,

apogee

by a posigrade

onboard

begin

to

pitched

Agena

3:52:34,

At

darkness,

orbit

spacecraft

should

-- At

spacecraft

switch phase one

comsystems

minute

a burn

of 32

fps

0

30 along

llne-of-sight

about

39 miles

of Agena.

(63 kilometers),

130 degrees of angular Spacecraft

Range to Agena will be

travel

will be pitched

and spacecraft

will be

from point of rendezvous.

up 27 degrees

for the posigrade

maneuver. Intermediate

Correetlons

pulse,

computer

by the crew.

-- Twelve minutes

displays

after initial

first correction

Twelve minutes

im-

to be applied

later, at 5:24:21

another

J

correction

is applied.

kilometers) Agena.

Range is then about 4½ miles

and crew begins

a semi-optlcal

approach

The crew will use radar information

directly

(7¼ to to

read out range and range rate. Velocity

Matching

Maneuver

veloclty-matching However,

real-time

continue fps.

two vehicles reducing

revolutions,

after

is about 43 fps.

techniques,

he will make

velocity

difference

to 4 fps at about 2,000 feet, then until docking

at less than 1

could occur as early as five hours lift-off.

Initial

Docking

-- During

the next two

three more docking

practices

will be performed.

The command pilot in daylight

of a theoretical

pilot will be controlling

He will reduce

velocity

Initial docking

Following

at 5:32:40

by semi-optical

decisions.

and 33 minutes Activities

maneuver

since the command

final approach

between

-- The magnitude

and pilot will each perform

and in darkness.

-more-

Other activities

a docking scheduled

31 -

during

this

lation

check,

Agena

period mass

attitude

vehicle,

are:

determination

control

platform

check,

After

will

7-hour

rest

from

Agena

Final

Separation the

spacecraft

grade

maneuver

of

7 fps.

entering

provide

proper

conditions

experiment

involving

craft

fall

at perigee

and

revolution. 298

tinue Nominal

will

Final

to get

End

of Mission

longitude

of

revolution. N/62

W)

Should occur Landing

ahead

is planned the

at

mission

23:40:50 area

does

over

about

Carnarvon sextant

five and

will

sighting

(5¼ kilometers)

it by

about

21 miles

after

orbit

will

retrofire,

and

by

about

during

ended 5 N/174 change.

-more-

be

179-185

spacecraft 21

miles

is at 46:10:20 spacecraft's

Atlantic

at 46:45:45,

not

occur

a retro-

3½ miles

in West

at

with

revolution,

about

degrees

be

will

12th

crew

by

-- Retrofire

Landing

Agena

the

background.

of Agena

168.7

yaw

star

Gemini

until

during

and

target

Agena

18:27

for Apollo

Agena

lead

and

docked.

darkness

Gemini-

of

while

This

trans-

activities,

from

Agena

below

kilometers)

-- At

separate

before

will

these

period

minutes

experiment,

check,

completing

will

lateral

photography

parallelism

maneuver. begin

Gemini-Agena

or

after

recovery

about

10:25

The

space-

one

miles will

(289-

per

con-

revolution.

at west 29th area

(27

a.m.

EST.

one

day,

retrofire

W during

15th

revolution.

will

Agena

Activities will

Following

exercise

will

when

Agena

begin

exercises3 of

about

in

orbit

four

will

passes

over

ground

will

command

miles

after

North

decay

target to about

months.

-more-

for

on

simu.late Agena

control its

typical

propulsion,

spacecraft

America.

Agena

(;$_!-5 kilometers),

non-powered would

requiring

2_ hours

-- Ground

information

probably

maneuvers

about

Landing

further

again

276

as potential This

Exercises mission

They

to gain "_

Agena

capabilities. rendezvous

Spacecraft

landing

Following

these

to a circular

orbit

where

be

future

185 miles

it will Gemini (271

left

missions.

kilometers)

L

33

-

MANNED SPACE FLIGHT TRACKING NETWORK GEMINI 6 MISSION REQUIREMENTS

NASA by

using

its

Defense

for

For

and

(2)

position)

through Manned

also

receive

launch

Eastern

Test

the

provide

command

the

Agena

will

of

Department

flight

and

the

by

the

of

controllers:

telemetry

Agena

data

Target

from

Vehicle

update

via

systems

complex.

-more--

be

(computed

space

from

Complex

(RTCC)

Bermuda

via

center,

provided

powered

from

radars

control

astronauts.

Computer

During data

the

the

will

Real-Time

(AFETR)

of the

ephemeris

for

support

Center.

operation

target.

displays

trajectory

Range

proper

to provide

computing

Spacecraft

computing

of

and

reentry

impact

of

Network

control.

will

insertion

computer

Irmmediate

those

Tracking

spacecraft.

network

and

Flight

and

tracking,

orbital

Gemini

spacecraft

and

network

Verification the

The the

6 the

Gemini

Space

information

Continuous

the

Manned

facilities

mission

through

onboard

the

own

Gemini

(I) launch

operates

the

flight, and Cape

the Air

launch at

RTCC

the will

Force

Kennedy

CDC-3600

L

- 34

-

TRACKING

For

the

tracking Agena

first

of four

time

Target

space

Vehicle

Vehicle

(GVL),

called

SLV-3.

The

C-band

Agena

throughout

orbital

The and

MSFN

track

Gemini

6,

will

providing

and

FPS-16

have

only

Officer

by

according

have

system

meeds.

-more-

mission.

Radar Air However,

phase.

spacecraft to

tracking

individual

systems the

therefore, or Flight

sta-

capable

of

Gemini

and

Verlort

transmission

Director

re-

Range

this

their

capability,

the Mission their

Data

Gemini

American

on both

through

antennas.

to

radar

information

simultaneously

a single

established

sites

Space

of

according

and

is a mission

rendezvous

out

one

signal

North

for

combinations

position

(C-band)

the

C-band

carry

(radar

(WL£)

be used the

carried

Some

space

vehicles

various

be

capability.

during

will

lifetime

of

Gemini

two

vehlcle_

target

the

Booster

carry

tracking

Station

will

Atlas

Vehicle

Skin

facilities

(NORAD)

not

assignments

Wallops

various

Command will

beacon.

the

separate

spacecraft, is the

will

Target

spacecraft,

For

be

Agena

require

Gemini

II which

spacecraft

the

vehicle

will

required,

of

Defense

Agena

as

S-band

(SPANDAR)

tion

Titan

one

quirement.

NORAD

The

the

and

bounce) launch

and

Gemini

beacons.

mission

vehicles: (ATV)_

Launch

tracking

a Gemini

(S-band)

links, priority Dynamics

however, will

- 35 After

Titan

target

for

Manned

Space

Cape

II

C-band

launch,

the

spacecraft

Flight

Tracking

Network Grand

Merritt

Island

Pt.

Patrick

AI_

_ite

Bahama

Ascension

Island

USNS

Coastal Range

Island,

B.W.I.

USNS

South

Africa

Grand

Stations

Capable

of

C-Band

Knot

Turk

Island

Eglin,

Fla.

Corpus

Christi,

Tracking

_._ite Sands,

Patrick

Ab_

I_NS

Antigua

Island

C_rnarvon_

Pretoria,

Australia

Island,

B.W.I.

South

A_rica

Bange

N.

M.

Tracker

F4_lin, Fla.

Island

Ascension

_ermuda

Island

Texas

are:

Island

Bahama

Sentry Tracker

Merritt

Grand

N. M.

Hawaii Rose

Bermuda

Calif.

