Nasa Gemini 7 / Gemini 6 Press Kit

IqATIONAL

AERONAUTICS AND SPACE ADMINISTRATION WASHINOTON DC 20546

FOR

RELEASE

RELEASE:

TELS. wc) 9-41',s WO _-6925

MONDAY P.M. November 29,

N0:65-362

1965

PROJECT: a :Nr 716

CONTENTS Title GENERAL

Page NEWS

RELEASE ..................

=.........

1-3

Launch Vehicle Countdown ........................ 4 Nominal Mission Plan - Gemini 7 ................. 5-6 Gemini 7 Experiments .................. ...... =---7-14 Experiments Flown on Earlier Missions ........ 7 In-Flight Exerciser .......................... 7-8 In-Flight Phonocardiogram .................... 8 Bone Demineralization ........................ 8-9 Human 0tolith Function ....................... 9 Proton-Electron Spectrometer ................. 9-10 Tri-Axis Magnetometer ........................ i0 Celestial Radiometry Space Object Radiometry-10-11 Simple Navigation ............................ ii

K

Synoptic Weather Photography ................ -12 Visual Acuity Astronaut Visibility ........... 12-14 Experiments to be Flown for the ................. First Time ...... 15-20 Synoptic Terrain Photography 11-12 Bioassays Body Fluids ..... z.................. 15 Calcium Balance Study ........................ 15 In-Flight Sleep Analysis ..................... 15-16 Optical Communication ........................ 16-18 Landmark Contrast Measurements ............... 18 Star Occultation Navigation .................. 18-20 Camera Equipment for Gemini 7 and 6 Missions .... 21-22 16 MM Maurer Movie Camera .................... 21 70 MM Hasselblad Camera ...................... 22 Gemini

7 to be

launched

no

Gemini

6 to be

launched

nine

-more-

earlier days

than later

Dec.

4,

1965.

/

-2-

Gemini 7 Fourteen Day Menu Cycle ................ Menu I, Menu II .............................. Menu III, Menu IV ............................. Gemini 6 Launch Preparations .................... Launch Vehicle Countdown - Gemini 6 ............. Nominal Mission Plan - Gemini 6 ................. Launch Windows ............................... Gemini 6 and 7 Rendezvous Orbit Geometry ..... Gemini 6 Experiments ............................. Gemini 6 Menu ................................... Manned Space Flight Network Gemini 6 and 7 Missions ........................................ Prime Computing Support ...................... Other Computer Support ....................... Network Readiness ............................. Tracking Two Manned Spacecraft .................. Orbits - Revolutions ............................ Crew Training Background ........................ Immediate Pre-Flight Crew Activities ............ Flight Activities ............................ Crew Safety ...................................... Survival Package .............................. Gemini 6 Suit .................................... Gemini 7 Suit .................................... Medical Checks ................................... Body Waste Disposal .............................. Food ............................................ Weather Requirements ............................ Planned and Contingency Landing Areas ........... Gemini Spacecraft ................................ Reentry Module ................................ Adapter Section .............................. Propellant ...................................... Rendezvous Radar ................................ Electrical Power Systems ........................ Gemini 7 ...................................... Gemini 6 ..................................... _el Cell Diagrams .......................... Gemini Launch Vehicle ........................... Crew Biographies ................................. Previous Gemini Flights ......................... Project Officials ............................... U.S. Manned Space Flights (chart) ............... Spacecraft Contractors .......................... NOTE

TO

EDITORS:

Supplemental information rapidly as it develops. -more-

will

be

released

as

23-24 23 24 25-28 29 30-34 30 32 35 36-37 38-39 38 38-39 39 39-40 41 42-43 I_4-45 45 46-47 46-47 48 49 50 50 50-51 52 53 54-59 54 54 59 59-60 60-63 60-61 61 62-63 64-65 66-74 75-77 78 79 80-81

NEWS

NA11ONAL

AERONAUTICS SPACE ADMINISTRATION WASHINGTON, AND D.C. 20546

FOR RELEASE

NO:

RELEASE:

TELS.

wo_4,5 WO

MONDAY P.M. November 29,

1965

Aeronautics

and

65-362

GEMINI?/6 FLIGHT TO

ATTEMPT

LONG

Within

the

next

Space

Administration

space

missions--a

rendezvous

of

Gemini launched

no

launched

is

a

Success

in

i.

longest

The

Astronauts

L.

190 hours

and

2.

The

later,

two

first

rendezvous

flights

space

of up

two manned

to

14 days

and

is

scheduled

to be

with

Gemini

is

7,

to be

13.

will

manned

Cooper

56 minutes,

out

4.

Dec.

U.S.

Gordon

carry

flight,

Dec.

will

the

to

National

spacecraft.

than

days

the

flight

long-duration

6, which

nine

weeks,

scheduled

Gemini

earlier

Gemini

three

MISSIONS

long-duration

two

7,

RENDEZVOUS,

DURATION

represent:

and

flight

nearly

Charles eight

rendezvous

to

date

Conrad

(Gemini were

in

5 flight

days).

of two

manned

maneuverable

spacecraft. -more-

'3-6925

11/23/65

--2--

from

3.

A minimum

the

same

Despite missions will major

Oct.

25

have

Gemini

availability

been

out

made

in

will

launch

which

be

That

Gemini

missions

The have

flight,

the

only

docked

two

Gemini

one the

plan.

prepared

the

a for

Target

change

with

Gemini

to

Agena

major

7

No

according

the

when

two

planned.

out

to

the

is,

7 flight

carried

to

6,

originally

postponed

orbit. was

forthcoming

the

is that

Agena.

spacecraft

will

connected.

decided

that

the planned

the

Gemini

6 launch

oheoked

out

on Pad

19)

out

of two

of Gemini

identical

was

to achieve

as

of

(already

launch

independently.

carried

is nearly

be physically

carry

out

6 spacecraft

It was

for

objective

6 mission

which

failed

In the not

carried and

Gemini

plan

Vehicle the

rendezvous

be

changes

flight the

the

launched

The

time

pad.

will

be

turn-around

a rendezvous

of

two

schedule vehicle

presented manned

-more -

an

of and

Gemini

spacecraft

opportunity

vehicles.

7 and

to

the

-3The devoted crew

first to

carrying

will

Gemini

6.

Gemini

7

the

During crew

the

will

only

days

the

Gemini

experiments.

At

out

maneuver

performing better

several

spacecraft

into

rendezvous

maintain

those

of

about

maneuvers

five

a target

attempt

their

7 mission

by

orbit

and

required

will

be

days

the

orbit

Gemini

6,

for the

spacecraft

to make

attitude,

themselves

a

target.

Following begin

a successful

liftoff,

to achieve

rendezvous

maneuvers

fourth (fly

orbit.

Following

formation)

quently, craft

Gemini

day,

proximately

Gemini landing

in

Ocean 8:20

fly

about

formation

reenter

the

after

about

a.m.

which Gemini two

isplanned 6 will

for

station

revolutions.

on Gemini

will

6 for

its keep

Subseone

space-

same

Earth's

atmosphere

46 hours

and

and

land

45 minutes,

in

will

area

be

about

329

at approximately

hours

8 a.m.

later.

(BACKGROUND

INFORMATION

-more-

and

FOLLOWS)

30 minutes,

EST,

two

the

at ap-

EST.

7 duration the

7 for

6 immediately

40 minutes.

6 will

Atlantic

Gemini

7 will

about

Gemini West

on

rendezvous,

Gemini

days

-4-

LAUNCH VEHICLE COUNTDOWN

Gemini 7

F-3 days

Start pre-count

F-1 day

Start mid-count

T-12 hours

GLV propellant loading

T-390 minutes

Complete propellant loading

T-300 minutes

Begin terminal countdown

T-120 minutes

Flight Crew to Complex 19

T-lO0 minutes

Crew enters spacecraft

T-75 minutes

CloSe spacecraft hatches

T-50 minutes

White Room evacuation

T-35 minutes

Begin erector lowering

T-15 minutes

Spacecraft OAMS static firing

T-O4 seconds

GLV ignition

T-O seconds

Liftoff

T+2 minutes, 36 seconds

Booster engine cutoff (BECO)

T+5:41

Second stage engine cutoff (SECO)

T+6:ll

Spacecraft-launch vehicle separation

-more-

t

-5-

NOMINAL

MISSION

_L_

Qe_ini-7 Gemini-7

is scheduled

to be launched

e:3opmEST, December

at about

orbit with an apogee

sustainer

engine

Immediately turn around

It will be launched

of 210 miles

orbit will be inclined The spacecraft

4.

28.87

from Complex

and 8 perigee

degrees

is to separate

to blunt

from

the booster

spacecraft

end forwsrd,

separation,

and begin

stsge.

Station

minutes

ground

elapsed

time (GET) from liftoff.

into about five minutes

before

radiometry

of the first

AS three hours,

keeping

experiments

darkness

50 minutes

to 12£ miles.

several

keeping

continue

darkness

on the

for sbout

This

will

25

time extends

period. during

the

lift-off

will be fired

as the spacecraft

in a posigrade

This m_neuver

is

maneuver

establishes

a space-

of 15 days. days

of the flight

will

be devoted

to conducting

experiments.

At about five

days in flight

craft orbit to provide maneuvers

the spacecraft

will be conducted

after

to raise the perigee

assigned

_fter

period.

thrusters

lifetime

will

the first

at its third apogee,

The next

The

30 seconds

station

second

craft orbital

of I00 miles.

rio the equator.

booster

remainder

into an elliptical

cutoff. following

Celestial

19, Cape Kennedy

required

and the expected 19 hours and four

the proper

will depend

liftoff

the crew will circularize target

orbit

on the decay

ti_J_ of Gemini

_,inutes following

for Gemini

rate

6.

of the Gemini

6, now planned

Gemini

the speceThe exact 7 orbit

for eight

d_ys,

7 liftoff.

-more|,

-6-

Under present

plans,

120 hours after lift-off the spscecraft change

circularization of the Gemi_

a posigrsde

of velocity

msneuvers

will be performed

7 spscecrafto

thrust at apogee.

of 1OO feet per second

The crew will

This will

give

result in

and circularizstion

st 185

miles. The rendezvous described

in the Gemini

The remsining completion retrofire

portion

near

6 Nominal

Gemini

of rendezvous

of the Gemini _ission

7 experiments activities.

6 and Gemini

recovery

szes st

will be conducted The Gemini

the beginning

-more-

is

_lsn.

the end of the 206 th revolution.

the West Atlantic

7 spececrsft

following

7 crew will initiate Landing

will be

of the 2OTth

Jn

revolution.

-7-

G_MINI Twenty continuing

7 mXPE_.Ik_';NTS

experiu,ents are scheduled

for Gemini

experi_:,ents end hsve been csrried

sbosrd

flights,

in repeating

missions,

experi_,sters hope to gsin date covering

under

varying

flight

these over 8 number

7.

