Mariner Mars 1969 Launches - Press Kit

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WO 2-4155ATI ON AL AERONAUTICS A ND SPACE AD MINISTR ATION

N E W S WASHINGTON,D .C. 20546 Ls ' WO 3-6925

FOR RELEASE: FRIDAY

February 14,1969

MLEASE NO: 69-26

Pw

GENERAL

MISSION

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30(CATEGORY)

2/6/69



NA TIO NA L AERONAUTICS AN D SPACE ADMINIS TRATION 'NO 2-4155

N E W S WASHiNGTON,D .C. 20546 TELS ' WO 3-6925

FOR RELEASE: FRIDAYFebruary 14, 1969

RELEASE NO: 69-26

MARINER MARS 1969 LAUNCKES

Two 900-pound Mariner spacecraft, F and G, w i l l be launched

from pads 36A and 36B a t Cape Kennedy on fly-by missions t o

Mars by th e National Aeronautics and Space Administration

dur ing a period beginning Feb, 24, 1969,

Launch dates are 8 p.m, EST, Feb, 24, f o r spacec ra f t F and4

I4 p .m . EST, March 24, f o r G. I f successful ly launched, the '

spacecraf t w i l l become Mariners V I and V I I .

fo r each will be the Atlas-Centaur,

The launch vehicle

A r r i va l dates a t Mars are J u l y 31 f o r F, and Aug. 5 for G,

each a r r i v i n g a t about 1 , m . EST on these dates.

Standard Time would be 10 p.m, one day ear l i e r for each space-

c ra f t , ) Mar ine r F will make a n e qua t o r i a l pass over the Mars

surface and Mariner 8 is scheduled for a p o l a r pass five days

l a t e r t o furnish data as d i f f e r e n t as poss ib l e from t h e s tand-

p o i n t of geography and climate.

(Pac i f i c

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The '69 mission i s a follow-on t o the 1964-65 Mariner

f l i g h t t o Mars and a precursor to the 1971 and 1973 Mars

missions, In 1971 two Mariner-class ve hi cl es w i l l o r b i t

Mars f o r three months, and i n t h e 1973 mission, Pr oje ct Viking,

two spacecraft w i l l o r b i t Mars and de tach sof t l anders to

descend to th e surface.

The Mars 169 miss ion objec t ives are t o s tudy the sur face

and atmosphere of Mars t o es tab l i sh th e basis f o r f u t u r e

experiments in the s ea rc h f o r e x t r a - t e r r e s t r i a l l i f e and t o

develop technology f o r fu tur e Mars missions.

The ' 69 f l i g h t s w i l l not determine i f l i f e e x i s t s on Mars

but w i l l h e l p es tabl i sh whether o r n o t th e Martian environment

i s s u i t a b l e f o r l i f e ,

Two t e l e v i s i o n cameras aboard each spacecraf t w i l l photo-

graph the d i s c of Mars dur ing t h e approach t o th e planet and the

surface dur ing t h e fly-by. The best re so lu t ion of the approach

p i c t u r e s w i l l be about 15 miles. Be s t resolut ion from Earth i s

about 100 miles. The h i g h e s t r e s o l u t i o n i n th e s u r f ac e p i c t u r e s

w i l l be about 900 f ee t , compared w i t h two miles i n th e Mariner

I V pic tures taken in 1965.

Two inst ruments , an inf ra re d spectrometer and an u l t r a -

v i o l e t spec trome te r w i l l probe the atmosphere of Mars, An

oc cul ta t ion experiment , i n which r a d io s i g n a l s pass through the

Martian atmosphere, w i l l y i e l d data on atmospheric pres sure s

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An inf r a red rad iomete r w i l l measure surface temperatures

on both the l i g h t and dark s i de s o f Mars. A c e l e s t i a l mechanics

experiment w i l l u t i l i z e t rack ing in forma tion t o r e f i ne astro-

nomical data. This mission represents t h e f i r s t opportuni ty to

make s c i e n t i f i c measurements on the n ig ht si de of Mars.

A l l the ins t ruments on the spac ecraf t a r e des igned t o

return informat ion on Mars i t s e l f . No i n t e rp l ane t a ry ins tmment s

w i l l be flown.

The instruments were chosen to a l low corre la t ion of the

re turned data. For example, su rf ac e temp eratu re measurements

w i l l be made i n th e a r ea s photographed t o a llow mapping of tem-

pe ra ture va r i a t i ons as they may be r e l a t e d t o s p e c i f i c s u rf ac e

fea tures .

A sharp i nc rease in data r e t u r n s w i l l be achieved overth e '64-65 Mariner missions. For example, the t e l e v i s i on p i c -

tures returned by Mariner IV, in 1965, contained 240,000 b i t s

of information. In 969 each pic ture w i l l contain 3.9 mil l ion

b i t s .

was 8 l/3 bits-per-second.

bits-per-second w i t h an exper imental capab i l i ty , to be used a t

Mars i f possible, of 16,200 bits-per-second.

on the condi t ion of the spacecraf t a f t e r a four to five-month

journey through space and th e co ndi t ion and av a i l a b i l i t y of the

210-foot-diameter antenna a t Goldstone, C a l i f . , one of the

world 's most s en si t i ve antennas.

In 1965 the t ransmission b i t rate from the spacecraf t

I n 1969 th e bas ic b i t ra te i s 270

The l a t t e r depends '

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NASA assigned project responsibility including mission

operations, tracking and data acquisition for the '69 mission

to the Jet Propulsion Laboratory which is managed for NASA

by the California Institute of Technology, Pasadena, C a l i f .

Launch vehicle responsibility is assigned to the Lewis Research

Center, Cleveland.

Convair, San Diego. Tracking and communications is assigned

to the Deep Space Network, operated f o r NASA by JPL.

The contractor to Lewis i s General Dynamics/

Cost of the Mariner Mars 1.969 mission will t o t a l $148

million, $128 million f o r the spacecraft and $ 2 0 mfllion for

launching and the launch vehicles,

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ISSIOM PR.QPILE

The two Mariner spacecraft will be targeted to observedifferent regions of Mars, The first spacecraft to be launched,spacecraft F, w i l l observe the equatorial region, and spacecraftG the southern polar region.

The launches are scheuuled for one month apart on February24 and March 24.The Mars arrival dates are July 31, 1969, f o r spacecraft F andAugust 5 for spacecraft G. The five-day separation at arrival(encounter) is determined by two requirements:occur over the Deep Space Net station at Goldstone, Calif., andthat the Inst ents observe specific areas.

The launch period extends into early April ,

that arrival

The C Q R I ~ U ~ ~ T Sboard the two spacecraft will be prog-edat launch with two missions for each spacecraft. One standardmission at the high bit rate of 16,200 bits-per-second and back-up mission at 27Q bits-per-second, U s e of the high bit rate isdependent on the condition of the spacecraft and availability ofthe highly sensitive 210-foot diameter antenna at Goldstone,

The back-up afssion is automatic and can be executed with-out commands from Earth. The standard mission is automaticwith the exception of sending execute commands for the back-upmiSS;bOn*

Both plans can be changed by re-programming the computerby Earth command.

At sepaaaation from the Centaur stage the spacecraft's al-titude control system ispowered, primary and secondary Sun sen-iors are activated and the Sun acquisition sequence is initiated.In addition, the Central Computer and Sequencer is enabled, thepyrotechnic subsystem is armed f o r deployment of the solarpanels, the Canopus sensor is turned on and the tape recordersare StQpped.the tapes to prevent free-running and snarling,

The latter run during launch to keep tension on

Sun acqufsition will be accomplished approximately 30minute8 af te s separation from the Centaur, Canopus acquisitionwill be cornpletedl one to four hours after separation, Canopusis acquired by solling the spacecraft which sweeps the Canopussensor through a complete circle. The sensor will ignore lightsources in ranges below or beyond the intensity of Canopus,However, in the event of a lock-on to a light source other thanCanopus, an override comand can be sent from Earth.

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Each spacecraft has the capability of performing two mid-course corrections. Under noma1 launch conditions spacecraft

F may require two,c3will require one. F may require two cor-rections primarily because of the longer flight time of the

early launch. The longer trajectory is more sensitive to mid-course errors. The first midcourse of F w i l l occur betweenfive and fifteen days after the launch, the second betweenlaunch plus one to five months. The first midcourse for Gwill be at about launch plus five days,

The maneuver sequence begins with transmission to thespacecraft of commands giving the direction and amount of apitch turn and a roll turn and the time of motor burn, Theseare stored in the Central Computer and Sequencer until an exe-cute cormnand is sent. The maneuver is controlled by the CC&S

which can command a maneuver abort if the turns are not per-formed according t o instruotiona. Earth command can also abortthe maneuver,

Approximately 8+ minutes after the pitch and roll turnsare completed the CCBCS will command firing of the midcoursemotors. The CC&S will count the required thrust time and thencommand the engine off. The necessary internal commands arethen given for reacquisition of the Sun and Canopus.

A period of tracking is required to determine the accuracyof the maneuver,will give an estimate of accuracy,

However, telemetry at the t h e of the maneuver

The spacecraft is then returned to the cruise mode untileither second midcourse or Mars encounter, The bit rate duringcruise will be either 8 /3 or 33 l/3 bits-per-second dependingon the telecommunications performance, The rate is changed byground command.

The basic encounter phases are far-encounter, near-

In the standard mission far-encounter will begin at en-

encounter, occultation and playback.

counter minus 48 hours for spacecraft F and minus 72 hours forG.as the spacecraft passes Mars.

Encounter (E) is defined as the point of closest approach

In the standard plan spacecraft F will take 50 approachpictures and spacecraft G 91 approach pictures. Playback willbe at the high bit rate of 16,200 bits-per-second before thefly-by, If it is not possible to follow the standard plan theCC&S will automatically command a sequence of eight approachpictures beginning at about E-21 hours and ending at about E-12hours for both spacecraft. Pictures from this sequence wouldbe stored and played back after the fly-by,

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Prior to far-encounter the CC&S Issues turn-on coarmandst o the scientific instruments, the data automation system,tape recorders and s m n platform control system.is switched to 66 2/3 bits-par-second.

Telemetry

The science instruments are warmed up shortly before thefar-encounter sequence. At the ppoper time the scan platformis commanded to the far-encounter position and the far-encounterplanet sensor I s turned on. The scan platform control systemwill switch to automatic tracking when the planet i s acquiredby the sensor. The far-encounter TV sequence begins with pic-tures from Camera B only being recorded on the analog tape re-corder at required intervals of time for each spacecraft.

A l l the science instsunnents except the infrared spectro-meter take data during this phase but, as the digital recorderi s not yet in operation, the non-TV data is not recorded. How-ever, selected portions of the data are transmitted as acquired,

Near-encounter will begin at the end of the approach pic-ture sequence, The far-encounter planet sensor I s disabled t o

insure that the scan platform a11 not automatically track dur-ing this phase and the platform is commanded to the near-encounter position.

Prior to near-encounter two planet sensors are turned on.

"Planet-in-View" signals from the sensors w i l l start the re-cording of data when preceded by a start command from the CC&So r from Earth.

The analog tape recorder, storing TV data only, w i l l bestopped at about the time the scan crosses Into the night sideof Mars or E plus three minutes. The digital recorder, whichhas 'been recording selected portions of TV data (every seventhpicture element to aid analysis) and all other science data, isnot stopped until E plus nine minutes to allow recording of non-TV data from the planetfs dark side.

Occultation w i l l begin at about E plus 11 minutes and last

f o r approximately 25 minutes,

At E plus seven hours the CC&S w i l l order the scan control,data automation system and the science instruments turned off.

Playback at 270 bits-per-second from the digital tape re-corder w i l l have started at E plus four hours and will continueuntil E plus 21 hours. It is then stopped and the analog play-back (TV data only), begins at the high bit rate of 16,200 bits-per=second.

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The analog recorder w i l l l a y back for two hours and 53minutes (one complete playback7 and then the d i g i t a l playbacki s resumed. The f i r s t d i g i t a l playback is completed a t ap-proximately E p l us 32 hours and the second d i g i t a l playbackbegins,playback .

A t the beginning of the f i rs t analog playback, encounterof the second spacecraft w i l l be a few dags away.t h e f i r s t spacecraf t w i l l be c lose ly s tudied f o r p o ss ib l e r e -finement to t h e encounter plan f o r t h e second spacecraft .

The second playback i s again in te r rup ted fo r ana log

Data from

After the i n i t i a l playback of data the analog W data w i l l

be t r a ns f e r r e d t o th e d i g i t a l tape recorder and played backagain a t 270 bits-per-second,

After completion of data recovery both spacecraft w i l l beplaced in th e c ru i se conf igurat ion fo r add i t i o na l t r ack ing andspacecraf t condi t ion data.