Sands,

USNS

Island

_stralia

Island

Arguello,

Antigua

Carnarvon,

Configuration Canary

Kauai,

Island

Pretoria,

be

tracking.

Kennedy

Grand

will

Grand

Turk

Grand

Canary

Pt.

Arguello_

Kaual,

-more

-

Island

}_waii

Island Calif.

the

prime

- 36 -

Stations Cape

Capable

of

S-Band

Tracking

Kennedy

Grand

Bahama

Grand

Turk

Bermuda

Carnarvon, Island

Canary

Stations Gemini

Kauai,

Island

Island,

Grand

are:

Pt.

B.W.I.

Capable Launch

Hawaii

Arguello,

Guaymas,

Island

Corpus

of Skin

Vehicle,

(radar

Christi,

signal

Spacecraft,

Merritt

Island

Carnarvon,

Patrick

AFB

_ite

Antigua

mission

Other

port

procedures

priorities

Computer

Goddard

for

Gemini

recovery

and

will

Turk

be

Island

used

as

needed

and

permit.

Space

Flight

6 includes

obtained

with

N. M.

Support

The

ginning

Target

Fla.

Grand

tracking

information

Agena

the

Australia

Sands,

Eglin,

Island

Skin

the

Tracking

Island

Island

Ascension

Tex.

bounce)

and

are:

Bahama

Calif.

Mexico

Vehicle

Grand

Australia

mission Agena

from

Conter

the the

realtime

processing Titan

siraulations lifetime.

-more-

of

!I and

through

computing realtime

Agena

Gemini

suptracking

systems spacecraft

be-

- 37 -

Goddard's

computer

wom,k's re_]diness system, method

Integrated

also

will

when

the

be

perfomned

and

quisition

Goddard's

Goddard

not

of' petwork during

the

and

vehicles

periods

"visible" are

Data

facilities

postlaunch

electronically

tests

from

the

worldwide

Realtime

Computing

Manned

Spacecraft

Center

CADFISS

Control

of

Mission

Test

the

again

by

some

within

ac-

4 and

Gemini

as

computer

Gemini

Center

5,

network

the

will

be

Complex

to

under

the

Manned

direction

conof

Director'.

entire

Control

Gemini

in

Houston's

6 mission

will

be

exercised

Houston,

Texas.

As

it

Realtime

Complex

will

did

on

serve

center.

Spacecraft

The beacon and

(Computation

Center's

from

Gemini

CADFISS

checkout

co_itinue until

flow

Spacecraft

the

m. syo<.em-b,}-

range.

Data

the

net-

<;om]:}nter-pro[_]rc_uned checkout

by

are

worldwide

@era .n.lo through

Subsystem)

spacecraft

stations

w[".],ce{,ti]'y the

CA_ ._I_)o _.eo-t._

Flow

by

to support

station-by-statio_b called

ducted

also

the

spacecraft

(spacecraft) DPN-6@model

has will

two be

beacon

tracking

nomenclature

The

model

ACF*

installed

in

the

reentry

module

(adapter)

in

the

adapter

package.

-more*Contractor

beacons.

The _eentry

ACF

beacon

_GENA

phase,

TARGET The

S-band

will

using

Agena

Target

beacon.

uso

band

will

be

beacon

target

for

C-band one

C-band

tracking

with

and

Gemini

Gemini

aid

spacecraft

J:'eceivers and

one

periods.

C-band

and

a modified

polarized Target

spacecraft

will

one

DPN-66.

antenna.

Vehicle

The

prior

C-

to

be

the

prime

of

tracking

launch.

inputs

spacecraft

only.

and

Vehicle

until

MISSION

MESSAGE

Times

All

orbital

and

to

capable

pointing

steerable

data

insertion

to

will

'4i!I track of

the

provide

their

antennas.

capability

stations

will

the

which

the

Agena

Gemini

radio

associated

Sites track

the

do

not

Gemini Target

spacecraft.

REQUIR]_4ENTS

types

summaries) sent

systems

simultaneously

simultaneous-tracking

i

contain

following

spacecraft

telemetry

be

these

and

SYST]_[S

(RE)

will

will

fo_, _ Agena

The

Sites

teletype

insertion,

for

be_ocon _'ill be

prime

frec_uency

have

lau.nch,

as a bac½_p

lineararly

launch.

ACQUISITION

Agena

DPN-66

Vehicle

The

will

Gemini

the

prirae for

_J]!]HI CL]']

E.'ch beacon

the

be

the

of flight from

flight

Houston

data

controller

M_tssion

-more-

transmission

Control

manned Center

(on-site stations immediately.

39Bermuda and

Agena

data

Corpus

Target

Bahama

Vehicle

Island,

Gemini

Mission

Control

PCI.Itelemetry

The

prime Command

out

worldwide

from

launch

Grand the

two

DCS

equipped

all

uplink

Canary

and data

Following required System Vehicle

for support

Agena

will

be

Cape

will

re-

Kennedy

by

is the

stations

through-

of

the

as always

be

provided

by

Center.

Max-

Control

throughout

Sentry £1ight

rendezvous

control

Carnarvon,

Coastal

astronaut

Arltigua

at key

Mission

is required

command

the

effecting

will

Houston

manned

format.

manner.

Command

Island,

USNS

and to the

located

recovery

coverage

ships,

in

(DCS)

at

computer

digital

(SCS)

network.

Director

command

same

system

System

through

Flight

imum

SYSTEM

data

spacecraft

high-speed

i_

Island,

Agena

in the

@emini via

Center

Turk

and

ground

Digital the

Grand

Center

COMMAND

tra_smit

Control

spacecraft

SPACECRAFT

the

Christi

to IIouston Mission

Grand mote

and

the

Australia, and

USNS

mission.

!_waii,

Rose

controllers

mission

Knot,

who

will

and are initiate

transmissions.

recovery, Target

further

Vehicle.

continued

lifetime.

-more-

to

co_ands

Network

determine

will

Digital the

Agena

be Command Target

The and

Texas,

Bermuda

upiink

sites

data

remoted

Cape

will

in real

time

to

Gemini I. 2. 3. 4. 5. 6.

SPACECRAFT

All

from

Bahsma,

be manned

Houston

real-time

¢,o_,mnands,the

a.

not

Grand

cortland transraissions

!n addition date

Kennedy,

i'ollowing

by

Grand

flight these

Mission

Control

digital

spacecraft

sites

Agena

Preretro with maneuver Preretro without maneuver Orbital navigation Maneuver Rendezvous Accelerometer error corrections

All

will

be

Center.

on-board

instructions

b.

Antigua,

controllers.

through

co_mnar_ds and

Turk,

clock may

Target

be

upsent:

\?ehicle

i. Maneuver 2. Ephemeris 3. Engine burn

time

COMMUNICATIONS

MSFN

stations

having

munications

can be

controlled

_ote

keying

from

(tone)

both

HF and

either

Houston

by

Mission

UHF

the

spacecraft

station

Control

com-

or by

re-

Center' and

Goddard.

The

following

co_mmunicator Control

(CapCom

sites and

are

not

will

be

Center:

-more-

scheduled remoted

to to

have Houston

a command Mission

Grand

Bahama

Kano,

Nigeria;

Arguello, Canton

Island;

Tananarive,

Bermuda;

Calif.;

Island;

Grand

Antigua

USNS

Malagasy

Turk

Island;

Range

Republic;

Island;

Pt.

Ascension

Tracker,

and

Island;

the

voice

relay

aircraft.