3Jmilsr flight

carried

st a symposium

on Ear$ier

Cardiovasculsr

spsce flight

s ntm,ber cf subjects

sbo_rd

Gemini

in Wsshington

missions

esrly

during

J

this fell.

the msnned

sp_ce

experi_ent

cardiovascular induced

in-Flight

incressing

Exerciser

to perfom_

performance.

blood

cycle lssts

below

two minutes

control

meesure

are built

periodicelly

pressure

of cyclic

distribution

The cuffs

the enviro_ental

The objective capsci_y

weightlessness.

pressurization

oxygen from

(heart snd blood

the thighs 8nd infleted

_,ercury pressure, automstic

the effectiveness

on the thighs ss e preventive

deeonditionJng

sround

(5)*

will determine

cuffs

by prolonged

spscesuit

Pdssions

Conditioning

tions of pneumstic

2.

Gemini

program.

This

uses

of manned

sym pc s ia will be held perlodic_lly

_Lxperiments Flown 1.

previous

ere

conditions.

.%esults of the experiments and 4 were presented

Fourteen

Jnflrof

system) into

the

to 80_sJ of

the cuffs. out of every

Th_ six _nd

systen_.

(4 snd 5)

of this experiment physicsl

The rapidity

is to sssess

work 8nd their

with which

-_ore

cspability

the hesrt

*ind" c_:te_ prev_ ous Gemini mission --

the sstron_uts' for sustsin_d

rste returns

to ncrme]

-8-

after

cessetion

physical

of exercise

fitness.

of exercise exercise

A workload

device

that requires

to e nylon handle

device

to determine In-_li_ht

Phonopardiogrsm

cf a _uscle

A microphone cardiac

apex.

on sn onbosrd

consists

the cepecity

obteined

4.

and

The purpose degree

st the other

end.

the control

of en astronaut's

the time _nterv_l

heart

between

the

of its contraction.

to sn estron_:ut's chest

recorder.

during

the flight

The sound

froJ_;e slmulteneous between

trace

will be recorded

will be eompored

inflight

electrical

well _t the

elec_rocgrdiogram

activetion

of the

systole.

(& and ))

of this experiment

of bone demineralisation

tion associated

cords attached

in spece.

_he onset of Ventriculsr

Bone De_dnoralizatiqn

of bungee

foot strop

state

detected

to deter_.ine the time interval heart muscle

on an

(4 and 5)

end the onset

biomedical

to the waveform

for work

by _,easuring

sounds

periods

for 30 _econds

will be colJ,peredwith

will be epplied

Heart

by specific

sn_otmt of effort.

of e p_r

the fatigue

will be deteyn_ned

activation

s known

deta obtained

in this experiment muscle

be provided

st one end and a nylon

fhe in-flight

3.

will

of an indiv_du_l's

st the rate of one pull per second

The exercise

data

is an indication

is to establish

influenced

with the cockpit

the occur_nce

by the rel_tive

of the G_mini

spscecreft

end

h,,m_obJliz_and weight-

lessness. _pecial terminal

bone

X-rays

will

be token

of the fifth digit

of en astroneut's of the right hend.

-more-

heel bone Three

end the

pro-flight

_ ......

-9-

and three post-flight exposures will be taken of these two bones _nd compared to determine if any bone demineralization has occurred due to the spece flight. The equipment to be used in this experiment will be closely calibreted clinicel X-ray machines, stendard ll-lnch by 14-inch X-rey films and calibrated wedge densitometers. 5.

Human _tolith _unction (5) A visual tester will be used to detern_ne the _stron_uts orienta-

tion capability during flight.

The experiment will me_sure changes in

otolith (gravity gradient sensors in the i_er

ear) functions.

The tester is a p_ir of special light proof goggles, one eye piece of which contains a light source in the form of a movable white line.

The astronaut positions the white line with a c_librated knurled

screw to what he judges to be the r_ght pitch axis of the spacecraft. The second astronaut then reads and records the numbers. 6.

P_roton-_lect_n_S_ectrometer (4) In order to determine the degree of hazard, if any, to which the

crew will be subjected on space flight, it is necessary to project what radiation environment any given mission will encounter.

Specif-

icelly, this experiment will meke measurements outside of the sp_cecraft in a region where the inner Ven Allen rediation belt dips close _o the earth's surface due to the irregular strength of the e_rth's magnetic field.

This region is usually referred tc Ps the South

Atlantic Geomagnetic Ano_mly.

-more-

-iO-

This measurement crystal,

charged-psrticle

the spacecraft. rmdie_icn levels 7.

on future

from

a_plitude

this experiment

magnetic

will

Spectrometer

The magnitude

be performed

experiment

Celestial rmdiometry Space Object ?_diometry The results

radiation

channel _ichelson cooled

includes

operate

with respect

through

the South

with respect in conjunction

by orienting

Atlantic

Geomag-

of the e_rth's

to the spacecraft. with

the fie]d,

The

the Proton Electron

line direction

and

(5) will provide

bodies

a three-channel

and various

section

information objects

region.

-more-

_ dual-

and a cryogenically radiant

intensity

The sensing

and ere directed

the spacecraft.

on

in space.

spectro-rsdiometer,

can measure

the infrared

adapter

tri-sxis

p_rticles.

The equipment

through

and

to pn orbStlng

en adepter-_,ounted

Interferometer-Spectrometer,

in the Gemini

objective

r_d]_t]on

the direction

of the three directions

of celestial

spectrometer.

the ultra-violet housed

field

of these experiments

intensity

Instrtm,entation

_nd to predict

is to monitor

to determine

pitch angle of the impacting 8.

will

field will be measured

measurement

of

will be used to correlate

the spacecraft

,mgneto_,_eter ss they pass

magnetic

assembly

(&)

The astronauts

Anomaly.

of a scintJllati_g-

mou_]ted on the _dapter

of this experiment

of the earth's

spacecraft.

by means

space n,ission.

_agnetometer

The purpose

fluxgate

Data

analyzer

_,easure_ents made inside

Tri-Axis

netic

will be accomplished

units

toward

the

from _re

-ll-

The objectives for these experiments are to determine the onset of sensitivity values for earth objects and sky b_ckground radiation and radiation signatures of various objects in space and on the ground. Observations will include exhaust pltm_esof rocket vehicles launched fro_ the _astarn or Western 'resti_nges, rocket sled exhausts at Hollor,,an Air Force Base, volcanoes and forest fires as well rs contrasting background areas such as deserts and warm ocean currents. 9.

_imple Navigation (4) The cap_.bilityof man to navigate in space and to provide a

reliable navigation system independent of ground support will be tested in this experiment.

_o

special instruments have been developed

for use on Gemini spacecraft to allow detailed menu_l-vlsu_.lexamination of the space phenomena thought to be best for space navigation purposes. These are a space stadimeter and a sextant.

This flight w_ll only

carry the space sextant w_th which the astronaut will use to make star-horizon angular measurelr_entsfor orbit_l orient_tlon deter_tlin_tions. The results will be co1_paredwith actual measurements to det(_rmine the accuracy of the procecures. lO.

Synoptic Terrain _'hotogroR_hxh (4 and }) The purpose is to obtain photos of selected parts of earth's

surface for use in research in geology, geophysics, geography, oceFnography.

This experiment has been flown on every flight since MA-8.

Experiment -- 70mm Hasselblad camera with 80mm Zeiss F2.8 lens; two packs of color film with 65 exposures each.

-more

-

Approximately n_nety

pictures

will

the shallow central ll.

be taken over aress

wsters

portion

Synoptic

the _ehsmes,

Weather

Photography

Westher

_bil_ty

to photogrsph detsil

TIROS meteorological

satellite.

purpose

from meteorologicsl knowledge

two magazines line

lines,

frontsl

typical

-- 70_

clouds,

with

wsve

of clouds

substentielly

esch.

jetstresm

cosstsl

Areas

cloudiness, zone,

induced

in the trade

lens;

of Interest

with

cirrus

convergence clouds

to

they provide

Zeiss F2.8

not sssocisted

of fronts, states,

informetion

exist.

ostlers with 80nm

intertropic_l

brosd banking

the current

In many tress

65 exposures

phenomenon,

from

ere contributing

observstions

to mske

selectively--in

Js to sugment

_ctivity

of Gulf

cyclones,

ranges,

systems

systems.

thunderstorm

in subtropicsl

mountain

westher

Hasselblad

stretus

and extratroplcsl

cloud

which

clouds end views

morning

pettern

s_tellites

of color film

_uell

ere

the west

is designed

_hsn cen be obLein_d

where few or no other

_xperiment

experiment

of the experiment

of the earth's

information

the Red See, end

eress

(3,4 end 5)

Photogrsphy

color and in greater

A primary

rr_msry

of _exico.

The Synoptic use of man's

around

of tile world,

squall

clouds, tropic_l cellulsr

by islends winds

--

end

or other

regions. 12.

Visual Acu_t_ Astronaut Visibil_t_ The visusl

nition

ability

of objects

(5) of the _stron_uts

on the earth's

surface

-more-

in the detection will be tested

_nd recog-

in these

experJ-

.-13-

ments.

The spececraft will be equipped with _ visicn tester _nd

photo_,eter. The astronauts will use the vision tester t_ evaluate visual sightings from space relative to e_rthbound b_seline _lues.

I II

I I

I II

I iI

I

I

I

I

I

I

i

L .....

J

L .....

' II ,' ,

I

J

L .....

I II I i

_

I Ii i I

L.___-J

I\EIIl,I ![' I J -II,llJl ,11 1 II'] -mOi_O

-

-i_.

The photo_eter

will _e_sure

light

due ho scsttering.

While

will

of p_nels

view s pattern

their findings. and vision

will be checked

During astronaut attitude verbal

Viewings

passage

the spscecraft

lsid out near Lsredo,

the on-board ity bas_s.

minutes vision

over

Tex_s

the sites,

asSronsut

observes

investigator

in each 2& hour period,

tester

the sstron_uts _nd record

w_th laborstory

for msintsining

com_,ents to the principal

_or five

window

experiments

pre- end post-flight.

of the spacecraft

the second

of the spscecr_f_

is oriented

will be correlated

shall be responsible while

Bttenu_tion

the cox1_1_nd

the proper

spscecraft

the target eree

end m_kes

st the site. esch 8stroneut

to test his own visusl

acuity

will use

on an opportun-

EXPERIMENTS 1.

TO BE FLOWN FOR THE FIRST

Bioassays In this

Bod_ Fluids experiment

the astronauts

flight will be studied and post-flight measured

blood

From analysis

produced 2.