The Mariners w i l l be launched on d i r e c t a s ce n t t r a j e c -t o r i e s from Cape Kennedy a t 8 s u% f ic i an% i n a l v e l oc i t y ( i n -j e c t i on ve l oc i t y ) to escape Earth p l u s th e a dd i t i ona l ve l oc i tyrequired t o p rovi de an encounter w i t h Mars. Escape velocity

(24,400 mph a r t d i r e c t a s ce n t i n j e c t i o n a l t i t u d e ) would only bes u f f i c i e n t t o place a Mariner i n a s o l a r orbit tha t would benear Earth 's o r b i t . The addj i t ional veloci ty i s c a re fu l l y c a l-cula ted t o y ie ld a s o l a r o r b i t t h a t w 3 i l l c ross the path 0% Marson a g$.ven date,

a t t he po in t of i n j e c t i on by th e Centaur second stage, Thef i n a l ve l oc i t y a nd t he i n j e c t i on po i n t varies from day t o daythroughout th e launch period as the re l a t i on sh ip between the

s i t i o n of Earth and Mars changes.

l a t i v e t o Earth. A t encounter a t yp i c a l s pa c e c ra f t ve l oc i t ywould be 17 ,7OO mph, r e l a t i v e to Wrs. It i s requ i red to s ta tev e l o c i t i e s i n the re la t ive sense because the ve loc i ty of a body

The t o t a l r equ ir ed ve l oc i t y i s imparted t;o the spacecraf t

A t yp i c a l i n j e c t % onve l oc i t y 1s 25,700 miles-per-hour,

the s o l a r system is based on the p o s i t i o n of %he observer.

To an observer on Earth th e ve lo ci ty of Mariner a t i n j ec -on would be as s t a t ed , 25,700 mph. To an observer on th e Sune ve l oc i t y of t he spacec ra f t a t injection would 91,6QO mph,i s i s because the Earth i t s e l f 1s orb i t i ng the Sun a t a speed

excess of 66,000 mph and t h i s v e l o c i t y p l u s t h e i n j e c t i o nve l oc i t y i s imparted t o the spacecraf t a t i n j e c t i on .

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The velocity of the spacecraft relative to Earth atinjection will slowly diminish as Mariner heads outward fromEarth and the Earth's and the Sun's gravitational fields pullon the spacecraft,Mariner will increase under the attraction of the planet.

will be trailing Earth by approximately 60,000,000miles.

Sun after injection. It will be ahead of Mars prior to encounterbut, as its velocity is still decreasing as a result of the Sun's

pull, Mars will catch up with the Mariner, pass it, and beslightly in front of the spacecraft at encounter. Encounteroccurs as the path of' the planet and the spacecraft cross.Mariner's direction of flight w i l l then carry it behind Mars.to allow the occultation experiment, It w i l l be behind Marsfor approximately 25 minutes,

As Mariner approaches Mars the velocity of

At launch Mars w i l l be ahead of Earth. At encounter Mars

The spacecraft w i l l follow a long curving path around the

In designing trajectories for the Mars mission the trajec-tory engineer must satisfy numerous restrictions o r constraintsthat influence the final trajectory. For example, the flighttime must not exceed certain limits imposed by the lifetlme ofthe spacecraft; injection velocities are prescribed by the capa-bility of the boost vehicle, thus affecting the transit time;

an adequate launch period must be provided; communication dis-tances must not be excessive; arrival at Mars must be properlytimed to coincide with those regions of maxlmum interest forscientific viewing; and encounter is designed to occur duringthe viewing period of Goldstone, the Mojave Desert station ofthe Deep Space Network,

include the effect of solar wind pressure on the flight pathas well as the gravitational attraction of Sun, Earth, Mars,Mercury, Venus and Jupiter.

Other factors influencing Interplanetary trajectories

In selecting an a3ming zone that will determine the path

of the spacecraft as it passes Mars, the trajectory engineermust satisfy the many and sometimes conflicting requirementsof the scientific experiments of the mission, for example, in-sure spacecraft occultation by Mars. It is also required toassure that the Mariner w i l l not -pact Mars, in order to pre-vent contamination of the planet by Earth microorganisms,

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The accuracy of the encounter with Mars will be influencedby launch accuracy, radio tracking accuracy, flight path calcu-lation accuracy, and the midcourse correction accuracy,

Calculations after launch will determine if the flightpath of the spacecraft is within the correction capability ofthe midcourse motor.two midcourse corrections in the event the first does not yieldthe desired accuracy for encounter.

Mariner has the capability of performing

The accuracies demanded by the launch vehicle and by the

midcourse motor c a n be illustrated by the following numbers.The injectSon velocity can vary only by plus or minus 40 miles-per-hour or the resulting trajectory will not be within thecorrection capability of the midcourse motor.. At midcoursemaneuver, an error of one mile-per-hour wlll result in movingthe spacecraft at Mars by 5,000 miles.

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SCIENTIF'IC EXPERIMENTS

Despite s t ud ie s from Ear th and t h e f l i g h t t o Marsof Mariner IV, our understanding of Mars i s l i m i t e d . Manyquestions remain t o be answered.

The purpose f o r f i v e of t h e s ix experiments i n the' 6 9 Mars mission i s t o explore the surface and atmosphereof Mars. The f i v e exper iments are designed t o y i e l d data on i t sphysical , chemical and thermal prope r t i e s ; t h e s i x th t ore f ine a s t ronomica l data.

A successful mission w i l l h e l p es tab l i sh informat ion

about th e present environment and provide a b a s i s f o r d e t e r-mination of t h e pl an et 's or ig in and his tor y. One answer beingsought i s whether o r n ot th e pas t o r presen t environmentwould allow t h e existence of l i f e forms.

The experiments w i l l not determine i f l i f e e x i s t s onMars. The investigation, however, w i l l h e l p se l ec t l andings i t e s f o r f u tu r e l i f e det ect ion experiments and h e l p answerother b iologica l ly impor tant ques t ions about Mars inc ludingtemperature ranges and t h e presence of water.

The best re so lu t ion of the sur face as seen from E a r t hi s about 100 miles. From Mariner IV i t was about two miles.

The Mariner pictu res , obtained over only one percent of t h esurface , revea led t h a t area t o be heavi ly cratered.

Earth based s t ud ies revea l t h a t about 1/3 of Mars i scovered by i r r e g u l a r l y shaped da rk areas which appear bluei n c ol or . The remainder of t h e plane t i s covered by br i gh t e rareas which are di s t i nc t ly o range co lored . The bas ic di f fe rences-climate, composition, water content-between t h e l i g h t andd a r k areas are unknown. The'6g mi ss ion shou ld prov ide someanswers t o these ques t ions .

The remarkably re gu la r and annu al wave of dark enin g tha tsweeps from th e poles toward t h e Equator over t h e da rk areasa t half-year i n t e r v a l s ( i n l o c a l s p r in g ) has been construedby some observers as evidence of vegeta t ive l i f e on Mars. Othert heor i e s i nc lude a chemical r e a ct i o n t o w a t e r v a po r from thepoles and volcanic ash o r d u st carr ied by seasonal winds.

Some observers have reported s t r a i g h t l i n e markingsi n the l i g h t areas, termed canals . Whether or n o t t h e y e x i s tas a c t u a l c on ti nuous f e a t u r e s o r a discont inuous ser ies off e a t u r e s i s unknown. Photography from t h e mission i s expectedto s e t t l e this poin t .

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Mars has two po l a r caps be l ieved t o be t h i n layerso f f r o s t o r i ce . The caps recede i n the Martian spring andt h i s may be assoc ia ted w i t h t h e wave of darkening.i s unknown i f the caps are carbon dioxide ice , water i c eor a mixture of both.

B u t i t

Extremely l i t t l e w ater has been detected i n t h e Martianatmosphere and i t i s not known if the h i s t o r y of th e planetincluded a period when f r ee water existed on t h e surface. Ifwater e x i s t e d i n th e pas t i t i s poss ib l e t ha t water i s f rozenunder th e s u r f a c e i n a form of permafrost . If l i q u i d waterdoes ex i s t on Mars i t i s bel ieved t ha t i t would be found i nsmall, l o c a l 'areas having some source of hea t other thanSunl ight , poss ibly a volc anic source, Such areas w i l l be sought

as l i k e l y areas f o r t he l a nd ing of l i f e detec t ion devices .

P r i or t o t h e data on t h e atmosphere returned by MarinerIV i t was bel ieved t ha t the atmosphere was denser. Observationsfrom E a r t h had placed t h e de ns i t y a t 25 m i l l i b a r s , p l u s o rminus 15. Mariner IV's value w a s a t t h e lower end of t h i srange, This meant, f o r example, t h a t water on Mars could onlye x i s t as i c e o r vapor. There i s no p o s s i b i l i t y of any permanentbod ie s of l i qu id water ex i s t i ng on t h e planet but temporarymoisture may o cc ur i n l o c a l areas.

The new pressure value also ruled out l anding onMars w i t h convent ional parachutes only. Stud ies were under-

taken on parachutes designed f o r an extremely thin atmosphere,Landing vehicles are now seen to employ both retro-rocketsand sp ec ia l parachutes .

It i s e s s e n t i a l t o an understanding of Mars t o knowt h e de ta i l ed composition of i t s atmosphere and related i n =format ion on pressure and temperature var ia t ion s, o ri gi n ofi t s gases, c i r cu l a t i on and c loud forms. The main consti tuentof t h e atmosphere i s bel ieved t o be carbon dioxide. Theatmosphere i s extremely t h i n w i t h a va l ue fo r t h e sur facepressure of 9 m i l l i b a r s as compared w i t h 1,000 mil l ibars f o rEar th .

Clouds observed on Mars a re a t t r ib ut ed t o condensed vapor(carbon dioxide or water) and dust .color , can pers i t s for days over large areas and can spreada t speeds as high as 100 mph.

The l a t t e r are yellowish i n

The Mart ian atmosphere a l so holds another mystery, ageneral haze that i s i n v i s i b l e t o t h e eye but can be photographedi n b lu e or v i o l e t l i g h t . It us ua l l y b l o t s ou t s u r f a c e f e a t u r e s ,but can suddenly clear. T h i s i s no t understood.

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The ins t ruments selected f o r th e 369 mission willprobe t h e surface and atmosphere of Mars i n t h e v i s i b l e andn e a r v i s i b l e p o r t io n of th e electr oma gnet ic spectrum, from t h einf ra red region through t h e v i s i b l e p o r t i o n t o

theu l t r a v i o l e t

region.

Molecules and atoms absorb and re-radiate t h e energyof Sunl ight i n s pe c i f ic wavelengths tha t are s igna tures ofthe t y p e of molecule o r atom. By us i ng de t e c t o r s s e ns i t i vet o these specif ic wavelengths the inst ruments can providedata on th e presence and amount of gases o r so l id s , and ontemperatures.

The occul ta t ion experiment uses t h e spacecraft r a d i oand r e qu i r e s no o t he r spacecraft hardware. Data for th ece l e s t i a l mechanics experiment i s obtained from the e f f e c t

of bodies i n space on th e spacecraft f l i g h t path as measuredby radio t racking.

Television

The ob j e c t i ve of th e t e levis ion exper iment i s tophotograph su rfac e and atmospheric fe at ur es over as muchof t h e plane t as p o s s i b l e to determine i f there are basicdifferences between the l i g h t and d a r k areas, le ar n moreabout the seasonal ly varying dark markings, and seek physZcalc lue s on t h e p l a n e t 8 s o r i g i n and evolut ion.

To accomplish these aims, and t o Drovi.de f o r t h eunexpected inh eren t i n an explorato ry mission, t h e experi-menters designed t h e experiment t o include:

... wo cameras w i t h medium and high re so lu t ion toprovide both broad and detailed coverage. Camera A, medium reso-l u t i o n (wide angle ) , Camera B, high resolut ion (narrowangle ).

... ed, green, and blue f i l t e r s on Camera A t ode l in ea t e co lor d i f fe rence , yel low on Camera B t o r educ ehaze.

... se r i es of a t leas t e ight p ic tures , and as many90, of the d i s c of Mars will be taken as th e spacecraftapproaches the plane t .

... ser ies of 24 close-up pictures of t h e sur face

as

t aken a t a c los ing range from approximately 6,000 t o 2,000miles from the s u r f a c e o

... t r a j e c t o ry chosen so t h a t the close-up photographsW i l l cover as many as poss ib l e o f th e var ious types of f e a t u r e sobserved on Mars.

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These f e a t u r e t y p es are: permanent da rk markings,changing dark markings, oases, "blue" maria, canals, po l a rcaps, wave-of-darkening areas, white markings on crater r i m s ,c i r c u l a r l i g h t areas and l ight areas that vary i n color . Alsoo f i n t e r e s t are various cloud formations observed on Mars.

The f i r s t series of photographs w i l l be taken duringth e far-encounter sequence as t h e spacecraft approaches Mars.The d i s k of Mars w i l l be v i s i bl e i n these photographs w i t hthe d i s k appearing l a r g e r i n each photograph as t he d i s t a nc ecl o se s between sp ac ec ra ft and pla ne t. Most of th e sur face w i l lbe photographed as the p l a ne t r e vol ves i n f ron t of the approach-ing spacecraf t .

s l i gh t l y fuz zy p i c t u r e s of low reso lut io n because of th egreat di s t ance of Mars from Ear th and because Ear th ' s atmosphered i s t o r t s the image of Mars. The Mariner mission provid es %hef i r s t oppor tuni ty t o photograph the d i s k close-up without thed i s t o r t i o n of E a r t h ' s atmosphere.