SPACECRA_

SYSTemS

The

Gemini

beacons,

voice

covery

light,

ing

of

the

the

ground

ground data

and

the of

transmission, The

The beacons, allows

sole

Agena

voice and

between by

Vehicle

spacecraft. Agena

from

groumd

and

vehicle

Ground also

recovery amd

track-

between

astronaut

communications

the

radar

to astronaut;

instrumentation and

re-

systems data the

trams-

Gemini

systems.

transmitters, of

allows

communications

the

these

(antennas,

transmitters,

system)

postlanding

link

tracking

to the

command

spacecraft,

and

systems

telemetry

two-way

the

Target

telemetry radar

communications

spacecraft

is provided

Gemini

cor_and

digital

spacecraft,

command

spacecraft

the

spacecraft

communications,

and

mission.

SUPPORT

are

station

digital from and

-more-

accomplished

system

(antennas,

command

system)

both

the

Gemini through

ground

and

spacecraft this

system.

-

Agena Target Vehicle Systems supported by Stations Table

42

On-Board Network

Gemini Spacecraft Systems Supported Stations

HI

Table

Telemetry (Real Time) Telemetry (Dump) L-Band Transponder S-Band Transponder C-Band Transponder Colmmand Receiver (Range Safety) Command Receiver (Command Control)

GROUND

NASA

be used

Communications 6.

Coastal

Sentry

Ship

mission-designated

ship

USNS

gation

Module Module Module Module Module Package

UH[_(voice)xrait-Rcv HF(voice)xmit-Rcv Telemetry(Real Time) Telemetry(Dump) Telemetry[Backup) L-Band Radar

Reentry

Module

C-Band

Adapter Adapter

package Package

Adapter

Package

Reentry

Module

C-Band Transponder Acquisit$on Aid Beacon Digital Command System UHF Recovery Beacon

Transponder

for

Shore

(NASCOM)

stations

support

positions

will

and

used

for be

for

USNS

based

predicted

Gemini

Rose upon

H_' radio

the propa-

RESPONSIBILITY

Manned management mission

Spacecraft

Center

responsibility control

during

a mission

bility

of

of the

simulation

(MSC).

of the Network

The

Gemini

-more-

has

program.

i_mmediately

or an actual

the MSC.

MSC

mission

the

overall

The

direction

preceding is

5

Knot

conditions.

NETWORK

and

Reentry Reentry Reentry Reentry Reentry Adapter

network

Gemini

and

#2

CO_@_UNICATIONS

The will

On-Board by Network

and

responsi-

- _3 -

Goddard

Space

and

Data

the

planning,

manned

as

Acquisition

and

instrumentation About

and

the

acquisition

at

operation

to

of the

is defined

and

augmentation

function

to mission the

for

operations

facilities

total

of Tracking

responsibility

modification,

support

bring

Office

technical

in response

directly

personnel

the

data

acquisition

hetwork

NASA

Technical

maintenance,

370 persons

contractor

and

Center.

data

The

centralized

tracking

Flight

operation,

of tracking

has

flight

Space

the

Center.

implementation,

space

Goddard

Flight

as an

requirements.

network

at

Goddardj

network

level

to

The

Department

some

150o.

Department Commonwealth and

of

operation

Contractual

of

Supply,

Australia.

Australia,

of the

is responsible

NASA

arrangements

station and

at

for

the

Carnarvon,

agreements

of Supply,

maintenance

Australia.

define

this

cooperative

effort.

Department

of

the maintenance and

facilities

clude

network

Range, and

and

stations

tracking

(DOD).

operational

required

_,_ite Sands

the

Defense

to at

Missile

and telemetry

DOD

the

ships.

is

responsible

of those

Project

Eastern

Range,

-more-{

control

support the

The

Test Air

Gemini. Range, Proving

DOD

for

assets These

Western Ground

inTest Center,

- _+4NETWORK

.

CONFIGURATION

x

X

x >_ X

C-band

Radar

x

x

>4 × x

S-band

Radar

X

>4

>4

X I , } t

>4

>4

x

X

I C)

>4

>_ X >d _

X

X X

X >4 >_

X

I Telemetry I Receive & Record

,

! Xl

Telemetry Real i Time Display L

! X

X

>4 >_I Telemetry Data Transmis s ion

× >4

x

>4

>4

High Speed Transmission

×

On

Site

Data

Process

&

Gemini

Data

Summary

Launch

Vehicle

Telemetry

Gemini Vehicle

Launch Command

Digital System

Command

I

>_ >_

×

>4

>4

I

>4

>4

>_ X

>_ >4

×

!

Frequency

1 x x x

Command

>_ >_ x ×

Voice

System - Transmit

I ......... i.&Receive_ >4 _ ×

X ×

× ×

l&

X

X

J

>4

+ >4>4_;>4_x !

×>4 x>4>4 >4

•

>4

>_

|

J

>4 tSpacecraft I

!Antenna

>_! >_ ' >_

Receive

X 1 Flight Control i Team Manned t

i >4

>4

>4[ Flight

>_

I Air >_

× x

.....................

× _I Teletype-Transmit

..... >_! X

.

× ×

x

&

Acquisition

S_v_tem Controller Group

MCC-H-Air to Ground Remote

Voice

Voice

J

ABORT PROCEDURES MODE I - EJECTAFTER SHUTDOWN MODE "ff - SALVO RETROSAFTER SHUTDOWN MODE TIT- SHUTDOWN, SEPARATE, TURN AROUND, RETROFIRE

20,700 FPS

MODE

VELOCITY

b_

t

A / TI

T

11" (WAIT 5

SECONDS

SECS) ]5,000 FT.

I

SEA LEVEL

I

OOE SECONDS

r

46

CREW

Every (Back-up)

Gemini feature.

the

launch

the

crew

for

escape. are

MODE

I

MODE

II

three

Survival

Detection

subsystem

of

has

a redundant

System

performance

catastrophic

modes

safety

aboard

and

malfunction

in

warns time

escape:

Ejection seats, and personal parachutes, used at ground level and during first 50 seconds cf powered flight, or during descent after reentry. (Delayed)

Retroroekets used between 50 and I00 seconds, allowing crew to salvo fire four solid retrorockets five seconds after engine shutdown is commanded. Normal separation from launch vehiclej using 0AMS thrusters, then making normal reentry, using computer.

for

turns with

crew

Malfunction

monitors

III

Except

landing

affecting

a potentially

There

MODE

The

vehicle

of

Vehicle,

system

SAFETY

Mode

I,

blunt-end

crew

spacecraft forward,

separates then

from

completes

Gemini reentry

Launch and

aboard.

package

Survival to

the

23

pounds.

gear,

astronaut's

mounted parachute

on

each

ejection

harnesses

-more-

seat

by nylon

and

line,

attached weighs

all

47 -

Each 3.5

astronaut pounds

has:

of

drinking

water

Machete One.nan flation,

life

sea

anchor,

Survival sewing

striker,

halazone

5_ by

dye

light

compass,

Survival

raft,

3 feet,

markers,

(strobe),

kit,

14 feet

tablets,

radio,

with

with

nylon

with

sun

line,

a _listle,

and

beacon

for

in-

bonnet.

flashlight,

of nylon

homing

CO 2 bottle

signal

mirror,

cotton

balls

and

batteries

for

power.

and

voice

reception.