Balance

sodium

of calcium

flight will

calcium

by careful

intake

urine will be

and enzymes

bags. body

which

may be

will

in this experiment

Sweat

of the crew in distilled

Sleep Anal_sis

cleaned

of this experiment levels

to

phosphorous_

calcium Careful

diet record-

fecal and urine

will also be measured

water

following

and the water

are to assess

of consciousness,

-more-

flight.

and total

for analysis.

3.

In addition

on a prescribed

during and after

be similarly

by means

be monitored.

be accomplished

will

during the con-

such as nitrogen

will be maintained

Undergarments

state of alertness_

Pre-flight

hope to measure

change to the body

of interest

be preserved

The objectives

space

in special

and output measurements.

prior to flight,

cleansing

In-Flight

acids

be evaluated

and magnesiumwill

ing of input-output will

stored

experimenters amino

fluids.

In-flight

of this

during

of stress.

The two astronauts

specimens

body

will be taken.

fluids

other electrolytes

for two weeks

to stress

Study

of orbital

chloride

of analysing

proteins_

and amount

of controlled

reaction

and a portion

of these

as a result

The rate

calcium_

samples

electrolytes_

Calcium

ditions

by means

at each voiding

hormones_

TIME

recovery.

analysed.

the astronauts'

and depth

of sleep

during

-16

flight.

An electroencephalograph

daring weightless monitoring sleep.

flight

(EEG) on the astronauts

to establish

tool to help determine

The electrical

activity

Optical

Communication

Laser is an acronym of Radiation° atom. phase

When

of the cerebral

or unison.

in a constant

Thus

doing will

The primary

ment will

be useful

The experiment

of optical

consists

system.

The flight

transmitter

resembles

It is made rechargeable converter,

It weighs

about

nickel-cadmium

in

obtained

and the

radiance

from this

transmitter

experi-

a lO-volt a d.c.

and a ground-

the same size as a home

and is completely

sight and a microphone.

-more-

for communications

are background

and is about

batteries),

In

will be established.

of a flight

lasers,

for

systems.

six pounds

up of four injection

a telescopic

control"

future

transmitter

camera.

the

station.

data will be recorded

data and the experience

equipment

of light

and a ground

data to be obtained

in designing

exciting

a new technique

frequencies

atmospheric

based receiver

movie

quantities

Emission

direction.

spacecraft

as a "pointing

This

by greatly

to demonstrate

an orbiting

atmospheric

by Stimulated

is produced

in one precise

and certain

and attenuation.

recorder.

is "coherent, " that is, it is directed

is an attempt

of an astronaut

of

be monitored

on the biomedical

emit small

the light

this, a demonstration be achieved

value

emission

steady beam

between

cortex will

for Light _Amplification

the atom will

This experiment communication

and recorded

and depth

(Laser)

Stimulated excited

use of the EEG as a

the state of alertness

by two pairs of scalp electrodes 4.

the possible

will be taken

power

(direct

self-contained.

supply current)

(eight to d.c.

-17Four gallium transmitter. wavelength

arsenide

They

injection

deliver

a total

of 9,000 angstroms.

four lines of light arranged pattern

at distances

Injection and efficiency

The ground-based is 30 inches with

one above

in diameter

a photomultiplier

resembles

beam

approximately

0.9 mile

Receiver Ascension radars

systems

is mounted

0.17

compactness,

atop

into light

located

weight

energy. telescope.

It

and focusing

at the focal

the receiver

of three

degree.

light

watts

plane.

barrel.

into a three

At 300 miles

unit

milli-

the beam will

be

in diameter.

have been

Island and Kauai,

and always

form

making a square

a short, blunt

(optical detector)

spread or about

power at a

by the lasers

of a collector

The argon gas laser has an output radian

the other

energy

and consists

An argon gas laser beacon

produced

for their

electric

receiver

of light

of the

feet to infinity.

chosen

in converting

are the heart

of 16 watts

The beams

of several

lasers were

lasers

installed

Hawaii.

point toward the

at White

Sands Missile

The receivers spacecraft

Range_

are slaved to FPS

when

it is within

range

of the radar. In operation orientation through

the command

while the co-pilot

the telescope

beam will be visible When

to the naked

argon

established.

aims the laser

at the ground-based

the spacecraft

the ground-based has been

pilot will maintain

laser

transmitter

argon

laser.

spacecraft by sighting The argon

laser

eye.

beacon

laser viii

proper

is acquired

be flashed

Both beacons

-more-

will

by the ground receiver

to indicate

then be aligned

that

contact

and voice

communications and say,

can begin.

The co-pilot

"i, 2, 3, 4, 5, testing

Voice

communications

During

will

the experiment

protection

against

radiation

which

energy

5.

Contrast

The purpose land-sea

Landmark provide

6.

Chilean telescope

is to measure of terrain Apollo

made

confidence

goggles

by stray shields

for

or reflect-

for stopping

that filter

out

level

the visual

contrast

of

to be used as a service

Guidance

Ik'om outside

_rlll be made

and Navigation

the atmosphere

to effectively

in the development

duplicate

system. will naviga-

sensor

the time

Coast

and equiI_nent used

will be

as the Florida

Coast_

and A_stralian

Coast.

for the Star Occulta-

used.

Navigation and operational of a simple,

capability

The astronauts

of such areas

Coast I African-.Atlantic

experiment

K_e feasibility

measuring

measurements

Occultation

navigational

have

to ground.

by the laser.

experiment

measurements

Navigation Star

safety

be caused

The glasses

spacecraft

for Apollo.

South American

tion

- from

will wear

might

and other types

data of a high

A photometric

laser.

data for the onboard

tion sightings

channel

Measurements

of this

contrast

Landmark

be one way only

the astronauts

emitted

boundaries

of navigation

to the voice

enter the eye from the side and lenses

the infrared Landmark

switch

5, 4, 3, 2, 1."

eye damage which

ed light from the onboard

will

will

will

value

accurate

of star occulting and self-contained

be investigated

determine

the orbit

stars dip behind

-_re

in this

-

orbital

experiment.

of the Gemini

an established

measurements

spacecraft

horizon.

by

-19-

As much be used

of the existing

for the recording

and time.

Nevertheless,

the performance

silvered

certain

sensor

mirror,

pre-amplifier

hand-held

of photometric

equipment

sensor

special

output

equipment

studies.

as is possible signal

will

intensity

will be necessary

Included

for

in the equipment

sensor.

The photoelectric

plle_,

onboard

of the navigational

is a photoelectric

partially

Gemini

consists

iris,

chopper,

and associated

to the astronaut's

of a telescope, optical

filters,

electronics.

eye for viewing

eyepiece,

reticle,

photomulti-

The instrument

is

out the spacecraft's

window. Asthe

astronaut

to be occulted. star within diverted

He then points

a reticle

circle.

a calibration automatically°

the star passes The tracking

A portion

simply

The astronaut

in which

of the radiation switch,

the intensity

}_ then tracks

the air glow,

solves the star acquisition

problem

role

ating a two-gimbal

automatic

tracking

be used if he were

not onboard.

the reticle

indicate

to point

as

level and complete

the next

would

switch. First,

he

star to be

the telescope

system which

During

the passage

in the procedure,

Third, he records

-NK)re-

the astronaut

the calibration

by locating

he uses his head

is then

lO0 seconds.

the 50% intensity

plays an essential

the

the edge of the earth.

will manually

depressing

about

of the star is

the star within

and behind

the astronaut

stars

at one and centers

With a hand-held

by momentarily

Second,

for bright

for each star is approximately

period

of the star through occultation

mode

he looks

the telescope

into the atmosphere

period

this tracking

transited.

the horizon,

to a photomultipliero

initiates measured

views

thus elimin-

of necessity

star occultation

times

-20-

manually for comparison with the automatic calibration mode. he notes peculiarities in the data as it is collected.

Finally,

In performing

this latter function_ the man is used to greatest advantage to advance the state of the navigational art as rapidly as possible.

-21-

CAME_

EQUIPMENT FOR G_MINI 7 AND 6 MISSIONS 16_94MAURER MOVIE CAMERA

I.

Camera A.

Equipment i. 2. 3.

B.

Characteristics 1. 2. 3. 4.

II.

two cameras 75mmlens (one camera) 75ram,25ram,18ramlens set (second camera)

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

FiLm Kodak S. O. 217 color film

III.

purpose Weather and Terrain Photography General purpose

-more-

I

-22-

70MM HASSELBLAD CAMERA

I.

Camera A.

Equil_nent 1. Camera 2. 80mm lens 3 • 250nmmlens 4. Photo event indicator 5. Ring Sight 6. UV filter 7. Film backs

B.

Characteristics 1. 2. 3. 4. 5.

II.

80_n 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 Kodak S. O. 217, MS, Ektachrome ASA-64 color emulsion on 2.5 railEstar Polyester base

III.

Purpose Weather and Terrain General Purpose

-more-

-23-

G_IINI 7 FOURTEEN DAY P_NU CYCLE

MENU I - DAYS i. 5. 9 & 13 MEAL A (R) (B) (a) (R) (R)

Days 5, 9, 13 only

CALORIES

Grapefruit drink Apricot cereal cubes (8) Sausage patties (2) Banana pudding Fruit cocktail

83 114 223 282 87

Al_ricot cereal cubes (day 13 only_ °9_ MEAL B (R_ (_) (B) (B) (R)

Beef and vegetables Potato salad Cheese sandwiches (6) Strawberry cubes (6) Grange drink

_NU

ii - DAYS 2,6, i0 & 14

MEAL A (R) (R) (B) (R) (B)

CALORIES

Grapefruit drink Chicken end gravy Beef sandwiches (6) Applesauce Peanut cubes (6)

83 9_ 268 165 297 905

M_AL B

98 1Z_3 324 283 83 931

(_) (R) (B) (2)

Orange-grapefruit Beef pot roast Bacon & egg bites (6) Chocolate pudding

_AL

C

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

Potato soup Shrimp cocktail Date fruitcake (4) Orange drink

83 119 206 307 715

MEAL C (R) (R) (R) (B)

Orange-grapefruit drink Tuna salad Apricot pudding Date fruitcake (4)

Total Calories Food 0nlyWeight

83 214 150 262 709

2,429 521.12 gm

Days 2, 6, iO only

Total Calories Food 0nly Weight

2,304 518.62 gm

(B) = Bite-sized food not requiring rehydration prior to ingestion. Usual serving consists of six bite-sizepieces. (R) = Rehydratable food, i.e., food which must be reconstituted prior to ingestion. -more-

220 119 262 8) 684

MENU III-

Day 3, 7, ll

M_AL A (R) (R) (B) (B) (_{)

MENU IV - Day 4, 8, 12

CALORZES

_AL

A

_a]_lon_alad Green peas Toasted bread cubes (8) Gingerbread (6) Cocos

2A6 81 1O7 183 190

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

Strawberry cereal cubes (8)-day 8 only Bacon squares (4) Ham and applessuce Chocolate pudding

Toasted bread cubes - day 3 only _AL B

807

(R)

Orange drink

CALORIES

ll4 135 127 307 82 766

MEAL B (R) (B) (_) (B) (B)

Grapefruit drink Bacon squares (4) Chicken & vegetables Apricot cubes (6) Pineapple fruitcake (6)

83 90 75 284 _79 911

M_AL C

(B) (g) (R)

Cheese sandwich (6) Butterscotch pudding Orange drink

Total Calories Food Only Weight

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

Beef and gravy Corn chowder Brownies (6) Peaches

16C 252 2A1 __ 751

I_AL C 70 324 234 8_ 711 2,&29 515.06 gm

-monte -

(B) (B) (S) (S) (_)

Coconut cubes (6) Cinnamon to_st (6) Chicken salad Applesauce Grepefrut drink

Total Calories Food Only Weight

310 99 237 165 83 894 2,All 509.58 gm

-25G_INI

6 LAUNCH PREPARATIONS

The launching of Gemini 7 and the rapid turn-around for the Gemini 6 mission will be one of the most complex operations ever conducted by launch operations crews.