Astronomers photographing Mars from Ear th record

The approach pictures w i l l g i v e s c i e n t i s t s th e f i r s td e t a i l e d p i c t u r e s of fea ture s p rev ious ly studied from Earth.The photographs may a l s o lo ca te haze, c louds o r dus t s torms,and al low s tu d ie s of changes during th e t i m e each ser ies i smade and during t h e f ive-day in te rv al between spacecraft .

The t e levis ion exper iment might be u s e f u l f o r d e te c ti o nof moist areas, i f any, on th e Mars surface. If meltingoccurred i n a l o c a l l y w a r m area, t h e water would qu ick ly vapor izei n the low Martian atmospheric pressure and form clou ds i n t h ecold Martian a i r above the pl an e t *s surface . Such a watercloud might r i se t o a cons iderable h e i g h t and have a d i s t i n c t i v eappearance.f u l i n d i c a t o r t o b i o l o g i s t s of th e p o s s i b i l i t y of some formof l i f e . However water is on ly one of many require ment s f o rt h e poss ib l e ex i s t ence of l i f e .

I f water i s present on Mars, i t would be a hope-

O f prime importance i s th e p o s s i b i l i t y of determiningwhether th e sur face of Mars has been i n i t s present s ta te overa long period of t i n e o r whether the presen t s t a t e i s only onestage i n a long hi s to ry of change. If t h e former were true itwould indicate th e planet probably has never had a dense atmosphereduring i t s h i s t o ry ; i f th e l a t t e r , it would be important t osearch f u r t h e r f o r e v idence t h a t l i q u i d water m i g h t have playeda r o le i n shaping the present surface . This would be p e r t i n e n tt o the development of l i f e on the plane t .

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O f p a r t i c u l a r i n t e r e s t i s t h e po ss ib i l i t y of photo-graphing the areas covered by t h e 21 c lose-up pic tures oft h e Martian surface taken by Mariner IV i n 1965. These would

y i e l d a more exact lo ca t i on of the pic tured areas on Mars andaid i n de te rmining the r e l a t i ons h i p of t h e 2 1 photographs t osurrounding areas. Any changes i n t h e appearance of theseareas over the four-year i nt er va l would a l s o be of i n t e r e s t .

The ex ist en ce and natu re of s t r a i gh t l ine markingson the surface, which have been reported by = m e astronomersand termed canals , may a l s o be c l a r i f i e d b y t h e approach ser iesof photographs,

The innermost of Mars' two Moons, Phobos, might appeari n th e approach series. To be su f f i c i e n t l y p rominent i n aphotograph t o y i e l d information on i t s s i ze , the Moon wouldhave t o be photographed a t f a i r l y c l o s e r an ge and pre fe rab lyaga ins t a black space background near the edge of Mars' disk .I t would probably be i n v i s i b l e i f photographed against theb r i g h t d i s k of Mars, To photograph i t a t very c lose rangeaga ins t a background of space, however, would re qu i re man-euvering t h e scan plat fo rm a t a time when t h e spacecraf t wasnearing t h e planet . Other requirements w i l l probably prohibi topera t ion of t h e scan plat form a t t h i s t i m e even i f the Moonwere favorably placed.

Camera B, equipped w i t h a modified Schmidt Cassegraintelescope, w i l l be used f o r the approach pic tu res .

The stan dar d approach p la n programmed i n t h e on-boardcomputer provides for 50 approach pictures . It i s presen t lyplanned t o increase t h i s t o 80-90 approach pic tures for space-c r a f t G by reprogramming the on-board computer a f t e r launch.T h i s plan i s dependent on the success of th e spacecraf t F en-counter and t h e condi t ion of space craf t G. Both of these plansa re dependent on t h e a v a i l a b i l i t y o f t h e 210 f t . diameter antennaa t Goldstone to a l low t ransmission t o E a r t h a t 16,200 b i t s - p e r -second before t h e f ly-by . If t h i s i s not poss ib l e the secondprogrammed plan w i l l be used.t u r e s f o r each space craf t and t ransmiss ion to Ear th a f t e r t h efly-by a t 270 bits-per-second,

Both cameras w i l l be used during t h e f ly -by t o recordsur face p i c tu re s .IV which photographed Mars i n 1965.camera has been equipped w i t h a wide-angle l e n s which w i l l coveran area 12 t o 15 times l a rger than t h e Mariner IV camera b u tw i l l have approximately the same r e s o l u t i on , t w o miles. There so lu t ion of Camera A w i l l be 1/10 tha t of Camera B arid cor re s -pondingly its photographs w i l l cover a n area 100 times la rgeron th e sur face of Mars. The bes t re so lu t ion f o r Camera B i s

expected to be 900 f t . compared w i t h two miles f o r t h e 1964-65Mars mission.

It provides e i g h t approach pic-

Camera A i s similar t o th e camera on MarinerFor t h e 1969 mission t h e



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The cameras w i l l ope rate al te rn at el y. They have beent imed t o provide overlapping of t h e Camera A photographs w i t ht h e h igh r e s o l u t i on Camera B photographs f a l l i n g in s ide th eoverlapped portion t o a i d i n in te rp re ta t i on . Each camera w i l lt ake one pic ture every 84.48 seconds.

The cameras w i l l be aimed a t a band of s pe c i f i c areasof i n t e r e s t on Mars. Careful s t ud ie s have been made t o de te rminese l ec t ion of areas t o be photographed. The p a t h of t h e space-c r a f t pas t Mars and t h e point ing angle of t h e platform arese lec ted on t h e bas i s of these s t ud i e s .

The pr inc ipa l i nves t iga tor i s Dr. Robert B. Leighton,of t h e C a l i f o r n i a I n s t i t u t e of Technology. Co-investigatorsare D r . Bruce C. Murray, D r . Robert P. Sharp, D r . Norman H.Horowitz, a l l of Caltech; Alan G. Herriman and Richard K. Sloan,of t h e J e t Prop ul sion Laboratory; Merton Davies, of Rand Corp.,Conway Leovy, University of Washington, and Bradford A. Smith,N e w Mexico State University.

-.nfr ared Spectrometer ( I R S )

T h i s inst rument w i l l determine t h e presence in t h elower Martian atmosphere of molecules t h a t sug gest biochemical

processes, a f f ec t t emperatures on t h e surface and l i m i t t h eamount of u l t r a v i o l e t r ea ch in g the surface ; de tec t v a r i a t i o n si n t h e composition of t h e atmosphere, part icularly water vapor,re l a t i ve t o geographic l oca tions .

The inst rument covers about the same areas as th e t e l e -vi si on cameras t o h e l p determine the composition of t h e l i g h tand d a r k areas v i s i b l e on Mars. Data from t h i s experiment cana l so be compared w i t h some of t h e r e s u l t s f rom th e u l t r a v i o l e tspectrometer concerning the composition of t h e Mar tian atmosphere,

The infrared wavelength region detected by t h i s inst rument(1.9 t o 14.3 microns) w i l l a l low de tec t ion, i f present , of water,carbon diox ide, methane, eth yle ne and ac et yl en e as w e l l asother molecules. The presence of or ga nic molecules would l endevidence t o t h e exis tence of e i t h e r pas t o r present l i f e onMars. This d ete ct i on however would n ot a l low fi r ml y s ta t i n ge i t h e r p o s s i b i l i t y .

The presence of s u lf u r dioxide and hydrogen sulphidecould ind i ca t e poss ib l e Mart ian vo lcan ic ac t i v i ty , a valuablec l ue as t o t h e h i s t o ry and i n t e r na l s t r u c t u r e of Mars,

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The de tec t ion of ozone molecules, correlated w i t hdata from t h e u l t r a v io l e t spectrometer experiment, could pro-vide informat ion on t h e amount of UV reaching th e surface.Ozone i s a s t rong absorber of W.

The d i s t r i b u t i o n of water vapor i n t h e atmosphere canbe cor re l a t ed w i t h ground’ fea ture s t o p o s s i b l y determine d i f -ferences between l i g h t and d a r k areas.i n the d i s t r i b u t i o n of water vapor could indica te poss iblefu ture l and ing s i t e s f o r l i f e detection equipment.

Any large va r i a t i ons

Analys i s of t h e data can also y i e l d informat ion onphoto chemical processes, sur fac e temperatures, re f l ec tedSunl ight, emiss ivi ty of surf acean d poss ibly chemical compo-s i t i o n a t t h e surface.

approximately e i g h t watts of power during t h e encounter sequence.

During the cruise por t ion of t h e mission i t w i l l draw f o u rwatts of power f o r heaters.

The experiment weighs 35.8 pounds, and w i l l us e

P r i nc i pa l i nve s t i ga t o r i s Dr. % C. Pimentel of theUniversi ty of Cal i fo rn i a a t Berkeley.D r . K. H e r r , a l s o of U.C./Berkeley.

Co-invest igator i s

Ult rav iol e t Spec trometer

The u l t r a v i o l e t s pe c t rom e t e r i s des igned t o i de n t i f ygases i n t h e upper Martian atmosphere by de tec t ion of var ious

molecules, atoms and io ns (molecules o r atoms t h a t have gainedor l o s t e lec t r ons) and t o de te rmine t h e i r amounts.

I d e n t i f i c a t i o n of the gases p r es e nt i n t h e Marsatmosphere can determine i f t h e atmosphere i s th e r e s u l t o fcondensation of s o l a r material , and there fore , primordial i no r i g i n , o r w a s formed by gases released from th e plane t , a son Earth, or a combination of t h e two. The composition, andthe re fore th e or ig in and evolut ion of the atmosphere can revealt h e age and evolut ion of t he pl ane t i t s e l f .

A s tudy of t h e atmosphere can a l s o determine the environ-ment i n which l i f e forms, i f present on Mars, would have t oex i s t.

A lack of oxygen, for instance, would mean that l i f eforms must have developed some means of obtaining oxygen otherthan from t h e atmosphere. The lack of a shie ld ing layer of

on Earth f i l t e r s out th e ul t raviole t wavelengthsd l y t o l i f e forms, would t e t ha t a l i f e formd r e qu i r e i t s own protec ex i s t or would existe c t i v e l a y e r of s o i l o r

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An u l t r av io l e t spect rometer i d en t i f i e s d i f fe r en tspecies (molecules, atoms and ions) by the wavelengths ofl i g h t t h a t they absorb or emit. Each specie absorbs t h eenergy of l i g h t , which i s composed of a number of different

wavelengths, a t one o r more wavelengths and re-radiates theabsorbed l i g h t a t t h e same o r longer wavelengths. An atomre-radiates t h e wavelength i t absorbg t h e spectrometer candetect ce r t a i n wavelengths and thus i de nt i f y th e specie.

UV s tud ie s o f Mars have not been made from Earth becausei t cannot penetrate our atmosphere. B r i e f st ud ie s have beenmade above t h e atmosphere from balloons and sounding rockets,T h i s miss ion represents t h e f i r s t a t t e m p t t o u t i l i z e a Wspectrometer t o i d e n t i f y gases i n t h e Martian atmosphere.

The W experiment w i l l a l s o y i e ld data on atmosphericde ns it y , t em pe ra tu re s r e l a t i v e t o a l t i t ud e and the amount of

UV which s t r i k e s the surface of Mars,P r i nc i p al i n v e s t i g a t o r f o r t h i s experiment i s D r . Charles

A. Barth of t h e Universi ty of Colorado. Co-investigators areW i l l i a m G. Fas t ie of t h e John Hopkins University; Fred C.Wilshusen, K e r m i t Gause, Ken K. Kelly, Ray Ruehle , JeffreyB. Pearce, Charles W, Hord, a l l of t h e TJniversity of Colorado,and Edward F. Mackey, of Packard-Bell Electronics,

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Infrared Radiometer ( I R R )

T h i s experiment w i l l provide temperature measurements ofthe sur face o f Mars by de tec t ion of thermal r a d i a t i o n i n thei n f r a r e d po r t i on o f the electromagnetic spectrum.