Sunglasses. Desalter of

kit,

with

brickettes

enough

to desalt

eight

pints

seawater. Medical

antibiotic

kit, tablets

containing and

stimulant,

aspirin,

sickness°

-more-

plus

pain,

injectors

motion for

sickness pain

and

and motion

- 48--

GEMINI PARACHUTE LANDING SEQUENCE 50,000 FEET

_

HIGH ALTITUDE DROGUECHUTE DEPLOYED

21,000 FEET

OPEN CABIN VENT VALVE

10,600 FEET

PILOT PARACHUTE DEPLOYED

DEPLOYMENT 9,_I_ FEET

_

6,700 FEET

i_

1,500 FEET

_

SEALEVEL

_

MAIN CHUTE

_

TWOPOINT SUSPENSION

_

CABIN WATER SEALCLOSED _

__

TOUCHDOWN

_

JETTISONCHUTE

)

PLANi'iED AND

There

are

two

and

contingency.

are

pre-positioned

short

time.

tingency and

a

areas,

longer

Planned

types

of

other

areas

areas

requiring

IJ_ND!NG AREAS

landing

to recover

recovery

Landing

CONTINGENCY

Planned

All

--

are

areas

for

those

where

spacecraft under

special

the

and orbital

search

and

Gemimi

6,

planned

recovery

forces

crew

within1 a

track rescue

are

con-

techniques

period.

Areas

PRIMARY

Landing in the West Atlantic (30-1) where the primary recovery vessel, am aircraft carrier, is pre-positioned.

SECONDARY

Landing in East and Mid-Pacific deployed.

LAUNCH

SITE

Landing in the event of off-the-pad abort or abort during early phase of flight, includes an area about 41 miles seaward from Cape Kennedy, 3 miles toward Banana River from Complex 19.

LAUNCH

ABORT

Landing in the event of abort during powered flight3 extending from 41 miles at sea from Cape Kennedy to west coast of Africa.

-more-

Atlantic, West Pacific areas where ships are

Contingency

All

Landin$

except Landing

the

those

of

during the

Support

the

spacecraft's

Planned

Landing

Areas

and

pararescue

requiring

withi_

Recovery

beneath

designated

Areas,

recovery

and

area

Areas

aircraft

a period

forces

mission

Department

of

will time

i_3 hour_: from

grou_d

track

are

Contingency support

for

splashdown.

be

provided

i)y the military

services,

will

be under

the

control

of Defense

Manager

Operations.

-more-

for

operatio_al Manned

Space

Flight

WEATHER

The

following

ground

track

Launch

Area

will

be

Winds

Ceiling

-- 5,000

Wave Planned

--

the

to and

gusts

base

during

along the

feet

feet

mission.

to 25 knots.

minimum.

maximum.

-- Eight

maxim1_u

cloud

-- Six miles

Landin$

base

minimum.

minimum.

_eet

maximum.

make

decision

Areas

director

will

based

upon

conditions

time.

Pararescue Surface

Winds

Ceiling

--

Visibility Waves

-- 25 knots

1,000

feet

-- Target

-- Five

feet

maxilm_n.

cloud

base

minimum.

visible.

maximum;

-more!

the

minimum.

-- 30 knots

1,500

Height

Flight

with

Conditions

Areas

Ceiling

Contingency

only.

prior

cloud

miles

-- Five

Winds

Wave

feet

-- Six

Surface

Visibility

lines

-- 18 knots

Height

Landln$

guide

evaluated

Surface

Visibility

at

are

REQUIREMENTS

swells

i0 or

ii feet

m_num.

53-

MEDI JAL CHECKS

At crew a

least

member.

check

one

medical

Performed

will

consist

measurement,

food

check over

of:

and

Solid secure

water

and

for

of bag

brought

Urine Co either

bacteria after back

WASTE

use

for

-- Secreted a collection

gas.

and

with

station,

blood

adhesive germicide

Adhesive

bag

each

pressure

evaluation.

Contains

and

ground

by

DISPOSAL

bag

to body.

be made

temperature,

intake

-- Plastic

attachment

formation seal

Wastes

will

a convenient

Oral

BODY

a day

is

stowed

lip

to provide

which

lip

also

in

empty

prevents

used

to

form

:food contai_'ler

analysis.

into device

fitted

-isor

or

6_ -

receptacle overboard

connected

dump.

by hose

GEMINI

The to

that

pressure wor_

by

the

extravehicular

It has

suit

worn

Gemini

6 SUIT

by

the

c L(_w )_[Gemmnm

5 crew.

It

is not

6 is identical

suitable

activity.

five

layers:

I. White cotton constant pockets to hold biomedical merit. 2.

Blue

3.

Black

nylon

comfort

wear undergarment instrumentation

neoprene-coated

5. White HT-1 wear and solar

with

suit

is a

n_rlon pressure

mechanically

environmental suit

through

him

with

in

cabin

The

suit,

pressure

sealed

visor.

control a

"suit

system. loop"

a breatheable maintains if cabin

nylon outer reflectance.

I_II

five

garment, Oxy[qen is

to cool

atmosphere

press1_re

layer

Gaseous

pounds

with equip-

layer. garment.

_. Restraint layer of dacron and teflon to restrain pre'_sure garmeut and maintai_

The

for

per

fails,

-more-

the

to protect

including

by

and

el" i00 percent inch

against

is provided

astronaut

net shape.

a helmet

_rnished

oxygen

square

link its

the to

the

provide

oxygen.

Oxygen

pressure.

is pressurized

to

3.7

psia.

55

FOOD

Number

of Meals

-- Three per day per astronaut

Type -- Bite sized and rehydratable. rehydratables

with special gun.

for two days.

Water is placed

Bite-sized

in

items need no

rehydration. Storage polyethelene, compartments right

-- Meals

individually

polyamide

laminate.

beside knees

wrapped

in aluminum

First day meals

of each crewman.

foil and

stored in

Second day meals

in

aft food compartment.

WATER MEASURING

A mechanical It consists cylinder

of a neoprene

mounted

ounce of water. pushes

water

measuring

crewman

system has been added to water gun.

bellows

at base of gun. When plunger

out of bellows

side of gun registers

SYSTEM

housed

The bellows holds one-half

of gun is depressed,

and through gun.

number

of times bellows

will record how much he drinks

beginning

in a small metal

and end of each use of gun.

-more-

a spring

A counter in right is activated.

by noting

numbers

at

Each

56 -

Day

J!,!

_]]

"A"

CALORIES

Bacon Square Potato Soup (Rehydratable) Gingerbread Peanut Cubes Grapefruit Drink (Rehydratable)

90 252 183 297 83 TOTAL

MEAL

CALORIES

"B"

Chicken and Gravy (Rehydratable) Cheese Sandwiches Strawberry Cereal Cubes Pineapple Fruitcake 0range-Grapefruit Drimk (Rehydratable) TOTAL CALORIES

92 32_ 171 253 83 9_

Salmon Salad (Rehydratable) Cinnamon Toast Butterscotch Pudding (Rehydratable) Brownies Grapefruit Drink (Rehydratable) TOTAL

2_6 99 117 241 83 7_

FIRST

-more-

CALORIES

DAY

- T()TAL

2,614.