A work schedule has been established for

flight testing, checkout and launching of Gemini 6 nine days after Gemini 7. The Gemini 6 spacecraft and launch vehicle were checked out thoroughly and counted down to some 42 minutes before liftoff on October 25.

Since that time both the spacecraft end launch vehicle

were placed in "bonded" storage under guard to insure that their mechanical and electrical integrity remains intact. The Gemini 6 checkout will be the same as if a problem had occurred several days before the originally planned Gemini 6 flight and the spacecraft had to be de-mated from the launch vehicle.

With

the problem solved, the spacecraft would again be _mted and a "compressed" checkout would take place in the days leading up to a launch, as most of the previous testing was still valid. Once Gemini 7 has been launched_ crews will be ready to erect the 6 launch vehicle and mate the spacecraft as soon as possible. schedule

The

calls for this to be completed some 24 hours after Gemini 7

liftoff. Certain testa conducted during a normal mission will not have to be repeated for Gemini 6 because they will still remain valid (their validity will be checked, however).

These include various

calibrations of launch vehicle, spacecraft and blockhouse automatic

•,-mo_e -

-26-

ground support equipment; weight and balancing of the erector, certain spacecraft pre-mate and extensive spacecraft launch vehicle combined systems tests.

Another departure from regular checkout

procedure is that the Gemini 6 spacecraft will be fueled and the water supply and batteries will be installed before it gets to the launch pad. The spacecraft and launch vehicle crews (McDonnell Aircraft is prime contractor for the spacecraft and Martin Company for the launch vehicle) will work on a three-s_ft,

24_hour schedule during

the period between the launches. The following is a general outline of the comprehensive work schedule: The Gemini 7 is scheduled for launch at 2:30 p.m. EST. As soon as possible an assessment of pad damage will be made. The blast d_ge meritpri_rily

has been very minimal in the past, requiring replaceof some expendable wiring at the base of the pad.

Various umbilical cables etc. will be checked to insure that they are operating.

This work can be accomplished at the same time as

the two launch vehicle stages are being erected end as the spacecraft is mated. During launch days plus one and two_ preparations will be made for final spacecraft systems tests.

The validity of the electrical

interface between the spacecraft and launch vehicle _ill be verified on the third day as individual tests of the two continue.

-more-

-27-

The final spacecraft systems tests are to be conducted on days three and four.

During this time the previous verification of

guidance betwe_

the spacecraft and launch vehicle is checked.

Liquid oxygen for the spacecraft environmental control system will be loaded aboard during this time as preparations are made for the simulated flight, scheduled for launch day plus five.

From this

point, to Gemini 6 liftoff, the checkout will be generally the saae as of any other Gemini flight. The simulated flight, which lasts some i0 to 12 hours, consists of three simulated launches -- A mode II abort run (an abort occurs some 1:38 after liftoff), a switchover to secondary guidance during powered flight, and finally, a normal flight and insertion into orbit, during which various orbital exercises, reentry and recovery tests are run.

The prime pilots and their backups participate in

these tests aboard the spacecraft at Launch Complex 19. Another "time saver" comes after the simulated flight when the various pyrotechnics aboard the spacecraft ere thoroughly checked and connected.

Since the pyrotechnics system was varified previously

and left in a flight mode configuration, only a short test for verification will

be required.

The Gemini

6 pre-_ount

(lasting

some four

hours

on the

third

day before

launch) and the mid-count (lasting some four hours on the second day before launch) will be very s_m_lar to regular Gemini procedures.

During the pre-

count significant portions of each spacecraft system ere again checked.

-__0 i_e -

-28-

Final interface tests between the spacecraft and launch vehicle (guidance, abort procedures etc.) are conducted during the mid-count. The Gemini 7 and 6 final countdowns will be about the same-the spacecraft starting at about T-6 hours end the launch vehicle at T-4 hours.

However, on Gemini 6, s hold will be declared st T-3

minute mark in the count to adjust the launch time to the planned rendezvous with Gemini 7.

This hold will last 25 minutes.

Gemini 6 launch time is scheduled for 9:35 a.m. EST.

-more.-

The

-_{9LAUNCH Gemini

VEHICLE

COUI_£DOWN

6

F-3 days

Start pre-count

F-1 day

Start mid-count

T-12 hours

GLVpropellant

T-390 minutes

Complete

T-3OOminutes

Begin terminal

T-120 minutes

K[ight

T-9O minutes

Crew enters

T-75 minutes

Close

spacecraft

T-50 minutes

White

Room evacuation

T-35 minutes

Begin

erector

T-15 minutes

Spacecraft

T-3 minutes

25-minute

T-04

GLVignition

seconds

T-O seconds T+2 minutes_

loading

propellant

loading

countdown

Crew to Complex

19

spacecraft hatches

lowering

OAMS

static firing

hold

Liftoff 36 seconds

Booster

engine

cutoff

T+5:41

Second

T+6:II

Spacecraft-launch

-mo re-

stage engine

(BECO)

cutoff

vehicle

(SECO) separation

-30NOMINAL Gemini

MISSION

PLAN

6

Gemini

6 is scheduled

from Launch

Complex

to be launched

19 at Cape Kennedy,

an elliptical

orbit of 168 miles

stage booster

yaw steering

same orbital inclination

will

plane as Gemini increment

7.

apogee

December Fla.

13 at shout

It will

be launched

and lO0 miles

be used to place Yaw steering

change if needed.

9:34am EST

perigee.

the spacecraft

provides

into

Second into the

up to 0.55 degree

The spacecraft

will

trail

Gemini

by 1208 miles at insertion.

Launch Windows Nominal

(EST)

Day

9:34am

to lO:21am

N

+

1

9:38am

to lO:25am

N

+

2

8:07s_

to 8:54am

N

+

3

8:llam

to 8:51_m

N

+

4

6:59am

to 7:25am

Rendezvous is on time.

During

lO0 seconds If liftoff attempted coverage

is planned

the first 35 minutes

delay in liftoff time occurs

beyond

until the beginning

9:42am to lO:14am

8:14am

orbit

of Gemini

of each launch

delays rendezvous 300 seconds,

to ll:24am

to 9:01am

6, if liftoff opportunity

by one spacecraft

rendezvous

will

of the seeonc_ day when better

each

orbit.

not be tracking

is available.

Sho_h]. l[ftoff 47 minute

for the fourth

ll:O_am

occur clurin_ the last

win_Jow, a different

be initiated

to narrow

intermediate

the catch-up -more-

12 _minutes oI.'the r_×imum sequence

distance

between

of maneuvers

will

the spacecraft.

7

-31-

In this case, engine cutoff occurs earlier to reduce velocity by 50 feet per second.

This causes the spacecraft to be inserted into

a lower orbit than planned, with a perigee of about i00 miles and apogee of 138 miles.

In this orbit the Gemini 6 catchup rate will

be increased due to the greater difference in altitude between the two spacecraft. Varying insertion velocity as described above has the effect of widening the launch window. Following a successful, on-tlme liftoff and insertion the uncertainties of the effect of drag on the spacecraft during its initial orbit may require a one foot per second posigrade burn at first perigee to raise apogee.

In the event of small insertion

dispersions, the magnitude of this maneuver may vary but the resulting apogee will be 168 miles. Near the second apogee a posigrade burn will add 53 feet per second to raise perigee to about 134 miles.

This reduces the catchup

rate from 6.7 degrees to 4.5 degrees per orbit and will provide the proper phase relationship between the two spacecraft for circularization at third apogee. Should the two spacecraft be in different planes, s plane adjustment will be made by Gem/ni 6 at the common node (where the two spacecraft orbits intersect) following the second apogee posigrade burn. At the third Gemini 6 spacecraft apogee, a posigrade burn of 53 feet per second will be made to circularise the orbit at 146 miles.

-more-

_3L)_

-33-

Gemini 6 will then be trailing Gemini 7 by about 184 miles. This is within range of the onboard radar and lock-on should have occurred.

A 32 feet per second posigrade burn will be made at terminal phase initiation along the line of sight to Gemini 7.

This will be

at a ground elapsed time of about 5 hours, 15 minutes - about one minute after entering darkness.

The range between the spacecraft

at this time is expected to be about 39 miles. Approximately 33 minutes following terra,el phase initiation a posigrade velocity of 43 feet per second will be applied to Gemini 6.

This places the two spacecraft into the same orbit and

rendezvous will have been accomplished. Should there be ccuputer, platform or radar failure, the mission can still proceed using ground data and radar-optical or optical rendezvous modes. Retrofire will occur at a ground elapsed t_m_ of 46 hours and I0 minutes, during the 29th revolution. West Atlantic recovery area.

-more-

Landing will be in the

-35-

G_NI

Three

experin_nts

Synoptic

Weather

Photography

2.

Synoptic

Terrain

Photography

3.

_adiation

all previous the Gemini

Gemini

levels located

experiments flights.

the amount

The shield w_ll

closest

is designed

inside

of those of these

6 mission:

flown

on

eppears

to n_asure

the spacecraft.

in

the crew members be removed

to the earth's

surface.

was _iso flown

where

sensors

beneath

p2sses

the radiation

on Gemini

4.

are

to simulate

8re receiving

as the spececraft

the area

r_di_tion

3even

One is shielded

anomaly,

This experiment

the Gemini

section.

the spacecraft.

of radiation

the South Atlantic

are repe_ts

A description

experiment

and distribution throughout

during

in sImcecraft

7 experiments

The radiation

dips

will be performed

i.

The photogrsphy

skin.