The inst rument i s boresighted wi th the t e le vi s i on camerast o a l low c or re l a t i on of sur face t emperatures w i th t e r r a i n fea-tures and clouds. .Th i s w i l l provide a map of the sur facere l a t i ng t empera ture va r i a t i ons t o sur face fea tu re s , I f t he r ei s f rozen water (pe rmaf ros t j on Mars, there i s a p o s s i b i l i t yof loca l ized mois t areas on the surface. This would requirea h i g h e r surface temperature i n the area which would bede t e c t a b l e . I c e w i l l not ac tua l ly . .me l t i n the low Martianatmospheric pressure but w i l l go from the s o l i d s ta te t o vapori n one s te p, However the po ss ib i l i t y of small, moist areasremain, Photographs could also r e v e a l a vapor cloud i n t he

same area.D a t a from t h i s experiment on th e Southern ice cap ( t he

instrument on th e s pa c e c ra f t targeted f o r t h e p o l a r pass) maydetermine i f t h e Martian poles are covered w i t h f rozen wateror frozen carbon dioxide. I f the temperature recorded i sapproximately -253 degrees F or lower, i t i s l i k e l y t h a t t h e capi s composed primarily of carbon dioxide, t h e major cons t i tuentof th e Mart ian atmosphere. Temperatures above th e po i n t wherecarbon dio xid e would vaporize, i n a range above -253 degrees F,would imply t h a t the caps are frozen water. Lower temperatureshowever would not rule out a mixture of f rozen water and carbondioxide ,

This experiment may a l so de te rmine if the white r i m s seenon cr a t e r s i n th e Mariner IV photographs of Mars are remnantsof carbon dioxide or water ices,

The inst ruments aboard both spacecraft w i l l scan theMart ian surface across th e s u n l i t po r t ion and i n t o t he darks i d e , i n e f f ec t , from la t e morning t o l a t e evening. T h i s dataw i l l y i e l d cool ing rates showing the d a i l y v a r i a t i o n s i n t e m -pe ra t u r e s as the surface absorbs heat from the Sun dur ing theday and loses heat dur ing the night hours . T h i s informat ionmay indicate i f the sur face i s solid, l i k e rock , o r composed ofloose material l i k e sand o r dus t . Data on t h e dark s ide of

Mars, which i s not obtainable from Earth, w i l l be of pa r t i cu l a rvalue.

The data w i l l a l s o be analyzed to see i f i t revea l sd i f f e r e nc e s i n c oo li ng ra tes f o r th e l i g h t and dark areas onMars.

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Two det ec to r s i n t h e inst rument w i l l each provide 30readings every 63 seconds.p l ane t a ry temperature, two w i l l be ca l ibr a t i on readings andone eng ine eri ng measurement on th e instrume nt: temperatu res

or vo l tages.

Of the 30 readings, 27 w i l l be

P r i nc i pa l i nve s t i ga t o r f o r th e experiment i s D r . GerryNeugebauer of' the C a l i f o r n i a I n s t i t u t e of Technology. Co-i nve s t i ga t o r s are Dr. Guido Munch, of Caltech, and Stillman C.Chase, of Santa Barbara Research Center.

S-Band Occul ta t ion

T h i s experiment was f i r s t performed a t Mars by the MarinerN spacec ra f t i n 1965. The data returned provided new valuesfor the a tmospheric pressure , den si t y and elect ro n den si t y i nthe Martian atmosphere, It changed s c i e n t i f i c views of Mars

considerably.thin Martian atmosphere about l / l O O t h t he den s i ty of Earth 'satmosphere.

data and, i n ad dit ion , ob ta in pre cis e measurements of therad ius of Mars and t o at tempt t o measure reflect ion of r a d i osig na ls from the su rfac e of Mars. The l a t t e r could be cor -r e l a t e d w i th data from other experiments aboard the spacecraftt o make e st im at es of t h e e l e c t r i c a l c h a r a ct e r is t i cs .

The data provided a new picture of an extremely

The objec t ives o f t h e ' 6 9 mission w i l l be to re f ine t h i s

This expe r iment u t i l i ze s t he rad io s igna l s t r ansmi t t ed

I t does require a t s a j e c t o ry tha t passes behind

from t h e spacec ra f t t o Earth and does not require on-board

equipment.Mars, as seen from Earth, thus occul t ing th e spacecraf t fromt h e view o f t r a ck i ng s t a t i on s .

As the spacecraft curves behind Mars, i t s rad io s igna lwill pass through the Martian atmosphere and be c u t o f f a t thesurface. The si gn al w i l l reappear a s the spacecraft comes outfrom behind t h e plane t and aga in the radio s igna l w i l l passthrough the pla ne t ' s atmosphere.

The atmosphere w i l l r e f r a c t th e r ad io waves, changingthem i n frequency and st re ng th . Measurements on Ear th of t hesechanges i n the rad io s i g n a l y i e l d t he data on t he de ns i ty andpressure of the atmosphere

.Similar changes i n t h e atmosphere of Mars are caused by

e lec t ron dens i ty and are al s o measurable. As the encounter w i thMars w i l l occur during a per iod of i ncr e as e d s o l a r a c t i v i t y ,the e lec t ron count is expected t o be up t o four times the va luesfound by Mariner I V .

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I f both Mariner F and G suc cessf ul ly encounter mrs theexperimenters will have four separate measurements as eachspacec ra f t w i l l provide a measurement on entrance intooccu l t a t i on and e x i t from occul ta t ion.

The t r a j e ct o ri e s have been planned t o provide fo ur pointss e pa ra t e d i n l a t i t ude f o r these measurements, This w i l l en-hance the re su l t s , as i t i s expected t ha t there may be va r i a t i onsof pressure at d i f f e r e n t loca t ions on the surface. The datawill also yreld an accu ra te va lue f o r the radius and obla tenessof Mars. The cu rrent va lues a r e uncer ta in , as var ious forms ofmeasurement a r e no t i n agreement, Knowing th e radius and f igure(shape) of' a p l a ne t can provide an est imate of i t s den s i ty anda i d I n understanding i t s i n t e r n a l s t r u ct u r e.

Determlnatlon of the a tmospheric densi ty of Mars i s v i t a lt o t h e des ign of future landing c raf t , and i s a c r i t i c a l f a ct o ri n the r e s o l u t i on of impor tant sc i e n t i f i c ques t ions on the na tureof the plane t ,

The p r i n c i p a l i n v e s t i g a t o r i s D r . A. J, Kl iore of the J e tPropulsio n Laboratory. Co- inve stiga tors are Dr. S. I. Rasool,Goddard I n s t i t u t e f o r Space Stu die s; Gunnar Fjeldo, StanfordUniversi ty, and Boris S e i d e l , J P L .

C el es t i a l Mechanics

This experiment derives i t s r e s u l t s from spacecraf t t rack-ing in fo ma t io n and does not requ i re s pe c ia l hardware on th espacecraf t . The e f f e c t of bodies i n space on the f l i g h t p a t h

of t he spacec ra f t is used t o determine th e masses of thosebodies. Ground equipment t h a t measures th e di s t ance from E a r t ht o the spacecraf t w i l l be used t o determine the distance fromthe cen te r o f t h e Ear th t o the center of Mars a t encounter.

The immediate objec t ives of the experiment are t o d e t er -mine: the mass of Mars; the Earth-Moon mass r a t i o a nd thedi s t ance from Ear th t o Mars a t encounter. Long range ob je ct iv esare t o o bt ai n an improved ephemeris of Mars ( i t s pos i t i on a tgiven times i n I t s s o l a r o r b i t ) and t o a t tempt t o measureG eneral Re l a t i v i s t i c e f f e c t s on the s o l a r o r b i t o f the ' 69 space-craf t.

It i s expected tha t th e ranging information a t encountercombined w i t h radar bounce data w i l l provide a determination oft h e s i z e of Mars. T h i s technique was used t o determine th eradius of Venus during th e Mariner V fly-by of that plane t on~ c t . 9, 1967.

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Improving the ephemeris of Mars is part of an existingJ P L project to improve the ephemerides of all the inner planets.The Mariner tracking data will Le combined with radar and

optical telescope data to achieve this result.The principal investigator f o r this experiment is John D.

Anderson of the Jet Propulsion Laboratory, and the co-inves-tigator is Warren L. Martln, also of JPL,

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The Mariner Mars 1969 fly-by spassembled and tested by the Jet PropPasadena, Calif. fndustrlal contractors prdesign and fabrication of the subsystwere provided by hundreds of manufact

Each Mariner weighs 910 poundsthe scan platfom to the top of thesolar panels deployed, the s acecraftagonal structure measures 5I&3 inchein depth,

magnesium framework with seven eleet onjtcs c o ~ p ~ r t ~ e ~ t s .hecompartments themselves provide s t ~ ~ c t ~ ~ a lupport to the

spacecraft.Four solar panels, each 84 inches lo and 354 inches

wide, are attached t o the top or su~ward de of the octagon,Each panel has a solar cell area of 20.7 square feet, or atotal cell surface of approximately 83 square feetspacecraft. Two sets of attitude control Jets conssix jets each, which s-t;abilize he tjpacecraft on three axes,are mounted at the tips of the four panels,

nd 18 inches

Mariner's basic structure i& a 3 ~ m p o u n ~ight~~idedorged

Metal bottles containing the nitrogen.gas supply forMariner's dual attitude control gas tern

pellant tank for the liquid-fuel midco~rse $ne is supportedby a cantilever arrangement inside the octagonal cavity, withthe rocket nozzle protruding through one of the eight; sides Qf

the spacecraft,

the systems are mounted on the top r of

The high-gain antenna is attached to the spacecraft by a

superstructure atop the octagon. Its num honeycomb dishreflector is circular, 442 inches in h r, and is parabolicin cross-section. The antenna feed is s orted at the focusof the parabola by a fiberglass truss. e reflector, whichweighs only 3.3 pounds, is in a fixed position so that Earthenters the antenna beam about l g o days after launch and remainsin the effective beam until more than one month beyond Mars.

The low-gain omni-directional antenna I s mounted at thetop of a circular aluminum tube, four inches in diameter andextending vertically 88 inches from the top of the octagonalstructure. The tube acts as a waveguide for the antenna. Acone-shaped thermal control flux monitor is mounted at the topof the antenna mast where it remains in sunlight with a minimumview of other parts of the spacecraft which could reflect lightinto its detector.

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The Canopus s ta r tracker assembly is located on the upperring structure of the octagon for a clear field of view be-tween two solar panels. Two primary Sun sensors are mountedon pedestals atop the octagon. Four secondary Sun sensorsare attached directly to the lower r i n g structure.

following: Bay 1, power conversion equipment, battery chargerand squib firing assembly; Bay 2, midcourse maneuver rocketengine; Bay 3, central computer and sequencer and attitudecontrol subsystem; Bay 4, flight telemetry and command sub-systems; Bay 5, tape recorders; Bay 6, radio receiver andtransmitters; Bay 7, science instment electronics and dataautomation subsystem; Bay 8, power booster regulators and space-craft battery.

The eight compartments girdling the spacecraft house the

Six of the electronics compartments are temperature con-trolled by ligntwelght louver assemblies on the outer surfaces.The octagon's interior is insulated by multi-layer fabricthermal shields at both top and bottom of the structure.

The Mariners will carry science instrumentation for fourplanetary experiments, Two additional experiments, spacecraftoccultation by Mars and celestial mechanics, require only thespacecraft communications system as the source of their data.

Two television cameras, an infrared spectrometer, ultra-violet spectrometer, infrared radiometer and two planet sensorsare mounted on a motor-driven two-degree-of-freedom scan plat-form on the bottom or shaded side of the octagon. Total ro-

tating weight of the platform mechanism and its science instru-ment payload is 167 pounds.



Th2 Mariner power subsystem sup pl ie s el ec tr ,c al powert o t h e spacecraft , switches ana con tro ls the power and pro-vides an accurate t iming source.

P r i m a r y power source i s an arrangement G f 17,472photovo l ta ic so la r c e l l s mountea on fou r panels which w i l lface the Sun during most of t h e f l i g h t to Mars. The cel ls ,covering 83 square f e e t , w i l l c o l l e c t energy and convertit i n t o e l e c t r i c a l power.

A rechargeable s i lver-zinc b a t t e r y w i l l providespacecra f t power during launch, midcourse and whenever

the panel s a re turned away f r c l m t h e Sun. The ba t t e ry w i l lbe k e p t i n a s t a t e of f u l l charge and w i l l be a va i l a b l edur ing planet encounter as an emergency power backup source.

Two power regulators will provide redundancy, I n theevent of a f a i l u r e i n one, i t w i l l be removed automaticallyfrom t h e l i ne and t h e second w i l l be switched i n to assumet h e f u l l load,

The so la r pane ls w i l l b e fo lded in a n ea r v e r t l c a lposi t ion above th e body of t h e spacec ra ft dur ing l am ch andw i l l be deployed a f t e r separa t ion f rom t h e launch vehicle ,Each panel weighs 27 pounds, inc luding th e weight of 4,368

s o la r c e l l s (2x2 cm. N/P) and protect ive g la ss f i l t e r s thatreduce the amount of so la r ra di at fo n absorbed without in t e r -f e r i n g w i t h the energy conversion. The cel l modules are sup-por ted by l i g h t w e i g h t p a n e l s t r u c t u r e s made of ’chin-gaugealuminum.

Nominal power from t h e panels i s expected t o be 800

watts a t maximum power voltage f o r c ru i s e c ond it ions i n s pac enear E a r t h , T h i s pow@? ca pa bi l i ty decr eases t o 449 watts a tt h e Mars di s t ance if there i s no d egradat ion bmause of solarf l a r e s . Maxfrnum power aemand i s expscted to be 388 watts a tenc ognter .