57

Day,,#2

MEAL

Chicken Sandwich Shrimp Cocktail Date Fruitcake Coconut Cubes 0range-Grapefruit

-

"A"

CALORIES

(Rehydratable)

Drink

(Rehydratable) 'I_TAL CALORIES

MEAL

"B"

Tuna Salad (Rehydratable) Apricot Cereal Cubes Strawberry Cubes Peaches (Rehydratable) Grapefruit Drink (Rehydratable)

214. 171 283 98 TOTAL

MEAL

196 13.9 262 310 83 9-_

CALORIES

"C"

Bacon and Egg Bites Meat & Spaghetti (Rehydratable) Toasted Bread Cubes

178 'TO 161

Chocolate Grapelrult

307 83 7-_

Pudding,(Rehydratable) Drink _Rehydratable) TOTAL

CALORIES

SEC0_[D DAY

-more-

TOTAL

2,618

- 58 -

GEMINI

The lO

feet

the

Gemini

spacecraft

in diameter

top.

Its

two

adapter

section.

Reentry

Module

The at

its

recovery

the

and

its

module

It has

(R_R),

Rendezvous of

at major

reentry

base.

SPACECRAFT

and

spacecraft,

18 feet,

base

inches

and

sections

is

II

three

(2)

is conical, 39

are

feet

main

the

5 inches

in diameter

reentry

high

and

sections:

7½

module

feet

(I)

control

(RCS),

and

recovery

section

is

forward

drogue,

the

pilot

at and

in

(3)

and

the

diameter

rendezvous

reentry

containing

long,

and

cabin.

(small)

main

end

parachutes

radar.

Reentry

control

tains

fuel

and

eight

attitude

A parachute

section

between

oxidizer

tanks,

control

thrusters

adapter

assembly

R&R

valves, each

and

cabin

tubing for

and

is included

control

sections two

rings

during

for main

conof

reentry.

parachute

attachment.

Cabin crew

seated

each

seat

section

hull. between

side-by-side, is

a hatch.

Equipment pressure

corrugated

between

and

not

RCS their

Crew

shingled

and

adapter

instruments

compartment

requiring

hull

and

beryllium

to provide -more-

and

houses

controls.

is pressurized

pressurized

outer

secbion,

aerodynamic

which and

Above

titanium

environment shell

the

is

located

is

heat

protection.

- 59 -

- 6o

- 61 -

r_

.<

0 Z R

ev

ILl

>

- 62

-

- 63

Z

o

_o

\

_Y

_:

Dish-shaped

Adapter

shield

adapter

base,

is 7_

containing

Retrograde and

part

of

for

the

the

for

serves

as a radiator

end

of cabin

section.

environmental for

_ue

_eet

in diameter

equipment

four

the

and

i0

solid

cooling

at

sections.

retrograde

rocket:_

system.

batteries

for

electrical

maneuver

system

(OAMS),

control

system

(ECS).

cooling

_ystem,

also

power, primaT.y

It also contained

in the

section.

NOTE:

The

retrorockets jettisoned

equipment

are after

fired

se_tlon For

retres

Gemini

6 ca rrie_

cells,

is

re enSry.

are

,

The

il_ediately

terror, fade

section

before Js

PO%_:_RSYST[_I

, i J

I0 batterle:_'.

idcntical

j_ttisoned

fired.

ELECTRICAL

fuel

and

contains

attitude

for

use

large

and

contains

section orbit

high

retrograde

radiator

oxygen

equipment

feet

section

the

Equipment fuel

forlas the

Section

The its

heat

to

Future

thorpe uzed

_ore-

on

Gemini the

flights

Gemini

will

5 flight.

- 65 -

The

;['or

batteries

Adapter

this

flight

include:

}]etteries

three ;TOO-amp/hour units, housed in the adapter sectffon. Ju_mtry power

Main

Batteries

Squib

source.

four 40-amp/hour units in reentry section for power and during reentry.

Batteries

the prior

to

three 15-amp/hour units in the reentry section, used to trigger explosive squibs.

PROPELLANT

Total

Available

Mission

-- 669

Propellant

pounds

budget

with

RENDEZVOUS

Purpose

-- Enables

bearing

angle

System

computer

crew

to Agena.

can

0ispersions

-- ;[85 pounds

RADAR

to measure

Supplied

so crew

No

range,

data

determine

to

range

Inertial

maneuvers

rate,

and

Guidance

necessary

for

rendezvous.

Operation and

returns

width.

them

Radar

Location rendezvous

-- Transponder

and

to

on Agena

spacecraft

accepts

-- small recovery

only

end

receives

at

a specific

signals

processed

of

spacecraft

section.

-more-

on

radar

frequency by

impulses and

transponder.

forward

:['aceof

pulse

- 6_;-

Size

-- less

than

Weight

-- les_

Power

Requirement

two

than

cubic

70 pounds.

--

less

STATIC

Experimcnt;_ problem Agena

of during

conclusive. are with in

the

the

but

Thorefore_

installed

on

the

and

th_oe

Gemini

9'orce Titan of

two

Gemini

II

stages,

protruding

at

Vehicle

(GLV-6)

first

fingers

contact

to a ground

rate.

is a modified

ballistic

identical

launch

the

considev, ed

VEHIC_

intercontinental to

be

the

copper

carried

a controlled

LAUNCH

cannot

to make

be

_s no and

flexible

cone will

there

spacecraft

experiments

charge

dissipated

Launch

the

docking

GEMINI

The

5 indicated

these

Any

_0 watts.

between

Agena

spacecraft.

Agena

4 and

charge

docking,

than

CI_ARGE DEVICE

on Gemini

a static

feet.

missile

vehicles

U.S.

consigting used

in

previous:

flights.

HEIGHT

FIRST STAGE 63 feet

SECOND STAGI{ _7 feet

DIAMETER

I0

iO feet

THRUST

i_30,000 Pounds (two engines)

feet

-more-

Air

i00,000 Pounds (one engine)

- 67 -

FUEL

50-50 blend of monomethyl and unsymmetrical-dimethyl

OXIDIZER

Nitrogen tetroxide (Fuel ts hypergolic, eously upon contact

Overall Combined

height

weight

of

is about

Modifications Vehicle

mit

booster 2.

system

the

(NOTE:

Malfunction

GLV

for use 6 same

3.

Radio

guidance

4.

Retro

and

5.

New

6.

New

7.

Trajectory

_.

Electrical,

as

as

system

control

system

and

ignites spontanwith oxidizer.)

spacecraft

is

the

Launch

Gemini

GLV

i through

5)

added

to detect

and

to

system

the

added

to provide

substituted

for

inertial

second

stage

equipment

truss

added.

second

stage

forward

oxidizer

skirt

of

tracking

reqJirements

hydraulic

Vehicle the

a secondary

guidance.

deleted.

direction

trans-

fails.

rockets

Launch

feet.

crew.

vernier

Gemini

109

pounds.

information

flight

if primary

II

detection

performance

Back-up

vehicle

340,000

to Titan

include:

I.

launch

hydrazine hydrazine

Space

and

instr_J_en%

Comraand.

-more-

Division

added.

simplified°

pro_'_ram ma_a<_eme_Y_ Systems

assembly

of

systems

for the

NASA Air

modified.

is under Force

Systems

- 68 -

- 69 -

AGENA

The Agena

TARGET VEHICLE

target vehicle

for Gemini

of the U. S. Air Force Agena D upper space vehicles craft

which helped

6 is a modification

stage, similar

propel Ranger

to the

and Mariner

space-

to the Moon and planets.

It acts as a separate vehicle,

placing

launch

itself into orbit with its main propulsion,

and can be maneuvered crew, using

stage of the Atlas/Agena

either by ground

two propulsion

control or the Gemini

6

systems.