6 EXPEi_NTS

their

through

belt

-36-

DAy #I

MEAL

"A"

CALORIES

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

90 252 183 297 83 TOTAL

MEAL

"B"

Chicken and Gravy (Rehydratable) Cheese Sandwiches Strawberry Cereal Cubes Pineapple Fruitcake 0range-Grapefruit Drink (Rehydratab2e) TOTAL

MEAL

CALORIES

92 324 171 253 83 CALORIES

"C"

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

FIRST

-more-

CALORIES

21_6 99 ii? 241 83 -_

DAY

2,611_

- TOTAL

-37-

DAY

#2

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

MEAL

"A"

CALORIES

(Rehydratable)

Drink

(Rehydratable) TOTAL CALORIES

MEAL

196 i19 262 310 83 --97-0---

"B"

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

214 171 283 98 83 TOTAL, CALORIES

MEAL

"C"

Bacon and Egg Bites Meat & Spaghetti (Rehydratable) Toasted Bread Cubes Chocolate Pudding (Rehydratable) Grapefruit Drink (Rehydratable)

178 70 161 307 83 TOTAL

SECOND

-more

-

CALORIES

DAY TOTAL

2,618

-38-

MANNED SPACE FLIGIIT NEw'WORK G_41NI 7AND 6 MISSIONS

The Manned Defense

Space Flight

Network

consists

of NASA and Delm_rtment of

facilities.

1_e Mission the entire Real-Time

Control

Gemini

(i)

Complex

computing

For Gemini

(2)

control mation

(MCC-H) will

control

(a key element

of the MCC-H) will

serve

center. will

provide:

data during launch

7 and the Gemini

6 spacecraft

and orbital for position

phases determination

operation.

Capability

to either

(RTCC)

and telemetry

from both the Gemini

Texas

As on Gemini _missions 4 and 5, Houston's

7-6 the network

Tracking

and systems

in Houston,

7-6 mission.

Computer

as the mission

Center

or both

for transmission spacecraft.

center s update

and verification

These

commands s generated

the spacecraft

for time-of-retrofire

of ground

computer

determination

at the mission

to provide

and reentry

commands

ctu_rent infor-

calculations

and

di splays. Prime

Computin_

Immediate

Su_ort

computing

impact by the RTCC and insertion Bermuda

support

at the Manned

and MISTRAM

Computer

NASA's for Gemini

GLDS

receive

(Missile

data from the Air Force Eastern

Other

Spacecraft

phase s the RTCC will

and radar

Kennedy-Houston

will be provided

(Gemini Launch

Center. high-speed

Tracking

Test Range

from launch through During radar

the launch data from

and Measurement

(AFETR) radars

System)

via the Cape

Data System).

Support

Goddard

Space Flight

7-6 includes

Center

(GSFC) real-time

computing

the processing

of skin tracking

information

-more-

support

-39-

obtained

from the second

computation

of their

GSFC RTCC will position

beacon

predicted

generate

predictions

Department

stages of both

skin track

of Defense

for their

at the GSFC will

to support

CMD_ RDR_

station-by-station_

CADFISS

Checkout

Gemini

Flight

use in the event

post-launch

the

space

Network

and the

of spacecraft

also _ll

when

checkout

until

TLM, method

Subsystem

be performed

the spacecraft

and continue

network's

a system-by-system

and Data Flow Integrated

stations

acquisition

the worldwide

computer-progrsmmed

facilities periods

by some

certify

7-6 through

(Computation

of network

"visible" within

Additionally_

flight.

readiness

_ring

Space

and the

Readiness

Computers

called

points.

(radar echo bounce)

for the Manned

loss or powered-down

Network

impact

launch vehicles

Tests).

by the GSFC

are not electronically the vehicles

are again

range.

Data Flow Tests

(DFT's) from the worldwide

Spacecraft

Center's

Real-Time

the Manned

Spacecraft

Center

Computing

network

Complex

under the direction

to the Manned

will be conducted of the CADFISS

from

Test

Director. TRACKING For Gemini data acquisition station

7-6,

TWO MANNED

various

assignments

SPACECRAFT

combinations

of spacecraft

will be accomplished

capability.

-more-

trackln_

according

and

to individual

-40-

Both Gemini spacecraft are equipped with C-Band beacon systems that aid station radars of the Manned Space Flight Network in pinpointing precise space position of each vehicle.

In order that these

radiated signals be readily distinguishable by the ground systems, their identifying codes have been altered slightly for precise recognition. Through the detection of the spacecraft beacon, ground trackers pinpoint each spacecraft with an accuracy equivalent to a 22 bullet hitting a twenty-five cent piece at a distance of one mile.

Electroni-

cally coordinated (slaved) telemetry receiving and radio command antenna systems acquire data from and send instructions to each spacecraft based in part on the space position information provided by the beacon tracking radars. After Gemini 6 spacecraft insertion into orbit, stations in the Manned Space Flight Network will, for the first time, simultaneously track and acquire information from two orbiting manned spacecraft. While both spacecraft are in orbital flight the on-slte flight data summary computer: (UNIVAC 1218) called TOMCAT (Telemetry 0n-Line Monitoring_ Compression and Transmission) processes Gemini 6 or 7 (whichever spacecraft has been designated "prime") spacecraft data. Upon termination of the Gemini 6 mission, all network station systems will revert to previous Gemini 7 operating modes for the remainder of the mission.

-more-

-41ORBIT3 - _OLU'i'lON_ The sp_cecrsft's earth.

A revolution

over 80 degrees every

course

is messured

is completed

west longitude,

esch

in revolutions

eround

time the sp_cecrsft

or at Gemini

sltitudes

the

pssses

sbout

once

96 _inutes. Orbits

are spsce referenced

and in Gemini

-moPe-

tske _bcut 90 minutes.

-21.2-

CREW TRAINING

In addition flight plished 1. Dynamic 2.

to the extensive

assignment

3. Chapel 4.

general

training

preparations

have

received

prior to

or will be accom-

prior to launch: Launch

abort training

Crew Procedures Egress

training

recovery usin_

Celestial

in the Gemini

Mission

Simulator

and the

Simulator.

and recovery

model and actual egress

the following

BACKGROUND

activities

equipment

elevator

pattern

using

a spacecraft

and personnel,

boilerplate

pad emergency

and slide _rlre.

recognition

in the Moorehead

Planetarium,

Hill, North Carolina. Parachute

descent

training

over _ater

using

a towed

parachute

technique. 5.

Zero gravity

6.

Suit_

7.

Training

member 9.

sessions

on the Gemini Detailed

aircraft.

fittings.

for each

translation

systems

crew.

and docking

briefing;

detailed

simulator. experiment

briefings;

flight

rules reviews.

Participation

and spacecraft

in KC-135

seat and harness

plans and mission IO.

training

in mockup

acceptance

reviewsj

review.

-more-

systems

revie_

subsystem

tests

-43-

During final preparation for flight, the crew participates in network launch abort simulations, Joint combined systems test and the final simulated flight tests.

At T-two days, the major flight

crew medical examinations will be administered to confirm readiness for flight and obtain data for comparison with post-flight medical examination results.

-more-

-44IMMEDIATE PEE-FLIGHT CREW ACTIVITIES

T-7 hours

Back-up flight crew reports tc the 100-foot level of the White Room to participate in final flight preparations.

T-5 hours

Pilots' ready room, lO0-foot level of White Room and crew quarters manned and made ready for prime crew.

T-% hours, 30 minutes

Primery crew awekened

T-4 hours

Medical examination

T-_ hours, &O _dnutes

Breakfast

T-3 hours, 15 minutes

Crew leaves euarters

T-3 hours, 5 minutes

Crew arrives st ready room on Pad 16

During the next hour, the biomedical sensors are placed, underwear end signal conditioners are donned, flight suits minus helmets and gloves are put on end blood pressure is checked.

The helmets

and gloves are then etteched and con_unications end oral temperatures systems are checked. T-2 hours, 15 minutes

Purging of suit begins

T-2 hours, 4 minutes

Crew leaves reedy room

T-2 hours

Crew arrives _t lO0-foot level

T-I hour, 30 minutes

Crew enters spacecraft

From entry until ignition, the crew participetes in or monitors systems checks and preparations.

-more-

-_5-

_t

Activities

At ignition assessing seconds

system after

the crew begins status

_Co,

contend

attitude

corrections

control.

After

check llst,

abort

pilot

spacecraft

are received

or aft thrusting. insertion

end detecting

the co_snd

and the pilot actuates

the primary

Ground

the detailed

phase

sittmtions.

initietes

separetion

forwerd

end selects

task of Thirty

thrusting rate

ccmput_,tions of insertion

end velocity successful

leunch

adjustments

insertion flight

velccity

ere m_de by forwerd

and completion

plan is begun.

of the

-46-

CREW

Every

Gemini

(Back-up)

feature.

the

launch

the

crew

for

escape.

are

MODE

I

MODE

II

MODE

III

Vehicle,

with

crew

Malfunction

monitors

three

Deteetion

subsystem

of

has

a reduadant

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 of powered flight, or during deseent after reentry. (Delayed)

Retrorockets used between 50 and i00 seconds, allowing crew to salvo fire all four solid retrorockets five seconds after engine shutdown is cow,handed. Normal separation from launch vehicle, using OAMS thrusters, then making normal reentry, using computer.

for

turns

Survival

Mode

I,

blunt-end

crew

spacecraft

separates

forward,

then

from

completes

Gemini reentry

Launch and

aboard.

package

Survival the

affecting

of a potentially

Except

to

The

vehicle

There

landing

system

SAFETY

gear,

astronaut's

mounted

on

parachute

each

ejection

harnesses

23 pounds.

- more

-

seat

by nylon

and

llne,

attached weighs

-47Each 3.5

astronaut pounds

has:

of

drinking

water

Machete 0ne-man flation,

sea

life

anchor,

Survival sewing

striker,

halazone

5½ by

dye

light

compass,

Survival

raft,

14

feet

tablets,

radio,

feet,

markers,

(strobe),

kit,

3

with

nylon

with

CO 2 bottle

sun

a whistle,

line, and

beacon

signal

cotton

in-

mirror,

balls

batteries

and

for

bonnet.

flashlight,

of nylon

homing

with

and

voice

for power. reception.

Sunglasses. Desalter of

with

brickettes

enough

to desalt

eight

pints

seawater. Medical

and

kit,

kit,

antibiotic

motion

containing

tablets

and

stimulant, aspirin,

sickness.

-more-

plus

pain,

motion

injectors

sickness for

pain

and

- 8-

G_MINI 6 SUIT

The pressure suit worn by the crew of Gemini 6 is identical to that worn by the Gemini 5 crew.

It is not suitable for extra-

vehicular activity. It has five layers: 1. White cotton constant wear undergarment with pockets to hold biomedical instrumentation equipment. 2.

Blue nylon comfort layer.

3.

Black neoprene-coated nylon pressure garment.