The b a t t e r y i s a seal-?d u n i t cont;aining 18 s i l ve r -z incc e l l s . Its minimum sapaclty ranges from 1,200-watt hoursa t launch t o about; 90Q-watt hours at pl an et encounte r. Loadrequirements on t h e ba t t e ry may vary between zero amps and9.5 w i t h b a t t e r y vol tages expec ted t o vary between 25.8 and33.3 v o l t s , The bat tery weighs 31 pounds.

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The bat tery w i l l be capable of de l ive r ing i t s requiredcapac i ty and meeting all e l ec t r i c a l r equ i rement s wi th in anope ra t iona l temperature range of 58 degrees t o 90 degrees F.

A t temperatures outside t h i s range, i t w i l l s t i l l func t iona l though i t s c a pa b i l i t y w i l l be reduced.

To ensure maximum r e l i a b i l t t y , t h e power subsystemwas designed t o l i m i t the need for b a t t e r y power a f t e r i n i t i a lSun ac qu is it io n. Except du rin g maneuvers, th e ba t t e ry w i l lremain i d l e and f u l l y charged.

Under normal f l i g h t condi t ions , t h e pr imary powerboos te r - regula tor w i l l handle a l l spacecraf t loads . A secondre gu l a t o r w i l l support power l o a d s on a stand-by basis.Should an out-of- tolerance vol tage condi t ion ex is t in t h e mainregula tor , t h e stand'-by regulator w i l l take i t s place on the

l i n e .

Primary form of power distributed t o othe r spacec ra f tsystems i s 2,400-cycles-per-second sq ua re wave. The gyrosp in motors us e 400 cps three-phase cur ren t , and th e i n f r a r e dspectrometer and scan motor are suppl ied w i t h 400 cps s ingle-phase current . The t r a ns m i t t e r a m p l i f i e r tube, b a t t e r y chargerand temperature contr*ol heaters use unregula ted de power fromth e s o l a r pane ls o r t h e ba t t e ry .

A c r y s t a l o s c i l l a t o r i n th e main power inverterc on t ro l s t h e f requency t o wi th in 0.01 p e r cent , assur ingothe r spaces ra f t systems of a r e l i a b l e , accurate frequencyon t h e i r power line. A backup c r ys t a l o s c i l l a t o r i s locatedi n the stand-by in v er te r. The spa cec raf t Ce ntr al Computer andSequencer (CC&S) us e s th e os c i l l a t o r f re quency as a t imingsource.

Telemetry measurements have been s el ec te d t o pro videt h e necessary informat ion for th e management of spacecraftpower l o ad s by ground command i f necessary.

equipment zre housed i n two adja cent el ec tr on ic s compartmentson Mariner 's octagonal base.

The bat te ry , regu la tor s and power di s t r i bu t io n

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Central Computer and Sequencer

Mariner i s designed t o op erate throughout i t s bas icmission without th e need of ground commands--with the s i ng l e

except ion of th e tr aj ec to ry cor rec t io n maneuver. This auto-matic c a pa b i l i t y i s made possible by t h e on-board commandfunct ion of t h e c e n t r a l computer and sequencer (CC&S). C r l t i c a levents, however, are backed up by th e ground command c a p a b i l i t y .

The CC&S performs t h e tim ing , sequencing and computationsfor other subsystems aboard the spacecraft . It i n i t i a t e sspacecraft events i n fou r d i f fe re nt mission sequences-- launch,cruise, maneuver, and encounter.

Timing and sequencing are programmed i n t o the CC&Sp r i o r t o launch but can be modified anytime during t h ef l i g h t by command from th e ground.

The launch sequence includes th e deployment of s o l a rpanels and t h e t u rn ing on of th e Canopus sensor and a t t i t u d econt rol sys tem t o es tab l i sh s pa ce c ra f t s t a b i l i z a t i o n and s o l a renergy conversion for t h e long cru i se ,

The crzlise sequence controls those spacecraft eventst h a t occur a f t e r the launch sequence and prior t o encounterw i t h a si ng le exception-the midcourse t r a j ec to ry corr ect ion .CC&S commands d uring t h e cruise sequence switch the Spacecrafttelemetry t ransmission t o a h ighe r o r lower b i t ra te ; unla tchthe scan platform; switch t h e t r a ns m i t t e r t o e i t h e r t h e h igh-ga in o r low-gain antenna; and se t t h e Canopus sensor a t var iouscone ang l es r e l a t i ve t o t h e predicted encounter t i m e .

The maneuver sequence controls t h e events necessary t operform t h e midcourse t r a j e c t o r y co rr ec tio n. Coded commands,generated a t JPL a f t e r ana ly s i s of t r ack ing data, are radioedfrom Ear th and s tored i n th e CC&S pr io r t o i n i t i a t i o n of themaneuver. They t e l l t h e spacecraft how f a r and i n which di rec -t i o n t o t u r n on i t s p i t c h and r o l l a x e sa n d how long t h e m i d -

course rocket engine must f i r e . Under normal circumstances,th e programmable computer portion and th e f ixed sequencer port ionof the CC&S operate i n tandem, pro vid ing redundancy. I f t h e r ei s disagreement on any maneuver event, w i t h th e except ion of

the command t o t u r n o f f the ro ck et eng ine, th e maneuver i saborted and t h e s pa c e c ra f t r e t u rns t o the c ru i se condit i on .A maneuver also can be performed by e i t h e r por t ion of the CC&Salone,

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The encounter sequence begins w i t h th e switchingof th e s pa c e c ra f t t r a ns m i t t e r t o high power p r io r t o t h ef i r s t f a r encounter TV p i c t u r e and continues through t h e mdof t h e data stor age playback phase of t h e mission. CC&S

commands include those controlling th e motion of th e two-axissc ience plat form; s ta r t i n g and s topping recording on bothtape recorders; switching t h e r a d i o t r ansmi t te r t o h i gh power;s e l e c t i ng the te lemetry data rate; and cont rol l ing t h e p l ay -back of recorded data. To change t h e programmed encountersequence, CC&S commands may be preempted by d i r e c t commandsfrom the ground.

The CC&S weighs about 26 pounds and i s housed wi tht h e a t t i t u d e control system's e l ec t ron ic s i n one of theeig ht compartments g i r d l i ng Marin er 's octagonal base.



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Temperature Control

If dependent s o l e l y upon direct sunlight for heat, anobject in space would be approximately 125 degrees F. colder

at Mars than at Earth.

For a spacecraft traveling to Mars-, away from Earth andfrom the Sun, the primary temperature control problem, then,is maintaining temperatures within allowable limits despitethe decreasing solar intensity as the mission progresses. Inairless space, the temperature differential between the sunlitside and the shaded side of an object can be several hundreddegrees.

Heating by direct sunlight on the Mariner spacecraft I sminimized by the use of a thermal shield on its Sun side. Theside away from the Sun is covered with a thermal shield to pre-

vent rapid loss of heat to the cold of space,

The top of Mariner's basic octagon is insulated from theSun by a multi-layered shield of aluminized Teflon mounted tothe high-gain antenna support structure.by a similar shield, or space 'blanket," to retain heat generatedby power consumption within the spacecraft.

The bottom is enclosed

Temperature control of six of the electronics compartmentsis provided by polished metal louvers actuated by coiled bi-metallic strips. The strips act as spiral-wound springs thatexpand and contract as they heat and cool. This mechanicalaction, which opens and closes the louvers, is calibrated toprovide an operating range from f u l l y closed at 55 degrees F.to fully open at 90 degrees F.22 horizontal louvers driven in pairs by 11 actuators. Eachpair operates independently on its own locab temperature de-termined by internal power dissipation,

The science platform and its array of instruments at thebottom of the octagon is covered by a third thermal blanketfitted also wlth a louver assembly, The platform is designedto be thermally isolated from the main equipment octagon by 8

plastic collar on the attaching support tube, Temperature con-trol is achieved by electrical dissipation in heaters and in

the instruments themselves,

A louver assembly consists of

Electric heaters are located wkthin the science platformet and in two of the elec$ronics bays to provide additional

ng certain portions of the mission.



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Paint patterns and polished metal surfaces are used onthe Mariner for passive control of temperatures outside of theprotected octagon and covered science platform. These surfacescontrol both the amount of heat dissipated into space and the

amount of solar heat absorbed or reflected away. The patternswere determined frm testing a Temperature Control Model (TCM)of the spacecraft in a space simulation chamber at JPL and fromthe application of actual mission data acquired during the 1964-65 MarAner IV mission to Mars.

The high-gain antenna dish, which i s dependent upon theSun for its surface heat, is painted green to keep it at nearroom temperature during planet encounter but within its upperthermal limit earlier in the mission,

A tempera~ure ontrol f lux monitor ( T C ~ ill perfam anengineering experiment by comparing actual f11 ht thermal per-formance with that determined by space-simulated t e s t s . Thedata is expected to provide a standard for future s imulabrtesting and spacecraft design. The cone-shaped TCFM is mountedat the top OS the om$-directional antenna mast where it remainsin sunlight with no view of the spacecraft which could reflectlight into its detector.surement o f the solar Zntensity to within plus or minus 1.5percent

The TCFM will make an absolute mea-



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Midcourse Propulsion

Mariner's midcourse rocket engine used a liquid mono-propellant and is capable of:firing twice during the Marsmission.tions to the spacecraft. The engine uses anhydrous hydrazineas the propellant and a spontaneous catalyst for decompositionof the hydrazine.

Ita function is to provide small trajectory correc-

The rocket nozzle protrudes from one of the eight sides of

The engine's direction of thrust is nearly parallel toMariner's octagonal base below and between two of the solarpanels,the panels, hence perpendicular to the longitudinal or roll axisof the spacecraft.

Hydrazine is contained in a ribber bladder enclosed in a

spherical pressure vessel. The propellant is forced into thecombustion chamber by nitrogen gas compressing the bladder. De-composition of the hydrazine, maintained by the catalyst storedin the chamber, causes the rapid expansion of hot gases in theengine.

Firing of the engine is controlled by the Central Computerand Sequencer, which receives the time, direction and durationof required thrust through the ground-to-spacecraft communica-tions link. At the command signal from the CC&S, explosively-actuated valves allow pressure-regulated nitrogen gas to enterthe propellant tank and open the propellant line to the engine,For termination of thrust, the CC&S timer actuates another set

of valves which stops propellant flow and tank pressurization.During rocket engine firing, spacecraft attitude is maintainedby autopilot-controlled jet vanes positioned in the rocketnozzle to deflect the engine exhaust stream,

Restart capability and redundancy are provided by secondsets of explosive start and shutoff valves.

Either of the two Mariners may perform one or two midcoursemaneuvers. It is anticipated, because of several trajectoryfactors, that the f i r s t spacecraft launched probably will requirea second maneuver while the second Mariner will not.

First maneuver for each spacecraft is expected to occurwithin five to 15 days following each Launch. A second maneuverwould be condueted about one to four months after launch.



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The midcourse propulsion system can burn for as littleas 100 milliseconds and can alter velocity i n any directionfrom less than mile-per-hour to 134 miles-per-hour. Max-imum burn time is 102 seconds. Thrust is continuous at about51.3 pounds.

Launch weight of t h e midcourse propulsion system, in-cluding the gas pressurant and 214 pounds of propellant, is47 pounds.

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Communications

Two-way communications with the Mariners will beaccomplished with a radio link between Earth tracking sta-tions and a dual transmitter-single receiver radio systemaboard each spacecraft,

The on-board communications system also includes a tele-metry subsystem, command subsystem, data storage subsystem andhigh and low-gain antennas,

The spacecraft S-band receiver w i l l operate continuouslyduring the mission at about 2115 megacycles.in the t w o Mariners will operate at slightly different fre-quencies. Similarly, no two transmitters will operate at ex-actly the same frequency.)

one antenna -- the low-gain omnl-directional antenna. It re-ceives uplink command and ranging signals from ground stationssf the Deep Space Network.

(The receivers

The receiver will be used with only

To provide the standard Doppler tracking data, the radiosignal transmltted from Earth is received at the spacecraft,changed in frequency by a known ratio and re-transmitted toEarth. In addition, a JPL-developed ranging technique wingan automatic coded signal provides range measurement8 with anaccuracy of a few yards at the Mars-Earth dlstance. The rangingfunctionmay be commanded on and off by ground command.

When no uplink signal is being received by Mariner, the

transmitted frequency of about 2195 megacycles opiginatas inthe spacecraft transmitter, The tranesmitter consists of tworedundant exciters and two redundant radio frequency poweramplifiers of which any combination is poasible. Only oneexciter-amplifier comb1na;tion w i l l operate at any one tlme.Selection of the combination will be by on-board failure de-tection logic with ground command backup.

Both amplifiers on each spacecraft employ traveling wavetubes and are capable of operating at 10 watts or 20 wattsoutput and the signal may be transmitted through either thehigh-gain or low-galn antenna. Transmission via the high-gainantenna will be required durlng the encounter and playback

phases of the mission.