HEIGHT

(liftoff)

36.3 feet

Including

shroud

LENGTH

(orbit)

26 feet

Minus shroud and adapter

DIAMETER

5 feet

WEIGHT

7,000 pounds

In orbit,

THRUST

16,000 pounds 400 pounds

Primary Propulsion Secondary Engines

FUEL

UDMH

Dimethyl

OXIDIZER

IRFNA (Inhibited Red Fuming Nitric Acid) in primary propulsion system MON (Mixed Oxides of Nitrogen) in secondary propulsion system

COMBUSTION

IRFNA and UDMH are hypergolic, on contact

-more-

(Unsymmetrical

fueled

Hydrazine)

ignite

- 70

Primary and secondary Main engine places Agena orbital

changes.

firing engines,

thrusters

Attitude

by gimballing

mounted

on Agena

nection

Two 16-pound-

are fo_ ullage and vernier

control

(roll, pitch,

main engine,

yaw) is accom-

or by six nitrogen

jets

co Agena for use a_ Gemini

renaezvous

include:

Docking

collar and _qulpment

with Gemini

during

transponder

to permit mechanical

con-

flight.

2.

Radar

3-

Displays

and instrumentation,

plus strobe lights

locating

and inspecting Agena

before docking.

visually

aft-

aft end.

Modifications

1.

for large

system, two 200-pound-thrust,

are for small phase changes.

plished

spacecraft

systems are restartable.

into orbit and is used

Secondary

thrust, aft-flring adjustments.

propulsion

compatible

_.

Secondary

propulsion

5.

Auxiliary

equipment

with Gemini

radar. for

system for small orbital changes. rack for special rendezvous

equi)_-

ment and telemetry. 6.

Command

control

equipment

to allow control by Gemini

6

crew or grouna controllers. Agena prograxa management the Space Systems Division

for NASA is under

the direction

of the A_r Force Sy_tom_ Command.

-more-

of

ATLAS

The of

the

Atlas

modified

Standard U.S.

missile,

similar

Mercury

Astronauts

Atlas three

main

booster engine

to

Launch

Air

VEHICLE

Vehicle

Force

the

launch

into

orbit.

Atlas

stage

engines

then

engines

at

on

the

pad,

staging,

at

is a refinement

intercontimental which

dropping

ballistic

placed

vehicle,

allowing

thrusting

(SI_-3)

vehicle

is a one-and-a-half

to continue

vernier

LAUNCH

Project

igJtiting off

the

single

altitude,

aided

the

all

outboard

sustainer by

two

small

engines.

HEIGHT

66

Feet

DIAI_ETER

16 Feet i0 Feet 5 Feet,

I0

WEIGHT

260,000

T_musT

390,000 330,000 57,000

Minus

RP-I,

OXIDIZER

Liquid

Section

pounds

Fully Agena

minus

pounds pounds

Total at liftoff Two booster (outer engines) One Sustainer (center) engine Two small vernier engines for trajectory and final velocity control

inches

pounds

a hydrocarbon Oxygen

-more-

Payload

Lower Booster Tank Sections Tapered Upper

Balance

FUEL

Agena

at

fueled, payload

resembling -297

degrees

End

kerosene F.

- 72

COMBUSTION

Unlike Titan's hypergollc, spontaneous ignition, Atlas combustion is achieved by forcing propellants to chambers under pressure, burning them in gas generators which drive propellant pump turbines.

Modifications the

Gemini I.

Special

2.

Improved

3. Agena

upper

to

6 mission

simultaneous

Atlas

system

propellant

Increased

Standard

Launch

Vehicle

for

include:

autopilot

of

for

rendezvous

utilization

both

thickness

fuel

and

of Atlas

system

mission. to

assure

oxidizer.

structure

for

support

of

stage.

4.

Simplified

5.

Retrorockets

interstage 6.

the

depletion

upper

-

pneumatic moved

adapter

system. from

exterior

equipment

pods

to

section.

Uprated

MA-5

propulsion

Modular

telemetry

system

(used

on

late

Mercury

flights.) 7.

Atlas is under Force

Standard

Launch

the

direction

Systems

Command.

of

kit

tailored

Vehicle the

Space

-more--

for

program Systems

each

mission.

management Division

for of

NASA

the

Air

_],ooo, ooo'.

a,

9ooooo

START ROLL O.

LIFTOFF 556

RANGE,_L_fi_LNJLES

1085

7B-

CREW Walter

M.

(for

Marty)

BIOGRAPHIES Schirra,

Jr.,

Gemini

6 command

pilot BORN:

Hackensack,

HEIGHT: 5 feet, brown eyes EDUCATION:

N. J., l0

inches

Bachelor Academy,

_,I_RITAL STATUS:

CHILDREN:

12,

M.

Ill,

1923

WEIGHT:

of Science 194-5

Married Seattle,

Walter

Mar.

to the Wash. June

170

lbs.

degree,

United

former

Josephine

23,

1950;

Brown

hair,

States

Naval

Fraser

Suzanne,

of

Sept.

29,

1957

EXPERIENCE: Schirra, a Navy Captain, received flight training at Pensacola Naval Air Station, Fla. As an exchange pilot with the United States Air Force, 154th Fighter Bomber Squadron, he flew 90 combat missions in F-$4E aircraft in Korea and downed one MIG with another probable. He received the Distinguished Flying Cross and two Air Medals for his Korean service. He took part in the development of the Naval Ordnance Training Station, China was project pilot for the FTU3 Cutlass for the Cutlass and the FJ3 Fury. Schirra Fighter

Sidewinder missile at Lake, Calif. Schirra and instructor pilot

the

flew F3H-2N Demons as operations officer of the 124th Squadron onboard the Carrier Lexington in the Pacific.

He attended the Naval Air Safety Officer School at the University of Southern California, and completed test pilot training at the Naval Air Center, Patuxent River, Md. He was later assigned at Patuxe_t in suitability development work on the F_H. He has more 2,700 hours

than 3,_00 hours in jet aircraft.

flying

Schirra 1959.

one

Mercury

was

of

the

seven

-more-

time,

including

astronauts

more

named

tha_

in April

On Oct. j,_ I<)62, Schlrra flew a zJx-orbit mi_._on_'"" in hie "SigriJa 7" spacecraft. The fligbt la;Jted n_ne hours and 13 minutes from liftofi" th:eo,_gh lar_d_ng anc_ he attained a velocit_ of' 17,5_'/ miles (28_200 kilometers) per hour, a rr, aximum orbital altitude of 175 statute miles (281 kilometers) and a total range of almost I_L[,O()O statute miles (231,'#00 k_lometers). The impact point was in the [acifie Ocean, about 275 miles (4213 kilometers) northeast oi,'Midway Island. He was awardec] the NASA Distinguished Service Medal for h.L_ flight. He was the backup conmland pilot for the Gemini 3 mission. Sehlrra is the son c_f _r. and Mrs. Walter _4. ,_.hlrraj _'_ " St., San Diego, Calif.

[email protected]

- 75

Thomas BORN:

P.

(for

Patten)

Weather,or,d,

H_IGHT.

6 feet

EDUCATION:

_¢_RITAL

• CHILDREN:

Okla., WEIGHT:

,_ta..iord, GeminA Sept. 175

].7, 19[JO Ibs.

Black

B_chelor of essence d_o_co Naw_l Academy, 195-]-

STArI_CS:

July

") 195}[; ,_,

hair,

olue

Prom Univc

Married to the former Weatherlcrd, Okla.

Dianne,

6 pilot

Faye

Karmn, ..

L.

Aug.