4. Restraint layer of dacron and teflon link net to restrain pressure garment and maintain its shape. 5. White HT-lnylon outer layer to protect against wear and solar reflectance. The suit is a f,ll pressure garment, including a helmet_rlth mechanically sealed visor. control system.

Oxygen is furnished by the environmental

Gaseous oxygen is provided to the suit through a

"suit loop" to cool the astronaut and provide him_rith a breathable atmosphere of i00 percent oxygen. pounds per square inch

Oxygen in the cabin maintains 5.1

(psi) pressure.

is pressurized to 3.5 psi (+.4,-0).

-more -

The suit_ if cabin pressure fails,

-49G_L_[INI7 SUIT

A new lightweight space flights. crew.

suit has been developed

for long duration

be worn for the first

time by the Gemini

It will

it is en intravehicular

_Jbility

suit desigmed

7

to give maxim_un

when depressurized.

It has two layers: i.

The inner layer coated

2.

nylon

Th_ outer

is the pressure

neoprene-

bladder.

layer is six ounce

it is a full pressure an aviator's

retaining

suit and weighs 16 pounds,

crash he]]net which

is worn under

The suit can be completely

taken

in a partially

doffed

in which

and the helmet

is unzipped

mode

HT-I nylon

off during

the soft helmet.

flight

or c_n be worn

gloves and boots

at the neck

including

and rolled

are removed

back

t(Jform a

headrest. .Exael'gencyti,,_eto donn is about _) seconds. five

to ten minutes

When

the suit from a p_rtielly the suit is totally

to donn it.

doffed

doffed

mode

it takes from

-50MEDICALCHECKS At least member. consist

one medical

Performed of:

and water

Oral

intake

check a day will

over a convenient temperature#

systems

bag with

to the body

a germicide

following

back

pump

opening.

device which

secure

of feces.

of bacteria

and a wet towel_

attach-

It contains

and gas.

are placed

lip is then

and stowed

of body wastes.

lip to provide

formation

Soiled

in the bag

used to form a liquid

in the empty

into a horn-shaped

The receptacle either

or dumps it overboard. in military

food

food container

seal

spaces

to earth for analysis.

Urine is collected adjusting

measurement_

for collection

for the collection

The adhesive

and the bag is rolled and brought

are used

prevents

tissues

use.

pressure

a check will

DISPOSAL

an adhesive

is used

which

itemsj toilet

station,

evaluation.

Two separate

ment

ground

blood

BODY WASTE

A plastic

be made by each crew

fighter

receptacle

is connected

transfers

the liquid

The system

is much

with

a self

by a hose to a

to the evaporator

like the relief

tube

used

planes.

FOOD Number Type

of Meals

-- Three

-- Bite-sized

rehydratables

with

per day per astronaut°

and rehydratable.

special

gun.

Water

Bite-sized

-more-.

is placed

items

in

need no rehydration.

-51Storage-polyethelene_ compartment

Meals

individually

polyamide beside

wrapped

laminate.

knees

First

in aluminum day meals

of each crewman.

foil and

stored in

Succeeding

days meals

in right aft food compartment. The water A mechanical gun.

intake measuri_

It consists

cylinder

mounted

ounce of water. pushes side

water

will

beginning

system

at base When

bellows

of gun.

plunger

out of bellows number

record how much

will be carefully

is an integral

of a neoprene

of gun registers

crewman

of each astronaut

part of the water

housed

The bellows

in a small metal holds

of gun is depressed_

and through of times

gun.

bellows

-more-

one-half a spring

A counter

in right

is activated.

he drinks by noting

and end of use of gun_

measured.

numbers

at

Each

-52-

The following

are

guidelines

only,

Conditions

along

the

grotmd

track will be evaluated prier to and during the mission. Launch Area Surface Winds -- 18 knots with gusts to 25 knots Ceiling -- 5,000 feet cloud base Visibility -- Six miles Wave Height -- Five feet maximum Planned I_udin_

Ar_

Surface Winds ~- 30 knots maximum Ceiling -- 1,500 feet cloud base Visibility -- Six miles Wave Height _

Eight feet maximum

Contineenc_ Landin_ Areas Fllght director will make decision based upon conditions at the time. Parare_cue_ Surface Winds -- 25 knots

maximum

Ceiling -- ipO00 feet cloud base Visibility -- Target visible Waves -- Five feet maximum; swells I0 or ii feet maximum

-illo32e -

-53PLANNF_ AND CONTINGENCY LAN_ING AREAS

There are two types of landing areas for Gemini spacecraft, planned and contingency.

Planned areas are those where recovery

forces are pre-positioned to recover spacecraft and crew within a short time.

All other areas under the orbital track are contingency

areas, requiring special search and rescue techniques and a longer recovery period. P_a_ne_ Lan_ing Area_ PRIMARY

Landing in the West Atlantic where the primary recovery vessel, an aircraft carrier, is pre-positioned.

S_CON_ARY

Landing in East Atlantic, West Pacific and Mid-Pacific areas where ships are deployed.

LAUNCH SITE

Landing in the event of off-the-pad abort for 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 flight, extending from 41 miles at sea from Cape Kennedy to west coast of Africa.

Contingency Landin_ Areas All the area beneath the spacecraft's ground track except those designated Planned Landing Areas are Contingency Landing Areas, roquiring aircraft and pararescue support for recovery within a period of 18 hours from splashdown. Recovery forces will be provided by the military services, and during mission time will be under the operational control of the Department of Defense Manager for Manned Space Flight Support Operations. -more-

OEMINI The Gemini in diameter two major _eentry

spacecraft

(k)

sections

are the reentry

module

reentry

spacecraft,

control

in dia_.eter at

module

and recovery

control

and oxidizer

control

Cabin section side-by-side,

is a hatch.

long,

the top.

and the adapter

lO feet lts

section.

pilot

valves,

between

rendezvous

,t its

and recovery

is the forward

_&_ and cabin

tubing

(_R),

parachute

and radar.

reentry.

contains

of eight _ttJtude

A parachute

ad_pter

attachment.

RCS and adapter

section,

houses

and controls.

is a pressurized

environment

end of the

sections

and two rings

during

their instruments

(small)

and main p_rachutes

is corrugated

and heat protection.

Dish-shaped

hull.

between

shield

Equipment

pressure

and shingled heat

the crew

Above each se_t

titanium

is located

shell which

end of cabin

in diameter

cabin.

between

for main

pressurized

and outer beryllium aerodynamic

section

Crew compartment

not requiring

(3)

each for control

is included

(I)

section

drogue,

tanks,

thrusters

assembly

sections:

(_iCS), and

containing

_eentry

large

5 inches

is ii feet high and 7_ feet

It has three main

seated

18 feet,

_odule

_ndezvous

fuel

is conical,

at its base and 39 inches

The reentry base.

SPACgCRAF I'

hull

to provide forms

the

section.

Adapte.r _e ction The adapter base, containing

section

is 7_ feet high and i_ feet

retrograde

and equipment

-i_ore -

sectJ ons.

Jn diameter

at J ts

-561.1.1

:D

I-I-!

O

O _

>-

OD c,D I--I.U

zO O_ _Z

,,,O I--


U

0

-r U a.

-57-

t_

0 Z m

C_ I,LI

.....

,,

,, ,,,,,,

•

-£;8-

".

/

-59-

.Retrograde section part

of the radiator

contains

for the cooling

E qu_pmentse_c_io_nn contains for

the orbit attitude

the envlron_entsl for

the cooling NOTE:

four

system,

system

retrorockets

are fired

after retros

are fired.

power

system

(ECS).

also contained

The equipzJ_nt section

retrograde

source

and

systems, fuel

(OA_S), primary

It also

oxygen for

serves as a radiator

in the equipment

is jettisoned

for reentry.

rockets

system.

electrics1

and _mnuever

control

solid

section.

immediately

The retrograde

section

before is jettisoned

P_OPELLANT Gemini-?

-- &23 pounds

Gemlni-6

-- 669 pounds GEMINI

The following craft

to support 1.

2.

modifications

Gemini-6

A transponder

rendezvous

radar system

Two acqusition

180 degrees

aport.

target vehicle. for approximately

-7 SPACEC_A_!MODIFICATIONS have been made

rendezvous

to receive has been lights

sp_ce-

mission:

end transmit installed

signals

in the nose

have been placed

These are the same lights

They flash about 80

to the Gemini-?

from

the Gemini-6

of the spacecraft.

on the adapter

designed

times per minute

section

for the Agena and can be seen

23 _iles. P_NDEZVOUS

RADA_

Gemini-6 Purpose

-- _ables

angle to Ge_inl-7.

crew to measure

Supplies

data

range,

to Inertial

-_ore-

range

Guidance

rate, and bearing System computer

-60-

so crew can determine maneuvers necessary for rendezvous. Operation -- Transponder on Gemini 7 receives radar impulses and returns them to Gemini

6

at a specific frequency and pulse width.

Radar accepts only signals processed by transponder. Location -- small end of spacecraft on forward face of rendezvous and recovery section. Size -- less than two cubic feet. Weight -- less than 50 pounds. Power Requirement -- less than 80 watts. _L_CTRICAL POWER SYSTemS Gemini-7 The fuel cell power subsystem includes two 68-pound pressurized fuel cell sections, each containing three fuel cell stacks of 32 seriesconnected cells.

Operating together, these sections produce up to two

kilowatts of DC power at peak load. Four conventional silver zinc batteries provide bBckuppower the fuel cells during launch and are l_ri_ and post-landing.

to

power for reentry, landing

Three additional batteries are isoleted electricelly

to activate pyrotechnicsaboard the spacecraft.

(The four m_in batteries

can also be brought on line for this purpose if necessary.) Besides its two cylindrical sections, the fuel cell battery subsystem includes a reactant supply of hydrogen and oxygen, stored ,t supercritlc_] pressures and cryogenic temperatures.

-61-

'_rlergyis produced the stacks poly_er

whore

plastic

ions combine chemic_l oxid8nt

end s catalyst

with oxygen will

are supplied.

by the spacecraft

drinking

of platin_,

theoretically Electrici_y system,

supply

end w8ter

_anks where

by a bledder

heaC end w_ter. ss long es fuel

for power,

end used as pressursnt

end This

end

heat is rejected

is diverted

it is sepereted

into

of

i_su]t_",t electrons

continue is used

the reactants

by en electrolyte

to form electricity,

coolant

drinking

supply

ce]l by forc_g

they ere chez,icslly changed

reaction

spacecraft

in the fuel

into the front the crew's

to supply

drinking

water. _emini-6 Gen_ni-6

Adepter

_ain

spacecraft

Batteries

Batteries

_quib Batteries

carries

lO batteries.

Included

in these

are:

three /_uO-emp/hour units, housed in the adapter section. Primery power source. four LS-amp/hour units in the reentry section for power prior to end during reentry. three 15-sJJlp/hour units in the r_entry section, used to trigger e_plos]ve squibs.