The low-gain antenna provides essentially uniform coveragein the forward hemisphere of the spacecraft. The high-gainantenna includes a 40-inch-diameter parabolic reflector whichprovides a highly directional beam for the downlLnk radio signal.Switchover of the spacecraft transmitter to the hlgh-gain an-kenna and back to the low-gain, if desired, may be commandedfrom Earth.

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All communicationu between the Mariners and Earth willbe in digital fom. Command signals transmitted to the space-craft will be decoded -- translated from a binary form into

electrical impulse8 -- in the command subayatem and routed totheir proper destination,

Three types of commands are transmitted to the spacecraft:a direct command (DC) resultE in the closure of 8 switch in oneof' the spacecraft subsystems; a coded command (CC) provides in-formation to the central computer and sequencer f o r the mid-course maneuver o r to update the CC&S program; a quantitative

command (QC) is used to step the man platform a variable num-ber of increments, There are 53 possible DC's which back upa l l critical automatic spacecraft functlons, choose redundantelements, initiate the midcourse maneuver and perform otherfunctions

Data telemetered f r o m the spacecraft will consist ofengineering and sclence measurements prepared f o r transmissionby the telemetry subsystem, the data automation subsystem ( real-time TV and science) and data storage subsystem (recorded scienceincluding TV). The encoded information w i l l indicate voltages,pressures, taperaturea and other values measured by the apace-c r a f t telemetry sensor8 and science instruments.

There arc three data channels: the engineering channelwhich operates throughout the flight; the science channel em-ployed during the encounter and playback phases of the mission;

and the high-rate alternate science channel,

Mariner can transmit information to Earth at five differentrates:33 1/3 bps at any time; on the science channel at 66 2/3 bpsduring encounter and 270 bps during data storage playback; andon the high-rate science channel at 16,200 bps,

The high-rate channel may be used during the encounterportion of the mission to transmit, in realtime, data beingplaced on the digital tape recorder -- one of two on-boardtape recorders which make up the data storage subsystem, IXlr-ing playback, television data on the analog tape recorder may

be fed directly to the telemetry subsystem through an knalog-to-digital converter and transmitted at the 16,200 bps rate.

on the engineering channel at 8 1/3 bits-per-second and

Certain conditions must exist in order to utilize thehigh-rate Channel. These include the availability of the 210-foot diameter antenna at the Goldstone Space ComunicatiorisComplex of the Deep Space Network for receiving,

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LOW-GAIN ANTENNA-

-HIGH-GAIN ANTENNA

CANOPUS SENSOR

SOLAR PANELS

LPROPULSIONUBSYSTEM

NOZZLE

-7-GAIN ANTENNA

ATTITUDE CONTRQL

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SCAN

WOE ANGLE TELEVISION

I R RADIOMETER

U V SPECTROMETER IR SPECTROMEER

P L A T F ~ I(ERU*L e L m w DELETED NARROW ANGLE TELEVISION

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INFRARE S

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INFRARE RADIOME

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During playback of th e analog tape recorder, t h i s datamay be recorded on th e d i g i t a l tape recorder and played backa t 270 bps using t h e standard 85-foo t-dimeter antennas,

Approximately 90 eng ineer ing measurements are obtainedby transducers throughout t h e spacec ra f t t o m a k e up t h e engi-neering data , The engineer-tng samples are taken continuouslyand can b e t ransmi t ted along w i t h sclence regardllesa of thescience channel or r a t e i n u se,

A l l video data received from th e televierion cmeraa i srecorded on t h e analog tape recorder , It can be erased i nf l i g h t , permi t t ing t h e recording of' a se t of TV plc turea ,playing it back and erasing; the tape and than recording anothers e t

Tho d i g i t a l tape recorde r w i l l be fe d by t h e data auto-mation system which formats a l l t h e measurements from th einf rar ed spectrometer , in fr ar ed radiometer and t h e u l t r a v i o l e tspectrometer 88 w e l l as se l ec t ed data from t h e t e l e v i s i oncameras. The d i g i t a l recorder needs no erasing.

Tota l capac i ty of t h e two recorders i s equiva l en t t o ap-proximately 195 mi l l ion b i t s of i n fom a t i on .

Att l tude Control

S t a b i l i z a t i o n of the spacecraf t dur ing the cruise and

planet encounter port ions of t h e Mariner Mars mission i s pro-vided by a aystern of 12 cold gas j e t s mounted a t t h e outer endsof t h e four s o l a r pa ne ls , The j e t s are linked by 1ogic . c i r -c u i t r y t o three gyroscopes (one gyro f o r each of t h e spacecraf t ' sth ree axes), t o th e Canopus senp1or and t h e primary and secondarySun sensors.

The gas system i s div ided in to two s e t s of six Je t s , eachse t complete w i t h i t a own gas supply, regu la tors , l l ne s andvalves so that a leak o r v a l v e f a i l u r e w i l l not deplete th e gasand jeopardize the mission.bo t t l e con ta in ing 23 pounds of ni t rogen gas pressur i zed a t2,500 pounds per-square-inch.

E i t h e r system can support th e e n t i r e f l i g h t i n th e event ofa f a i lu r e i n th e other .

Each system 18 f ed by a t l tanlum

Normally, both sets w i l l opera te dur ing t h e misjsion.

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The primary Sun sensors are mounted on the sunlit sideof the spacecraft and the secondary sensors on the shadowedside. The sensors are light-sensitive diodes which informthe attitude control system when they see the Sun. The atti-tude control system responds to these signals by turning thespacecraft and pointing the solar panels toward the Sun forstabilization on two axes and for conversion of solar energyto spacecraft power,priate jet nozzle, imparting a reaction to the spacecraft tocorrect its angular position.

Nitrogen.gas escapes through the appro-

The star Canopuz39 one of the bri htest in the gala willprovide a second celestial reference 7along with the Sun7 ponwhich to base the midcourse maneuver. The Canopus sensor willactivate the gas jets to roll the spacecraft about the already-fixed longitudinal or roll axis until it is "locked" in cruiseposition, Canopus acquisition occurs when the light intensityin the field of view of the sensor matches the intensity anti-

cipated for the star Canopus. Brightness of the SensIor's tar-get star will be telemetered to the ground to verify the correctstar has been acquired,

The Canopus sensor design incorporates the capability ofpreventing recurring loss of roll reference caused by brightparticles in the sensor field of view, The sensor logic willallow a bright fast-moving particle to drift through the fieldof view without causing the Spacecraft to initiate a new rollsearch for the star.

Periodically durlng the flight, the Canopus sensor willbe updated to compensate for the changing angular relationship

between the spacecraft and the star. The sensor's field ofview or "look angle" will be changed electronically to followCanopus throughout the mission. The update, which will occurfour times at approximately three-week to four-week intervals,will be commanded at predetermined times by the on-board Cen-tral Computer and Sequencer with ground command backup. Afifth Canopus tracker update will occur about 30 days after thespacecraft flies by Mars.

Upon receipt of commands from the CC&S, the attitude con-trol system orients the spacecraft to align the thrust axis ofthe midcourse motor in the direction required for the trajec-tory correction maneuver.

During firing of the mldcourse motor, stabilization ofthe spacecraft will be effected by the use of four mdder-likejet vanes mounted in the downstream end of the engine nozzle.The Harinerrs autopilot controls spacecraft attitude duringengine firing by using the gyros to sense motion about thespacecraft's three axes for positioning the Jet vanes.

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Each vane has its o m separate control system and, becausethe midcourse motor is not mounted along aqy of the three axes,each is activated by a mixture of signals from the three gyros.Constant adjustment of the angles of the jet vanes ensures thatthe motor thrust direction remains through the spacecraft's cen-ter of gravity.

Scan Control

Mariner's science instruments are mounted on a scan plat-form which can be rotated about two axes to point the instru-ments toward Mars during the spacecraft's approach and passageof the planet.of the spacecraft.

The platform is located below the octagonal base

The instruments are the ultraviolet spectrometer, infraredradiometer, infrared spectrometer, wide-angle television camera

and narrow-angle television camera. A l s o located on the plat-form are three planet sensors and two high pressure spheres con-tainrng hydrogen and nitrogen for cooling a detector in the IRspectrometer.

The scan control system allows multiple pointing directionsof the instruments as the encounter phase of the mission progresses.The platform's two axes of rotation are described as the clockangle motion about the axis of the tube extending vertically fromthe octagon and cone angle motion about an axis which ishorizontal.

The I67-pound platform is motor driven and moves 215 degrees

in the clock and 64 degrees in cone,

As Mariner approaches Mars (about three days before closestapproach), one of the scan control system's three optical sensingdevices 0- the far encounter planet sensor -- tracks the centerof brightness of Mars enabling the narrow-angle TV camepa to be-gin a series of full-disk pictures of the planet.

The other planet sensors, called narrow-angle Mars gates,initiate several science events during the near encounter portionof the mission. One of the sensors provides a signal which acti-vates the cyrogenic cooldown of the detector in the IR spectro-meter. The second provides the information initiating the re-

cording of instrument data.

At about 12 hours before Mariner's closest approach toMars, the scan platform twists on both axes to a pointing angleset before launch or updated during the flight by ground command.

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Data Automation Subsystem

The f i v e s c i e n t i f i c i ns tr um en ts on t he s pa c ec ra ft arecont rol led and synchronized by t h e Data Automation Subsystem(DAS) and the data from t h e ins t ruments i s converted by t h eDAS i n t o a s u i t a b l e d i g i t a l form f o r t r a n s m i t t al t o Earth.

The experiments controlled by t h e DAS are t e l ev i s ion ,inf ra r ed radiometer , inf ra r ed spec trometer and u l t r a v i o l e tspectrometer. The S-band occultat ion experiment and the celea-t i a l mechanics experiment do not require special equipmentaboard the spacecraf t and are not con t ro l l ed by the DAS.

During encounter the DAS accumulate s va r i ed s c i en t i f i cdata, reduces the data to a common digital fsm and eomon

rate md then feeds the data to t h e d i g i t a l tape recorde r o rt o t he r a d i o t r a ns m i t t er telemetry channel a t prope r i n t e rva l s .

The DAS is composed of three units; l og i c c i r c u i t r y ,s pa c e c ra f t i n t e r f a c e c i r c u i t r y and power csnvertm?.weight i s about 14 pounds and power ~~~~~~~t~~~ is 18 watts.

The t o t a l

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LAUNCH VEHICLE

The launches of Mariners F and G m a

the Atlas-Centaur launch veh icl e ( A C - 1 9 ,

Mariner program. Atlas-Agena launch ve hithe previous Mariner missions. U s e of the A tvehic le w i t h i t s gr ea te r payload c apa bil i ty al lows for rowthof the spacecraft ,pounds compared with 575 pounds f o r Mariner IV t o Mars i n 1964and 542 pounds f o r Mariner V to Venus i n 1967.

Mariners F SC G weigh approximately %48

The launches of Mariners F and G mark the f i r s t use ofAtlas-Centaur vehi cles f o r int erp lan eta ry missions. In t h epast , Centaur has been used t o successfully launch sevenSurveyor spacecraft to t h e Moon-and t o place an Orbit ingAstronomical Observatory in Ear th o rb i t . Centaur, which wasdeveloped under the direction of the Lewis Research Center wasthe f i r s t U.S. rocket t o use the high energy liquid oxygen,liquid hydrogen propellant combination,

AC-19 and 20 w i l l use a di re c t ascent s i ngle burn tech-nique f or placing t h e spacecraft on th e proper t ra j ec tor y toMars. I n t h i s mode the Centaur engines w i l l be required toignite only once in space.

To reach t h e proper t ra je ct or y the launch vehicle w i l lhave t o make either one or two dogleg maneuvers, depending ont h e day of launch.

A C - 1 9 and 20 cons is t of an Atlas SLV-3C booster combinedw i t h a Centaur second stage. The two sta ges a r e 10 f e e t i ndiameter and are connected w i t h an int ers tag e adapter . BothAtlas and Centaur stages re l y on in te rna l p ressur izat ion fo rs t r u c t u r a l i n t e g r i t y.

The A t l a s booster develops 395,000 pounds of thmst a tl i f to f f , u s ing two 168,000 thrust booster engines, one 58,000thrust sustained engine and two vernier engines developing 670pounds thrust each.

The Atlas booster develops 395,000 pounds of t h r u s t a tl i f t o f f , u s i n g two 168,000 pound th ru s t bo os te r engines, one

58,000-pound t h r u s t su st ai ne r engine and two ve rn ie r engin esdeveloping 670 pounds t h r u s t each.

Centaur carr ies insulat ion panels and a nose f a i ri n g whichare je t t i soned a f t e r the vehicle leaves t h e E a r t h ' s atmosphere.The i ns ul at io n panels weighing about 1,200 pounds, surround t h esecond s tanks to prevent t h e hea t of a i r f r i c t i o nfrom cau bo il -o ff of l iq u id hydrogen durin g f l i g h tthrough ere. The nose f ai r in g pr ot ec ts the payload.