EXPERIENCE: S_afford, an Air Force ha jot, the United States Air Force upon graduabion Naval Academy at Annapolis. Following his he flew fighter _.nterceptor a_.rcra_ in the and Germany, and later attended the United Experlmental Flight Test School at EJward Calif.

cy_;S

{ St___te_:_

Shoemaker

of

_=_, ,)o .19_I _,

was coI_mlmssmo_o_] im from the U. S. flight training, United _tat ..... Stat_-, Air Force Air Force ]]asc,

He served as Chief of th<; Performance Branch, USAF Ac_o_pac_ Research Pilot School at Edwards. In this assignment he was responsible for supervision and administration of the flying, curriculum for student test pilots He e_c,,b]._._acd ........ ' text books and participated in and directed the wrJ.til_g of ?li[.j_ test manuals for use by the staff and students. Stafford

is co-author

Flisht Testin_ Testin$.

and

of

the

Aerody-nammc

He has logged more than than 3,000 hours in jet

Pilot's

Handbook

Handbook

4-,300 hours aircraft.

flying

for

Perf0_ancc

Performance

FliJ_t

tim(), muclu(_m_<_ more

Stafford was one of the nine astronauts named by NASA in September 1962. He was the backup pilot for Gemini3. Stafford is the son of Mrs. Mary E. Stafford and the late Dr. Thomas o Staf2ord, Weatherford, Okla.

-l_10re -

- 76

Virgil I. command pilot BORN:

(ffor Ivan)

Mitchell,

Ind.,

HEIGHT: 5 feet brown eyes

7

"Gus"

April

inches

,

Grissom,

3,

Gemini

0 backup

]926

WEIGHT:

]50

lbs.

Brown

hair, )

EDUCATION:

MARITAL

CHILDREN:

Bachelor of from Purdue

STATUS:

Science degree University

Married to the Mitchell, Ind.

Scott,

May

16,

]-950;

former

in mechanical

Betty

_4ark, Dec.

L.

30,

engineering

Moore

of'

1953

:_

EXPERIENCE: Grissom is a lieutenant colonel in the United States Air Force, and received his wings in March 1951. He flew i00 combat missions in Korea in F-86's with the 334th FighterInterceptor Squadron. He left Korea in June 1959 and became a jet instructor at Bryan, Tex. In August 19D5, he entered the Air Force Institute of Technology at Wright-Patterson Air Force Base, Ohio, to study aeronautical engineering. In October 1956, he attended the Test Pilot School at Edwards Air Force Base, Calil'., and returned to WrightPatterson Air Force Base in 1957 as a test pilot assigned to the fighter branch. Grissom has logged more than 4,000 hours flying time, _cludLng more than 3,000 hours in jet aircraft. He was awarded th_ Distinguished Flying Cross and the Air' Medal with Cluste_' i'_, service in Korea. Grissom was named in April 1959 as one of the seven Mercury astronauts. He was the pilot of the Mercur_-Redstone 4 (Liberty Bell 7) suborbital mission, JuIy 21, 1961 and the command pilot of the Gemini 3 mission.

:

He is responsible for the one of three organizational Apollo and Operations).

Gemini group in the Astronaut units im that office. (The

Grissom

and

is the

son

of Mr.

Mrs.

-moreL

Dennis

Grissom,

0ff]ce, others

M_tcheil,

-

Ind.

- 77 -

John BORN:

San

W.

(for

Francisco,

HEIGHT: 5 feet green eyes EDUCATION:

MARITAL

Young,

Calif.,

9 inches

Gemini Sept.

WEIGHT:

6 backup

24,

1930

172

Ibs.

pilot

Brown

hair,

Bachelor of Science degree in aeronautical engineering from Georgia Institute of Technology

STATUS:

CHILDREN:

Watts)

Married to the Savannah, Ga.

Sandy,

Apr.

30,

former

1957;

Barbara

John,

Jan.

V.

17,

White

of

1959

EXPERIENCE: Upon graduation from Georgia Tech, Young entered the United States Navy and is now a Commander in that service. From 1959 to 1962 he served as a test pilot, and later program manager of F4H weapons systems project, doing test and evaluation flights andwriting technical reports. He served as maintenance officer for all-weather Fighter Squadron 143 at the Naval Air Station, Miramar, Calif. In 1962, Young set world time-to-climb records in the 3,000 meter and 25,000 meter events in the F4B Navy fighter. He has logged more than than 2,700 hours in jet Young was among the in September 1962. He

is the

son

of Mr.

3,200 hours aircraft.

flying

time,

including

group of nine astronauts selected He was the pilot of Gemini 3. and

Mrs.

William

-more-

w

H.

Young,

more

by NASA

Orlando,

Fla.

- 7_

PREVIOUS

Gemini

I, Apr.

Unmanned

8,

to

test

vehicle

and

days.

No

Gemini

2, Jan.

flight,

using

launch

vehicle

performance

second

Unmanned

adverse

shut

engines

recovered

Gemini

3, Mar.

First John 53

W.

expected out

Young

23,

area

in

lift

Mercury

of

launch

environment. for

Space-

about

four

qualify

spacecraft

Delayed

three

Cleo

and

malfunction

of hydraulic

ballistic

times

Dora.

into

heat

by

December

detection

component

reentry

reentry

system

failure.

Atlantic

Space-

Ocean.

1965

flight, crew.

Landed

of plane,

orbital

after

as

ability

orbited

hurricanes after

because

manned

minutes.

landing

including

down

to

systems.

terminated

craft

launch

vehicle

flight

spacecraft

attempt

and

spacecraft,

1965

ballistic

weather,

launch

launch

production

attempted.

19,

and

first

to withstand

stage

recovery

protection

FLIGHTS

1964

spacecraft

craft

GEMINI

orbital

Gemini and

-

after

flight,

earth

50 miles

own

Virgil

three

(81

because

reentry. its

Astronauts

Orbited

about

Atlantic

during

with

orbit.

is first

manned Grissom,

man

-more-

to

times

fly

did

short

not

into

hours, of planned

provide

spacecraft who

and

in four

kilometers)

spacecraft First

I. Grissom

made space

to maneuver subtwice.

.... 19 -

Gemini

4, June

Second landed

3-7,

manned

of flight.

pilot.

Astronaut

21 minutes

of

maneuvering

quantity

Guidance

System

Longest

(Pete)

Conrad,

22 hours

Conrad,

on

of

flight,

excellant ground

Spacecraft Atlantic

landed recovery

information

has

held

to perform

because

of in

zero-lift

more

time

insuf-

Inertial

reentry.

Failure

of

management

permitted about vessel

100

miles

because into

-more

is first

-

than

in

to make

any

heating

system

mission

during power,

cells

by

flight

kilometers)

two

other

of oxygen

(161

onboard

times

second

complete

of

120

Cooper

world's

electrical

to

Gordon

becomes

of fuel

crew

L.

eart_

in space

flight,

use

the Cooper

threatened

careful

programmed

circled

space

system

operational

personel,

a hand

Attempt

Astronauts

59 minutes.

astronaut.

but

accomplished

Malfunction

to perform

Jr.,

first

supply

command

using

failed

om record.

and

flights;

experienced cell

stage

was

59

1965

flight

human.

space.

and

97 hours,

pilot,

(EVA),

fuel.

crew

space

space

day

second

after

II was

in

of maneuvering

21-29,

orbital

in fuel

GLV

required

5, Aug.

most

White

time

62 revolutions

A. McDivitt

Activity

first

with

ficient

days,

H.

area

James

Extravehicular

near-rendezvous

seven

Astronaut

for

completed

recovery

Edward

unit

Charles

flight

Atlantic

minutes

and

Gemini

in primary

Gemini

1965

first and

both

crew

and

successfully. from

erroneous

base-line

computer,

although

primary

computer

itself

performed

as

transponder-bearing celled

because

- _O

-

Plan

to rendezvous

planned. pod

of problem

carried with

aloft fuel

-more-

by Gemini cell

oxygen

with

a

5 was supply.

can-

f

•

- 81

U.o. MISSION

MR-3

MANNED

SPACECRi_'T HRS. MIN.