--mC r_]-

8

-64-

GI_LINI LAUNCH

The Gemini

Launch

II intercontinental GLV dimensions

Vehicle

ballistic

VEHICLE

(GLV) is a modified missile

consisting

U. S. Air Force of two stages.

are:

F_IGHT

First Sta_e 63 feet

Second Sta_e _ feet

DIAMET_q

l0 feet

lO feet

THRUST

430,000 pounds (two engines)

lO0,000 pounds (one engine)

FUEL

50-50 blend of monomethyl hydrazlne unsymmet ri cal-dimethyl hydrazine

OXIDIZER

Nitrogen tetroxide (Fuel is hypergolic, eously upon contact

Overall Combined

height

weight

of launch

vehicle

is about 340,000

Modifications

to Titan

and

ignites spontanwith oxidizer).

and spacecraft

is 109 feet.

pounds.

II for use as the Gemini

Launch

Vehicle

include : i.

Malfunction

detection

booster

performance

information

2. system

Backup

flight

if primary

Titan

control

system

system added

to detect

and transmit

to the crew. system added

to provide

a secondary

fails.

3.

Radio

guidance

substituted

for inertial

4.

Retro

and vernier

5.

New second

stage equipment

6.

New second

stage forward

7.

Trajectory

tracking

8.

Electrical_

rockets

deleted. truss

oxidizer

requirements

hydraulic

guidance.

added. skirt assembly simplified.

and instrument -more-

added°

systems

modified.

-65-

Gemini direction

Launch

Vehicle

program

of the Space Systems

management

Division

CoN_and.

-more-

for NASA

is under the

of the Air Force

Systems

,

J

-66CREW Frank BORN:

Borman,

Gary,

EDUCATION:

MARITAL

Mar.

I0

7 command 14,

pilot

1928

inches

WEIGHT:

163

ibs.

Blonde

hair,

Bachelor of Science degree, United States Military Academy, 1950; Master of Science degree in aeronautical engineering, California Institute of Technology, 1957.

STATUS:

CHILDREN:

Gemini

Ind.,

HEIGHT: 5 feet, blue eyes

BIOGRAPHIES

Married Ariz.

Frederick,

to

Oct.

the

4,

former

1951;

Susan

Edwin,

Bugbee

July

20,

of Tucson,

1953

EXPERIENCE: Upon graduation from West Point, Borman, now an Air Force Major, chose an Air Force career and received his pilot training at Williams Air Force Base, Calif. From 1951 to 1956 he served with fighter United States and in the Philippines and at the Air Force Fighter Weapons School.

squadrons in the was an instructor

From 1957 to 1960 he was an instructor of thermodynamics fluid mechanics at the U.S. Military Academy.

and

_ was graduated from the USAF Aerospace Research Pilots School in 1960 and later served there as an instructor. In this capacity he prepared and delivered academic lectures and simulator briefings, and flight test briefings on the theory and practice of spacecraft testing. Borman has logged more than 4,400 hours more than 3,600 hours in Jet aircraft. CURRENT by NASA Bo_nan

ASSIGNMENT: in September is

the

son

Borman 1962.

of Mr.

was

and

one

Mrs.

-more-

flying

of the

Edwin

nine

Borman,

time,

including

astronauts

Phoenix,

named

Ariz.

j_

-67-

James BORN:

A.

(for

Arthur)

ClevelanJ,

Ohio,

6 feet

WEIGHT:

HEIGHT: EDUCATION:

MARITAL

March

25,

165

Jr.,

Gemini

7 pilot

1928

ibs.

Blond

hair,

blue

eyes

Bachelor of Science degree from the United States Naval Academy, 1952; attended University of Wisconsin 1946-1948.

STATUS:

CHILDREN:

Love11,

Married to Milwaukee

the

former

Marilyn

Barbara Lynn, Oct. 13, 1953; Susan Kay, July 14, 1958

James

Gerlach

A.,

of

Feb.

15,

1955;

EXPERIENCE: Lovell, a Navy Lieutenant Commander, received flight training following his graduation from Annapolis. He served in a number of Naval aviator assignments inclmding a three-year tour as a test pilot at the Naval Air Test Center at Patuxent River, Md. His duties there included service as program manager for the F4H Weapon System Evaluation. Lovell was University

graduated from the Aviation of Southern California.

lie served as flight Squadron i01 at the

instructor Naval Air

Lovell has logged 3,000 hours 2,000 hours in Jet aircraft.

Safety

School

of the

and safety officer with Station at Oceana, Va. flying

time,

including

Fighter

more

than

CURRENT ASSIGNMENT: Lovell was selected as an astronaut by NASA in September 1962. In addition to participating in the overall astronaut training program, he has been assigned special duties monitoring design and development oi" recovery and including crew life support systems and developing techniques for lunar and earth landings and recovery. Lovell is the son of Mr. Edgewater Beach, Fla.

and

Mrs.

-mor©-

James

A.

Lovell,

Sr.,

-68-

Edward H. command pilot BORN:

San

HEIGHT:

Antonio,

6 feet

EDUCATION:

MARITAL

(for

PROFESSIONAL

Tex.,

White

Nov.

WEIGHT:

171

14,

II,

Gemini

7 backup

1930

Ibs.

Brown

hair,

Brown

eyes

Bachelor of Science degree from United States Military Academy, 1952, Master of Science degree in aeronautical engineering, University of Michigan, 1959

STATUS:

CHILDREN:

Higgins)

Married to the of Washington,

Edward,

May

15,

former D.C.

1953;

ORGANIZATIONS:

Patricia

Bonnie

Lynn,

Eileen

Sept.

15,

Finegan

1956

Associate member of Institute of Aero-space Sciences; member of Sigma Delta Psi, athletic honorary; and member of Tau Beta Pi, engineering honorary

EXPERIENCE: White, _ an Air Force Major, received flight training in Florida and Texas, following his graduation from West Point. He spent 3½ years in Germany with a fighter squadron, flying F-86's and F-100's. He attended Force Base,

the Air Calif.,

Force Test in 1959.

Pilot

School

at

Edwards

Air

White was later assigned to Wright-Patterson Air Force Base, Ohio, as an experimental test pilot with the Aeronautical Systems Division. In this assignment he made flight tests for research and weapons systems development, wrote technical engineering reports, and made recommendations for improvement in aircraft design and construction. I_e has logged more than 3,600 hours flying more than 2,200 hours in Jet aircraft.

time,

including

CURRENT ASSIGNMENT: White is a member of the astronaut team selected by NASA in September 1962. He was assigned as the !pilot for the second manned Gemini mission which flew for four days (June 3-7, 1965). White was the first U.S. astronaut to take part in extravehicular activities. He was outside the Gemini _ spacecraft for 22 minutes and was the first human to use a personal propulsion unit for maneuvering in space. White is the son Petersburg, Fla.

of MaJ. •

Gen.

and

-more-

Mrs.

Edward

H. White,

St.

-69-

Michael BORN:

Rome

Collins, Italy,

I_IGHT: 5 feet, brown eyes EDUCATION:

MARITAL

Oct. i0½

Bachelor Military

STATUS:

CHILDREN:

Gemini 31,

inches

7 backup

pilot

1930 WEIGHT:

of Science Academy

163

degree

Married to the former of Boston, Mass.

Kathleen, May 6, 1959; Ann Michael L., Feb. 23, 1963

ibs.

from

Brown

United

States

Patricia

M.

S.,

31,

Oct.

EXPERIENCE: Collins, an Air Force Major, chose career following graduation from West Point.

hair

an

Finnegan

1961;

Air

Force

He served as an experimental flight test officer at the Air Force Flight Test Center, Edwards Air Force Base, California. In that capacity, he tested performance and stability and control characteristics of Air Force aircraft, primarily Jet fighters. He has logged more than 3,000 hours flying time, including more than 2,700 hours in Jet aircraft. He is a member of the Society of Experimental Test Pilots. Collins

was

NASA

October

He is James

in

one

of the

third

group

1963.

of astronauts

selected

by

!

the son of the late MaJ. L. Collins of Washington,

Gen. James D.C.

-more--

L.

Collins

and

Mrs.

-70-

Walter

M.

(for Marty)

Schirra,

Jr.,

Gemini

6 command

pilot BORN:

Hackensack,

HEIGHT: 5 feet, brown eyes EDUCATION:

MARITAL

Mar.

i0 inches

Bachelor Academy,

STATUS:

CHILDREN:

N.J.,

M.

III,

1923

WEIGHT:

of Science 1945

Married Seattle,

Walter

12,

to the Wash. June

ibs.

Brown

degree,

United

States

former

Josephine

23,

170

1950_

hair,

Naval

Fraser

of

Sept.

29,

Suzanne,

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-84E 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 Sidewinder missile at the Naval Ordnance Training Station, China Lake, Calif. Schirra was project pilot for the PTU3 Cutlass and instructor pilot for the Cutlass and the FJ3 _ry. Schirra Fighter

flew F311-2N 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 Rive:r, Md. He was later assigned at Patuxent in suitability development work on the F4H. He has more 2,700 hours

than 3,800 hours in Jet aircraft.

flying

Schirra 1959.

one

Mercury

was

of the

seven

-more-

time,

including

astronauts

more

named

in

than

April

-71-

On Oct. 3, 1962, Schirra flew a six-orbit mission in his "Sigma 7" spacecraft. The flight lasted nine hours and 13 minutes from liftoff through landing and he attained a velocity of 17,557 miles (28,200 kilometers) per hour, a maximum orbital altitude of 175 statute miles (281 kilometers) and a total range of almost 144,000 statute miles (231,700 kilometers). The impact point was in the Pacific Ocean, about 275 miles (443 kilometers) northeast of Midway Island. Me was awarded the NASA Distinguished Service Medal for his flight. He was the backup command pilot for the Gemini 3 mission. Schirra is the son of Mr. and Mrs., Walter M. Schirra, St., San Diego, Calif.

-more-

-72-

Thomas BORN:

P.

(for

Weatherfordj

HEIGHT:

6

EDUCATION:

MARITAL

CHILDREN:

Patten)

feet

Okla., WEIGI_:

Stafford, Sept. 175

17,

Ibs.

Bachelor of Science Naval Academy, 1951

Gemini

6 pilot

1930 Black

hair,

blue

from

United

Married to the Former Weatherford, Okla.

Faye

L.