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The configuration f o r the A t l a s and Centaur vehicles areb a s i c a l ly th e same as they were f o r the Surveyor f l i g h t s .Certain improvements have been Introduced since th e l a s tSurveyor f l i g h t s Including the use of e x p l i c i t guidanceequations rather than implicit ones, to provide addit ionalopera t ional f l e x l b i l i t y .

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-4 1-

Launch Vehicle Characteristics

+Li f to f f weight including spacecraft :

L i f to f f height :

Launch Complexes:

Launch Azimuth Sector

SLV-?C Booster

**Weight: 284,431 lbs.

Height:

Thrust:

75 fee t ( inc ludingin t e r s a g e a d ap ter

395,000 lbs. (sea

l e v e l )

Prope lla nts : Liquid oxygen and

Propulsion: MA-5system (2-

R P - 1

1 6 8 , O O O - l b . - t h ~ ~ ~ tengines, 1-58,000-lb, sustainer engineand 2-670-lb.-thmstvernier engines, )

Velocity:

Guidance:

5,766 mph a t BECO

8,372 mph a t SECO

Pre -programed aut o-p i l o t through BECO,Switch t o Centauriner t ia l guidance forsustainer phase.

* Measured a t %wo inches of r i se**Weights a r e based on AC-19 configuration,

s l i g h t l y .

323,105 pounds

113 fee t

3 6 ~c B

87 - 108 degrees

Centaur Stage

37,826 lbs.

48 f e e t ( w i t h payloadfa r i n g

30,000 lbs. (vacuum)

Liquid hydrogen andl i qu id oxygen

Two 15,000-pound-thrustRL-10 e n g k e s . 14 s m a l lhydrogen peroxideth rus te r s .

22,392 mph a t space-

c ra f t sepa ra t ion ,

In e r t i a l guidance,

AC-20 v a r i e s j u s t

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-4 4 -

Flight Sequence

F l i g h t sequences of the AC-19 and AC-20 rocket vehicles

are basically the same w i t h times varying only a second or twoi n some ca se s as noted on th e accompanying ch ar t, For p r ac t ic a lpurposes th e following sequence de sc ri pt io n i s the one for A C -19a t th e opening of the window Feb. 24.

Atlas Phase

After liftoff, AC-19 w i l l r i s e v e r ti c a l ly f o r about 15seconds before beginning i t s pi tc h program. St ar ti ng a t twoseconds after l i f t o f f and continuing to T+l5 seconds, thevehic le w i l l roll to t h e desired f l i g h t azimuth of between 87and 108 degre es. The azimuth va rf es according t o the day o flaunch.

After 152 seconds o f f l i g h t , t h e booster engines ape shutdown (BECO) and jettisoned. BEGO occurs when an accelerationof 5.7 g t s i s sensed by accelerometers on the Centaur and th es i g n a l i s issued by th e Centaur guidance system, The bo os te rpackage i s je t t i soned 3.1 seconds after BECO, The Atlas sus-tainer engine continues t o burn for approximately anotherminute and 4 1 seconds propell ing the vehicle t o an al t i t ud e ofabout 83 miles, attainrtng a speed of 8,300 mph. Susta inerengine cutoff (SECO) occurs a t prop ellan t depl etion . Centaurinsula t ion panels and nose f a i r in g a re je t t i soned p r i o r t o SECO.

The Atlas and Centaur st ag es a r e then separate d, Anexplosive shaped charge sl ices through the interstage adapter .Retro-rockets mounted on the Atlas slow th e spent stage.

Dogleg Maneuver

Although the launch azimuth for Feb. 24 i s 108 degrees,because of a dogleg maneuver t o th e south, the equivalent f l i g h tazimuth is approximately 130 degrees a t window opening on Feb.24, Safety consideration s di ct at e the difference between thetwo headings t o avoid t h e Lesser A n t i l l e s area during reentryof the vehicle , i f d e s t ru c t i s necessary f o r range sa fe ty pur-poses.

I n order to reach the proper equivalent azimuth on Feb. 24it i s necessary for th e vehicle to perform two dogleg maneuverst o th e south , One begins BECO p lus 8 seconds and the secondbegins a t Centaur main engine s t a r t p lus 4 seconds.

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-4 5-

A s the requi red equ ivale nt f l i g h t azimuth changes f rom130 t o ll5 degrees the amount of th e dogleg maneuver decreases.Between 115 and 108 degrees, only one dogleg maneuver i s

necessary. Between 108 and 87 degrees a d i r e c t p la n ar t ra-j e c t o r y i s possible and so no e x t r a maneuver is needed.

Centaur Phase

A t fou r minutes, 24 seconds into t h e f l i g h t , t h e Centaur 'stwo RL-10 eng ines ign i t e ( P I S ) f o r a planned seven min ute, 15second burn. T h i s w i l l place Centaur and th e spacecraf t on ani n t e r p l a n e t a r y t r a j e c t o r y a t a speed of about 24,768 mph.MECO, th e Centaur sta ge and sp ac ecr af t are r eo r ien ted w i t h t h eCentau r a t t i tude con t ro l thrus ters t o p lace the spacec ra f t onth e p r o p e r t r a j e c t o r y a f t e r separa t ion .

After

Separat ion

Separat ion of t he Mariner space cra f t i s achieved by f ir ingexp los ive bo l t s on a V-shaped metal band holding t h e spacec ra f tt o t h e adapter. Compressed springs then push the spacecraftaway from t h e Centaur vehicle a t a rate of 2 .1 feet-per-second,

Retro Maneuver

Four and a ha l f minutes a f t e r spacec ra f t sepa ra t ion , t h eC e n t a u r s t a g e a t t i t u d e c o n t r o l t h r u s t e r s are used t o reor ient ;the vehic le . The remaining l iquid and gaseous propellants arethen vented from a spec ia l tube in t h e base of the Centaur

rocket .

The r e t r o maneuver in su res t h a t there i s n o p o s s i b i l i t y ofc r a sh i n g i n t o the plan et and thereby v io la t ing the Mar tianq u a r a n t i n e r e s t r a i n t . The spent Centaur stage w i l l go i n t o as o l a r o r b i t .

Launch Window

The Mariner F launch window opens a t approximately 7:54 p.m.EST on Feb, 24, and t h e Mariner G window a t about 4:58 p.m. ESTon March 24,ear l i e r for t h e f i r s t f e w days and afterwards changes more rap-i d l y , Each launch window i s r es t r i c t ed t o one hour.

In case of delays th e window opens a f e w minutes

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-46-

TRACKING AND DATA SYSTEM

The Je t Propuls ion Laboratory has been assigned byNASA the r e s p o n s i b i l i t y f o r e s t a b li s h i n g t h e ground-basedf a c i l i t i e s f o r s u p p o r t i n g t h e Mariner Mars ' 6 9 p r o j e c t t r a c k in g

and data acq u i s i t i o n requ irement s. These requirements coverlaunch vehic le and spacecraft t e lemet ry ; met r ic data involv ingthe t r a c k i n g of the launch vehicle by C-band radars and t h e M

Mariner at S-band frequencies; sending of commands t o t h espacecraft; and real-time tr an sm iss io n of some of these datat o th e Space F l ig ht Opera tions F ac i l i t y (SFOF) a t J P L i nPasadena, C a l i f .

The near-Ear th t r a j ec to ry requi rements aremet bys e l e c t e d f a c i l i t i e s of th e A i r Force Eas te rn T e s t Range,in cl ud in g communications s h i p s on t h e At lan t i c , and t h e GoddardSpace Flight Center managed networks, Tracking and communicationw i t h t h e s p a c e cr a f t from i n j e c t i o n i n t o t h e t r a n s f e r o r b i t t o

Mars u n t i l t h e end of the mission w i l l be carr ied out by t h eDeep Space Network ( D S N ) ,

The DSN consists of nine permanent space communicationss t a t i o n s on f o u r c o n t in e n t s ; a sp ace cr af t mon%t;oring s t a t io na t Cape Kennedy; t h e Space F l ig h t Ope ra t ions F a c i l i t y a t JPL;and uses a ground communications system linking a l l l o c a t i o n s .

Permanent s ta t ions, placed s t r a t e g i c a l l y around t h eEar th , i n c l u d e f o u r s i t e s a t th e Goldstone Space CommunicationsComplex i n t h e Mojave Desert i n C a l i f o r n i a ; two s r te s i nA u s t r a l i a , a t Woomera' and a t Tidbinbi l la near Canberra ; t h e

Robledo and Cebreros s ta t ions near Madrid, Spain; and a s t a t i o n

a t Johannesburg, South Af ri ca. Each i s equipped w i t h an @-foot;-diameter parabol ic an tenna , w i t h t h e except ion of t h e MarsS t a t i o n a t Goldstone (210-foot antenn a). The sp ace cr af t moni-t o r i n g s t a t i o n a t Cape Kerinedy i s equipped w i t h a four- footantenna,

The DSN i s under the t e c h n i c a l d i r e c t i o n of J ? L f o rNASA Is Office of Tracking and Data Acquis i t ion . I t s missioni s t o provide met r ic data (spacecraf t ve lo c i ty and range fromE a r t h ) , receive telemetry from and send commands t o unmannedp l a n e t a r y spacecraf t and Sun-orbit ing probes from the t i m e

t h e y are i n j e c t e d i n t o orbit un t i l t hey comple t e t h e i r missions,

The ground communications system, used by t h e DSN f o ro p e r a t i o n a l c o n t r o l a nd data transmission between t h e s t a t i o n sand the SFOF a t JPL, i s par t of a larger network, NASCOM, whichl i n k s a l l of NASA's s t a t i o n s ar ound th e world. NASCON i s underthe t e c h n i c a l d i r e c t i o n of t h e GoddaTd Space F l i g h t Center,Greenbelt , Md.

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The Goldstone DSN s t a t i o n s are operated and maintainedby J P L w i t h t h e assis tance of the Bendix Field Engineering Corp,

The Woomera and Tidbinbilla stations are operated byth e Australian Department of Supply, Weapons Research Estab-lishment ,

The Johannesburg station i s operated by t h e SouthAfrican government through the N at i o n a l I n s t i t u t e for Tele-communications Research,

At Madrid, JPL opera tes one s t a t i o n under an agreementw i t h the Spanish government and t h e support of In st i t u t o Nacionalde Tecnica Aerospacial ( I N T A ) and t h e Bendix Field EngineeringCoo Spain operates t h e second station.

The 1969 Mariner mission of two sp acec r a ft t o Mars w i l lspan a t i m e perio d of about s i x months, The Deep Space Networki s capable of monitoring bo t h Mariner spacecraft on a nearcon t inua l basis w i t h over lapping s ta t i on coverage during cr i t i c a levents,

Nerve center of t h e network i s i n th e Space FlightOperat ions Faci l i ty a t JPL. The overseas s ta ti o n s and Gold-s tone are l inked to the SFOF by a communications network, al lo wi ngtracking and telemetry information t o be sen t there f o r a n al ys i s.

I n a d d i ti o n t o the giant antennas, each of t h e s t a t i o n s

of the DSN i s equipped w i t h t ransmit t ing , receiv ing, data hand-l i n g , and i n t e r s t a t i o n communication equipment, Microwavefrequencies (S-band) w i l l be used i n a l l communications w i t h theMariner spacecraft .

The Echo station a t Goldstone, along w i t h Woomera i nAus t r a l i a , Cebreros i n Spain and Johannesburg i n South Afri ca,w i l l be primary s t a t i o n s f o r t h e m is si on ,watt t r ansmi t t e r , The Mars s t a t i o n a t Goldstone, w i t h its210-foot ant enn a and 20,000 w a t t t r an sm i t t e r also w i l l be usedper iodical ly dur ing t h e mission, and extensively for r ece iv ingscience data during planet encounter and playback portions ofth e mission.

Each has a 10,000

A 3O-foot antenna, operated by N A S A ' s Manned Space FlightNetwork on Ascension Is la nd i n the South Atlantic, w i l l providecoverage during t h e launch and inject ion port ion of each ofthe two f l i g h t s .

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Metric data obtained immediately a f t e r l i f t o f f and throught h e near-Earth phase w i l l be computed a t both t h e Real-TimeComputer System, AFETR, Cape Kennedy and t h e Central Computing

F a c i l i t y i n t h e SFOF SO t h a t accu ra te pred ic t io ns can be s en tt o the DSN stat3-ons giving t h e loca t ions of the Mariners i n t h esky when they appear on the horizon,

S c i e n t i f i c and engin eerin g measurements radioed from t h espacec ra f t a r e r ece ived a t one of the s ta t i on s , recorded ontape and simultaneously t ransmit ted t o the SFOF v i a high speeddata l i n e s and te le ty pe . Incoming information i s agai n recordedon magnetic tape and en te re d i n t o t he SFOFfs computer system f o rprocess ing ,

Sc ie n t i s t s and eng inee rs seated a t consoles i n t h e SFOF havepushbutton control of the displayed information they require

e i t h e r on TV sc r ee n s i n th e consoles o r on pro je c t io n screens andau tomat ic p l a t t e r s and p r in t e r s . The processed information alsoi s sto red i n the computer system di sc f i l e and i s a v a i l a b l e oncommand.