(Shepard)

_4R-4 (Grissom)

HRS. SEC,

,_PACJ FLIGHTS MANNED HOURS IN MISSION HRS. MIN. SEC.

T'OTAL mANNED CUMULATIVE HRS. MIN.

I{RS. SEC.

15

22

15

22

15

22

].5

37

15

37

30

59

MA-6

(Glenn)

4

55

23

4-

55

23

5

26

22

MA-7

(Carpenter)

4

56

05

4

56

05

IO

22

27

MA-8

(Schlrra)

9

].3

ii

9

13

Ii

19

35

38

MA-9

(Cooper)

34

19

49

34

19

49

53

55

27

Gemini 3 (Grissom & Young)

4

53

O0

9

46

O0

63

41

27

Gemini 4 (McDivitt & White)

97

56

Ii

195

52

22

259

33

49

Gemini 5 (Cooper & Conrad)

190

56

Ol

381

52

02

641

25

57

-more-

- 92 -

PROJECT George

E.

william

OFFICIALS

Mueller

C.

Associate Office of

Schneider

Flight, Acting

NASA Headquarters Director, Gemini

Deputy Office

Director, of Manned

NASA E.

E.

Christensen

Administrator, Manned Space

Gemini Space

Program. Program, Flight,

Headquarters.

Director,

Mission

Operations,

NASA Headquarters Mission Director Charles

W.

Mathews

Christopher

C.

Kraft

Gemini Manned

Program Manager, Spacecraft Center,

Flight

Director,

Spacecraft G.

Merritt

Preston

Deputy Launch

Gen.

Leighton

I.

Davis

USAF,

Manned

Center,

Houston

Mission Director Operations. JFK

Center, Lt.

Houston.

for Space

Fla. National

Range

Division

Commander and DOD Manager of Manned Space Flight Support Operations Maj.

Gen.

V.

col.

Richard

G.

Huston

USAF,

Deputy

DOD

Manager

C.

Dineen

Director, Directorate Gemini Launch Vehicles, Space Systems Division, Air Force Systems Command

Lt.

Col.

John

G.

Albert

Chief, 6555th Air

Gemini Launch Division, Aerospace Test Wing,

Force

Kennedy, R.

Admiral

B.

W.

Sarver

USN,

-more-

Missile

Test

Center,

Fla.

Commander

Task

Force

140

Cape

--

SPACECRAFT

McDonnell tractor

for

Aircraft

the

St.

The Eagle Pitcher Joplin, Mo. Corp. York,

Northrop Newbury

Co.

Co.

Corp. Park, Calif.

con-

Environment System

Control

Guidance

Parachutes

OAMS,

RCS

Calif.

Chemical Md.

_ontractors

Corp.

Retrorocket

Ejection

Corp.

Rendezvous

System

Seats

Radar

System

include:

General Dynamics, Div., San Diego,

Convair Calif.

Airframe and Integration

Roeketdyne Div., North American Aviation, Inc., Canoga Park, Calif.

Propulsion

General Electric Co., Syracuse, New York

Guidance

II

prime

include:

Computer,

Westinghouse Electric Baltimore, Md.

Titan

Others

is

Batteries

Weber Aircraft Corp. Burbank, Calif.

Atlas

Mo.,

N.Y.

Rocketdyne Canoga Park, Thiokol Elkton,

Louis,

spacecraft.

AIResearch Manufacturing Los Angeles, Calif.

IBM New

--

CONTRACTORS

Corp.,

Gemini

C_ -)

Contractors

Systems

Systems

include:

Martin Co., Baltimore Divisions, Baltimore,

Md.

Aerojet-General Corp., Sacramento, Calif.

Airframe and Integration Propulsion

-mo.ce-

Systems

Systems

Titan

Agena

II contractors

(cont.)

General Electric Syracuse, N.Y.

Co.,

include: Radio Command System

Burroughs Corp., Paoli, Pa.

Ground

Aerospace Corp., E1 Segundo, Calif.

Systems Engineering Technical Direction

D contractors

Suit

Guidance

Computer

and

include:

Lockheed Missiles and Space Co., Sunnyvale,

Food

Guidance

Calif.

Airframe and Integration

Bell Aerosystems Co., Niagara Falls, N.Y.

Propulsion

McDonnell Aircraft St. Louis, Mo.

Target

Co.,

Systems

Systems

Docking

Adopter

contractors: U. S. Army Laboratories, Natick, Mass.

Food

Whirlpool Corp., St. Joseph, Mich.

Procurement, Packaging

Swift and Pillsbury

Principal

Co., Co.,

Chicago and Minneapolis

contractor: The David Worcester,

R. Clark Mass.

Co.,

Formulation

Concept

Processing,

Food

Contractors

- 85

ABBREVIATIONS

AND

SY_0LS

FREQUENTLY

USED

ASC0

AUXILIARY

SUSTAINER

CGLVTC

CHIEF GEMINI CONDUCTOR

LAUNCH

VEHICLE

GATV

GEMINI

TARGET

VEHICLE

ECS

(S/C ) ENVIRON_ENTAL

ETR

EASTERN

FLT

FLIGHT

DIRECTOR

GAATV

GEMINI

ATLAS

GEN

GENERAL

GLV

GEMINI

GN2

GASEOUS

GT

GEMINI

IMU

INERTIAL

IRFNA

INHIBITED

LC

(14)

LAUNCH

CONDUCTOR

LD

(lJ_)

LAUNCH

DIRECTOR

- COMPLEX

14

LD

(19)

LAUNCH

DIRECTOR

-COMPLEX

19

L_'LD

LAUNCH

MISSION

LN2

LIQUID

NITROGEN

L02

LIQUID

OXYGEN

LTC

LOCKHEED

MCC

MISSION CONTROL CENTER (DEFINED WITH THE WORD

AGENA

TEST

TEST

CONTROL

SYSTEM

RANGE (HOUSTON)

AGENA

LAUNCH

TARGET

VEHICLE

VEHICLE

NITROGEN TITAN MEASURING RED

TEST

MISSION

OAMS

ORBIT

ATTITUDE

PCM

PULSE

CODE

UNIT

FUMING

NITRIC

- COMPLEX

ACID 14

DIRECTOR

CONDUCTOR

DIRECTOR

(GEMINI) -more-

OFF

INFORMATION

MD

S/C

CUT

HOUSTON

OR

(HOUSTON) MANEUVERING

MODULATIC':

SPACECRAFT

SYSTEM

CAPE)

86

SPCFT

CHIEF

SLD

SIMULTANEOUS

SLV

STANDARD

(ATLAS)

STC

SLV

CONDUCTOR

SRO

SUPERINTENDENT

OF

TDA

TARGET

ADAPTER

UDHM

UNSY_ETRICAL

WMSL

WET

- END

-

SPACECRAFT

TEST

DOCKING

MOCK

TEST

LAUNCH

CONDUCTOR

DEMONSTRATION

LAUNCH

RANGE

VEHICLE

OPERATIONS

DIMETHLHZDRAZINE

SIMULATED

LAUNCH