STATUS:

degree

Dianne,

July

2,

1954;

Karin,

Aug.

eyes

States

Shoemaker

28,

of

1957

EXPERIENCE: Stafford, an Air Force Major, was commissioned in the United States Air Force upon graduation from the U.S. Naval Academy at Annapolis. Following his flight training, he flew fighter interceptor aircraft in the United States and Germany, and later attended the United States Air Force Experimental Flight Test School at Edwards Air Force Base, Calif. He served as Chief of the Performance Branch, USAF Aerospace Research Pilot School at Edwards. In this assignment he was responsible for supervision and administration of the flying curriculum for student test pilots. He established basic text books and participated in and directed the writing of flight test manuals for use by the staff and students. Stafford is co-author of the Pilot's Handbook for Performance Flight Testing and Aerodynamic }landbook for Performance Flight Testing. He has logged more than than 3,600 hours in Jet

LJ,300 hours aircraft.

flying

time,

including

more

Stafford was one of the nine astronauts named by NASA in September 1962. He was the backup pilot for Gemini 3. Stafford is the son of Mrs. Mary E. Stafford and the late Dr. Thomas S. Stafford, Weatherford, Okla.

-more-

-73-

Virgil I. command pilot BORN:

(for

Mitchell,

HEIGHT: 5 feet brown eyes EDUCATION:

MARITAL

Ivan)

Ind.,

"Gus"

April

7 inches

3,

Grissom,

WEIGHT:

CHILDREN:

Married to the Mitchell, Ind.

Scott,

May

16,

1950;

6 backup

1926 150

Bachelor of Science degree from Purdue University

STATUS:

Gemini

former

Mark,

Ibs.

Brown

hair,

in mechanical

Betty

Dec.

engineering

L. Moore

30,

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 1952 and bec_ne a Jet instructor at Bryanj Tex. In August 1955, 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, Calif., 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, including more than 3,000 hours in jet aircraft. He was awarded the Distinguished Flying Cross and the Air Medal with Cluster for service in Korea. Grissom was named in April 1959 as one of the seven Mercury astronauts. He was the pilot of the Mercury-Redstone 4 (Liberty Bell 7) suborbital mission, July 21, 1961 and the command pilot of the Gemini 3 mission, March 23, 1965. He is responsible for the one of three organizational Apollo and Operations).

Gemini group in units in that

the Astronaut office. (The

Grissom Ind.

and

Grissom,

is

the

son

of Mr.

Mrs.

-more-

Dennis

Office, others

Mitche11,

K'

w !"

-74-

John BORN:

San

W.

(for

Francisco,

HEIGHT: 5 feet green eyes EDUCATION:

MARITAL

Young,

Calif.,

9 inches

Gemini Sept.

WEIGHT:

Bachelor of engineering

STATUS:

CHILDREN:

Watts)

Apr.

24, 172

pilot

1930 ibs.

Brown

hair,

Science degree in aeronautical from Georgia Institute of Technology

Married to the Savannah, Ga_

Sandy,

6 backup

30,

former

1957;

John,

Barbara

Jan.

V. White

17,

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 and writing technical reports. He served as maintenance officer for all-weather Fighter Squadron ill3 at the Naval Air Station, Miramar, Calif. In 1962, Young set world time-toclimb 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

more

group of nine astronauts selected by NASA He was the pilot of Gemini 3, March 23, 1965. and

Mrs.

William

-more-

H. Young,

Orlando,

Fla.

-75-

PRE_IOUS

Gemini

i, Apr.

8_

Unmanned to

test

and

1964

flightj

using

launch

vehicle

performance

spacecraft

second

and

days.

No

recovery

attempted.

Gemini

2,

Jan.

1965

heat

launch shut

and

weather, attempt

engines

Spacecraft

Gemini

including

down

23_

as

flight, crew.

53 minutes.

Landed

landing

in Atlantic

expected out

area lift

of plane,

orbital

during after

Mercury

launch

reentry

Dora.

component

times

by

December

detection

reentry

four

three

and

malfunction

Space-

for about

Delayed Cleo

ballistic

of

system

failure.

into

Atlantic

Ocean.

I. Grissom

and

1965

manned

Young

after

ability

spacecraft

systems.

of hydraulic

spacecraft,

environment.

to qualify

after

because

and

orbited

hurricanes

terminated

3_ Mar.

W.

flight

production

launch

vehicle

spacecraft

recovered

First

launch

ballistic

protection

adverse

John

stage

19_

first

to withstand

craft

Unmanned

FLIGHTS

orbital

Gemini

vehicle

GEMINI

with

Astronauts

Orbited

about

earth

50 miles because

reentry. its

own

flight,

is

Virgil

three

(81

orbit. first

-more-

manned Grissom,

man

in

kilometers)

spacecraft First

times

to

fly

did

four

short

not

into

of plamned

provide

spacecraft who

hours,

made

to maneuver sub-

space

twice.

-76-

Gemini

4_

June

Second and

1965

manned

landed

Gemini

in primary

59 minutes command

3-7_

of

21

using

held

completed recovery

Astronaut

Astronaut

accomplished a hand

Atlantic

flight.

pilot.

flight

minutes

of

H.

A.

unit

White

for

after

97

McD1vitt II was

Extravehicular

maneuvering

revolutions

area

James

Edward

62

was pilot,

Activity first

hours,

(_A),

time

in space. [.

Attempt

to

failed

perform

because

Malfunction perform

5, Au$.

Longest Cooper

and

times

Jr.,

22 hours

and

days,

two

orbital

other

heating

power,

flight

(161

day

and

crew

space

required

(_

fuel.

crew

and

in

to

fuel

on

cell

excellant

has

the

time

supply

but

threatened

use

of

management

Spaco_raft

landed

Atlantic

in

Failure

system

careful

is

flight,

astronaut.

permitted

-more-

Cooper

space

personnel,

primary

earth

more

first

operational

ground

L. Gordon

59 minutes.

flights;

of" flight,

from

circled

experienced

._ucce_Jully.

kilometers)

Astronauts

Conrad,

most

system

first

record.

human.

second

by both

complete miles

seven

during

stage

1965

Conrad_

world's

electrical cells

21-29_

any

second

reentry.

(Pete)

than

GLV

of maneuvering

System

Charles

space

mission

Guidance

on

in

oxygen

quantity

flight

to make

of

with

space

first

becomes

insufficient

in Inertial

zero-lift

Gemini

120

of

near-rendezvous

crew about

recovery

of' fuel to ]OO vessel

-77because

of

onboard

computer,

planned.

Plan

carried with

erroneous

aloft

fuel

cell

Note:

Gemini

1965.

The

which

Gemini

despite

a

although

to by

base-line

computer

rendezvous Gemini

oxygen

successful

to

programmed

itself

performed

into as

a transponder-bearing

cancelled

because

of

pod

problem

supply.

was

attempt

6 was

with

5 was

6 previously

launch

information

was

scheduled cancelled

rendezvous, Atlas

booster

-more-

for

launch

whenthe

failed launch.

Oct.

Agena,

to achieve

25j with

orbit

-7g-

PROJECT

George

OFFICIALS

E o Mueller

Associate A_linistrator_ Office of Manne_i Space Flight, NASA Headquarters, Acting Director, Gemini Program

LeRoy E. Day

Acting Deputy Director, NASA Headquarters

William

C. Schneider

Deputy Director, Mission Operations_ Office of Manned Space Flight, NASA Headquarters, Gemini 7 and 6 Mission Director

Charles

W. Mathews

Gemini Progr_n Manager, Mannec_ Spacecraft Center, Houston, Texas

Christopher

G. Merritt

C. Kraft

Preston

Lt. Gen. Leighton

Maj.

G_n.

Flight Director, Center, Houston

Program,

Spacecraft

Deputy Mission Director for Launch Operations t Job_l F. Kennedy Space Center, NASA_ Kennedy Space Center, Florida

I. Davis

USAF, National Range Division Co_nander and D0D Manager of Manned Space Flight Support Operations

V. G. Hasten

Col. Richard

Manned

Gemini

USAF, AFETR

C. Dineen

Deputy

DOD Manager and Commander

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

Lt. Col. John G. Albert

Chief, Gemini Launch Division, 6555th Aerospace Test Wing, Air Force Missile Test Center# Cape Kennedy, Florida

Rear Adm. W.

USN, Manned Spacecraft Support, • Conm_nder, Task Force 140 (Atlantic Ocean Recovery Forces)

C. Abhau -more

-

-79-

U.S. MISSION

MANNED

SPACECRAFT HRS. MIN.

HRS. SEC.

SPACE

FLIGHTS MAN-hUED HOURS IN MISSION HRS. MIN. SEC.

TOTAL MANNEDHRS. CUMULATIVE HRS. MIN. SEC.

MR-3

(Shepard)

15

22

15

22

15

22

MR-4

(Grissom)

15

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

l0

22

27

MA-8

(Schirra)

9

13

ll

9

13

ll

19

35

38 i

MA-9

(Cooper)

34

19

49

34

19

49

53

55

27

Gemini 3 (Grissom & Young)

4

53

00

9

46

O0

63

41

27

Gemini 4 (McDivitt & White)

97

56

ll

195

52

22

259

33

49

Gemini 5 (Cooper & Conrad)

190

56

O1

381

52

02

641

25

51

-more-

-80-

SPACECRAFT

McDonnell tractor

for

Aircraft

the

Gemini

CONTRACTORS

Corp.,

spacecraft.

AIResearch Manufacturing Los Angeles, Calif. The Eagle Pitcher Joplin, Mo. IBM New

Corp. York,

Northrop Newbury

Co.

Co.

Others

is prime

con-

include:

Environment System

Control

Computer,

Corp. Park, Calif.

Guidance

Parachutes

OAMS,

Chemical Md.

contractors

RCS

Calif. Corp.

Westinghouse Electric Balt_nore, Md.

Retrorocket

Ejection

Corp.

_endezvous

System

Seats

Radar

System

include:

General Dynamics, Div., San Diego,

Titan

Mo.,

Batteries

Weber Aircraft Corp. Burbank, Calif.

Atlas

Louis,

N.Y.

Rocketdyne Canoga Park, Thiokol Elkton,

St.

Convair Calif.

Airframe and Integration

R0cketdyne Div., North American Aviation, Inc., Canoga Park, Calif.

Propulsion

General Electric Co., Syracuse, New york

Guidance

II contractors

Systems

Systems

include:

Martin Co., Baltimore Divisions, Baltimore,

Md. -raore-

Airframe and Integration

Systems

-81-

Titan

Agena

II

contractors

(cont.)

AeroJet-General Corp., Sacramento, Calif.

Propulsion

General Electric Syracuse, N.Y.

Radio Command System

Co.,

Suit

Guidance

Burroughs Corp., Paoli, Pa.

Ground

Aerospace E1Segundo,

Systems Engineering Technical Direction

Corp., Calif.

D contractors

Guidance

Computer

and

include:

Lockheed Missiles and Space Co., Sunnyvale,

Food

Systems

Calif.

Airframe and Integration

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

Propulsion

McDonnell Aircraft St. Louis, Mo.

Target

Co.,

Systems

Systems

Docking

Adapter

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.,

-end-

Formulation

Concept

Processing,

Food

Contractors