The SFOF, desig ned for? 24-hour-a-day fu nc ti on in g and equippedt o handle mul t ip le s pace f l igh t miss ions concurren t ly , i s mannedby some 250 personnel of J P L and Bendix Field Engineering Corp.,dur in g c r i t i c a l events--launch, midcourse maneuver, pla netencounter--of a Mariner mission.

I n t h e SFOF'S Mission Support Area (M S A ) , s t a t i o n s are s e tup for t h e pro jec t manages, opera t ions d i re c t or i n charge of the

miss ion , opera t ions manager respons ib le f or ph ysic a l opera t iono f the SFOF and three support ing technical teams--Space ScienceAnalysis, FlrLght Path Ana lysis and S pa ce cr af t PerformanceAnalysis.

Space Science Analysis i s r e spons ib le fo r eva lua t ion o fdata from the s c ie n t i f i c experiments aboard t h e spacecraf t andfo r genera t ion of commands controlling the experiments.

F l i g h t Pa th Analysis is r e spons lb le fo r eva luat ion oft r ack ing data, determination of f l i g h t path and ge nera t ion ofcommands affecting th e t r a j e c t o r y o f t h e spacecraf t .

Sp ace cra f t Performance Analysis e val ua tes th e condit ion ofthe spac ecra f t from engineer ing data rad ioed t o Ear th andgenerates commands to the spacecraf t affect ing i t s performance,

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PROJECT TEAMS

Marine r And At las-Centaur Teams

NASA He adquar ters , Washington, D.C.

D r . John E. Naugle

Oran W. Nicks

Donald P. Hearth

Associate Administrator forSpace Science and Applications

Deputy Associate Administratorf o r Space Science andAppl ieat ions

Director, Lunar and PlanetaryPrograms

Newton W. Cunningham Ma riner Program Manager

Joseph B. Mahon Di re ct or , Launch Ve hic le andPropulsion Programs

T. B. Nor ri s Centaur Program Manager

Je t Pro pul sio n Laboratory, Pasadena, C a l i f .

D r. W i l l i a m H. PickeringAdm. John E . Clark

Robert J . Parks

Harr is M. Schurmeier

Gordon P. Kautz

Henry W. Norris

John R. Casani

V i c t o r C Clarke

Dr. John A. St a l l U m P

Laboratory Directo r

Deputy Laboratory Director

Assis tan t Labora tory Direc torf o r F l i g h t P r o je c t s

Mariner Pro Se ct Manager

As sis tan t Manager f o r Pro jec t

Mariner Spacecraft System

Deputy Spacecraft System

Mission Analysis and Engineering

P r o j e c t S c i e n t i s t

Control

Manager

Manager

Manager

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W i l l i a m H. Bayley As s i s t an t Laboratory Dir ec to rf o r T r a ck ing a nd DataA c qu i s i t i on

D r . Nicholas A, Re nz et t i Mar iner Tracking and DataSystems Manager

filarshall S. Johnson Mariner Mission Opera t ionsSystem Manager

Lewis Research Center, Cleveland, 0.

D r . Abe S i l v e r s t e i n Director

D r . S . C. H i m m e l A s s i s t a n t Direc to r f o rRockets and Vehicles

Edmund R. Jonash Chief, Launch Vehic les Divis ion

W i l l i a m R. Dunbar Centaur Project Manager

J e r r y D. S t r i e b l i n g Mariner Mission Engineer

Kennedy Space Center, F l a .

D r . Kurt R, Debus D ir e c to r , KSC

Robert H. Gray

John J . Neilon

John D. Gosse t t

Direc to r , UnmannedLaunch Operations

Deputy. Direc tor , UnmannedLaunch Operations

Manager, CentaurOpera t i ons Branch

E r i n c i p a l S c i e n c e I n v e s t i g a t o r s

D r * Robert B. Leighton Te lev is ionC a l i f o r n i a I n s t i t u t e of Tech.

Dr. George C. Pimente l In f ra red Spec t romete rU n ive r s i ty o f Ca l i f o r n i a ,Berkeley

D r . Charles A. B a r t h

Uni vers i ty of Colorado

U l t r a v i o l e t S p ec tr om et er

D r . Gerry Neugebauer Inf rared RadiometerC a l i f or n i a I n s t i t u t e of Tech.

D r . Arvydas J. Kl io re S-Band Oc cul ta ti onJ e t Propuls ion Labora tory

D r . John D. Anderson C e l e s t i a l MechanicsJ e t Propuls ion Laboratory

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Mariner Mars 1969 Subcontrac tors

Following i s a l i s t of some key subcontractors who

provided instruments, hardware and s e r v ic e s f o r the Mariner

Mars 1969 Pr o j e c t :

Spacecraf t Engineer ing Subsystem Contracts

Elec t ro-Opt ica l SystemsPasadena, C a l i f .

Honeywell, I n c ,Minneapolis, Minn,

L i t t o n Systems I n c .Guidance 8c Control Div,Woodland H i l l s , Cal i f .

MotorolaGovernment Electronics D i v .Sc o t tsdale , A r i z ,

Northrop Corp,Northrop Space Labora to r i e sHawthorne, C a l i f ,

Philco-Ford Corp.Space & Re-Entry Systems Div,Palo Alto, C a l i f .

Texas Instruments, Inc.Apparatus DivisionDallas, Texas

TRW Systems GroupRedondo Beach, C a l i f .

Science I n s tm e n t Contrac ts

Univers i ty of C a l i f o r n i aSpace Science LaboratoryBerkeley, C a l i f .

Power Subsystem

Att i tude Contro l andScan Subsystems

Data AutomationSubsystem

Command Subsystem ,

C e n t r a l Computer andSequencer

E n g ineer i ng Mechani csSubsystem

Radio Subsystem

Telemet ry SubsystemData StorageSubsystem

Propulsion SubsystemTemperature Control FluxMonitor

Inf rar ed Spect rometer

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1st Tier Subcontracts

Philco-Ford Corp. Electronics

Space & Re-Ent;ry Systems Div.Palo Alto, Calif.

Air Products & Chemicals, Inc. CryostatsAdvanced Products DepartmentAllentown, Penn.

Boelng Corp,Spaccl Systems DivaSeattle, Wash.

Santa Barbara Research CenterGoleta, Calif.

University of ColoradoLaboratory for Atmospheric

Boulder, Colo.dc Space Physics

1 s t Tier Subcontracts

Packard Bell Electronics C o r p ,Space B Systems DivisionNewbury Park, Calif.

Electro-Mechanical Research Xnc.Princeton DivisionPrinceton, No J.

Santa Barbara ResearchGoleta, Calif.

Electro-Optical SystemsPasadena, Calif.

General Electrodynamics Corp.Garland, Texas

John H. Ranson LaboratoriesL o s Angeles, Calif.

Pressure Vessels

Detectors

Ultraviolet Spectrometer

Electronics

Photomultiplier Tubes

Infrared Radiometer

Television Electronics

Vidicon Tubes forTelevision

Fab and Test OpticalElements for TelevisionSubsystem

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Other Subcontractors

ABRPasadena, C a l i f

Accessory Products Co,Dive of Textron I n c ,Whit t ie r , Cal i f ,

Adloff and K i n gPasadena, C a l i f .

A i r Borne Controls Inc,Sun Valley, C a l i f ,

Almor Development

Long Beach, C a l i f .

B l a d d e r s f o r Propuls ionSubsystem

P l a t i n g

Operational SupportEquipment (OSE) Cables

Cabling

Advanced Mechanical Components Machine S t r u c t u r a lVan Nuys, C a l i f . Components

A n a d i t e I n c ,South Gate, C a l i f .

Astroda taAnaheim, C a l i f ,

A and T Engineer ingBurbank, C a l i f ,

P l a t i n g

T/M Input Module,461 -1000 Computer,Data Input System,DIS Upgrade

Machined S t r u c t u r a lComponents

Bendix Cor pora tion ConnectorsElectr ica l components Divis ionSidney, N , Y.

Brown Metal F i n i s hE l Monte, C a l i f ' .

Cinch Manufacturing Co.Chicago, Ill.

Cont inenta l T e s t Lab Inc.Fern Park (Orlando), Fla,

Pol i sh ing

Connectors

Screening of E l e c t r o n i cP a r t s

Control Data Corporation Lease General Purposewney, C a l i f , D i g i t a l Computer System

l l a ry Equipmente m T e s t Complext e m

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-54 =

Data Science CorporationSan Diego, C a l i f .

Dickson Electronics Corp.Hollywood, C a l i f .Dynamics Instr. Co,Monterey Park, Calif .El ec t r i c S to rage Ba t t e ry , Inc.Exide Missi le & Elec t ron ics Div.Raleigh, N. C.

E l e c t r o n i c Assemblers Inc .Sun Valley, Cal i f .

E le ct ro ni c Memories Inc.Hawthorne, C a l i f .

Engineering Design a n d DevelopmentPacoima, Calif .F a i r c h i l d SemiconductorMountain V i e w , C a l i f .

F ibre form Elec t ronicsLos Angeles, Cal i f .

First Plaza Company

Mid-Continent Lab Inc .Lincoln, Nebr.

HelioteckA Division of Textron El ec tr on ic sSylmar, C a l i f .

Hi-Shear CorporationTorrance, C a l i f ,

Holex CorporationH o l l i s t e r , C a l i f .

Informat ics I n c ,Los Angeles, Cal i f .

I n s t r u m e n t Machine Co.South E l Monte, C a l i f .

Magnetic Logic Modulesf o r cC&s

Zener Diodes

Limi ted FrequencyO s c i l l a t o r s

S p ac ec r af t B a t t e r i e s

OSE Cables

Core Memory PlaneF a b ri c a ti o n f o r CC&S

Cables

E l e c t r o n i c P a r t s

Chassis

Screening of Electronic

Parts

S o l a r Cel l s

Power Squib Cartr idges

Release AssembliesRelease Devices andCar t r idges

Software

Pi n p u ll e r Body Assys

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-55-

ITT CannonE l e c t r i c Co.Los Angeles, C a l i f ,

Joseph Alzibler Co,North Hollywood, Calif .Jutco Znc.Gardena, Calif .Kearfott D i v i s i o nGeneral Prec i s ion Inc.L i t t l e F a l l s , N. J.

LaRae “ In d u s t r i e sLos Angeles, C a l i f .

Lawrence Indus t r ie sBurbank, C a l i f .

Lowell ObservatoryF l a g s t a f f , Ariz.

N e w Mexico State U n i v e r s i t yLas Cruces, N. M.

Omega EngineeringSun Valley, Cali f .

Optlcal Coating Lab Inc,Santa Rosa, Cal i f . *

Optics Tech. I n c .Palo Alto, C a l i f .

Pevkick Engineering Co, , n c .Burbank, Cal i f .

Pie rce P rec i s ion Shee t MetalPasadena, Calif.

Planning Research Corp.Los Angeles, C a l i f .

PMP Tool & Eng. CompanySun Valley, Calif .

lif.

Company

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Connectors

Machined StructuralComponents

OSE Cables

Gyroscopes,Pulse Sum t o AnalogC o n v e r t e r

Chassis and S t r u c t u r a lSupports

Circu i t Boards

Mars Pola r Cap Studies

Visual Imaging Observa-t i o n s of Mars


Microsheet CoverglassF i l t e r f o r S o l a r Cells

Modulation TransferFunction Bench

Machined StructuralComponenta

Sheet Metal TemperatureC o n t r o l Shie lds

Software

Thermoelectric OvenSubchassis

Chassis



-56-

ProtospecPasadena, Calif.

Chassis

Pyronetics Inc.Santa Fe Springs, Calif.

Rosan Inc.Newport Beach, Calif.Roselm Electronics Co.El Monte, Calif.

Sheffield ManufacturingSun Valley, Calif.

Sherman CorporationInglewood, Calif

Signeti s CorporationSunnyvale, Calif.Skarda Manufacturing CooE l Monte, Calif.

Skyline ComponentsCanoga Park, Calif.

Teb Inc.Arcadia, Calif.

Teledyne Precision Inc.Hawthorne, Calif.

Trans-Sonics Inc.Lexington, Mass.

Wems, Inc.Hawthorne, Calif.

WilorcoLong Beach, Calif.

Wfltronics

IRS Cooling SystemExplosive ValveAssembly, Manifold

AssembliesInserts and Bolts

OSE Cables, PowerSupplies

Chassis and Subchassis


Inkegrated Circuits

chassis

Handling Equipment


Relays

Transducers

Bi-Polar Anabog-to-PulseWidth (A/pw) ConverterModules

Power Supplies

OSE Cables

Mariner Mars 1969 Launches - Press Kit

Documents

Transcript of Mariner Mars 1969 Launches - Press Kit