I NAIIONAL aeronautics and space administration rr. c;-' WA S H I N G T O N , D C . 2 0 ' i 4 6 ras" • - . ^ FOP. RELEASES THURSDAY P.M. May 26, 1966' RELEASE NO: 66-12?

PROJECT: SURVEYOR A

(To be launched no earlier than May 30, 1966)

COr^ENTS GENERAL RELEASE ^-l-i SURVEYOR A SPACECRAFT 5-17 F r a m e , M e c h a n i s m s a n d T h e r m a l C o n t r o l 5 - 8 P o w e r S u b s y s t e m 8 - 1 0 T e l e c o m m u n i c a t i o n s — • l l r - 1 2

F l i g h t C o n t r o l S u b s y s t e m - 1 3 - 1 4 Television 15-l6 E n g i n e e r i n g I n s t r u m e n t a t i o n — I 6 - I 7 AT L A S - C E N TA U R ( A C - I O ) L A U N C H V E H I C L E 1 8 - 2 2 P r e - f l i g h t C h e c k o u t — — - — — — 2 0 - 2 1 C e n t a u r F l i g h t H i s t o r y — — 2 1 - 2 2 ATLAS-CENTAUR FACT SHEET 23 ' . ATLAS-CENTAUR FLIGHT SEQUENCE 24-. S U R V E Y O R F L I G H T P R O F I L E 2 5 • . S U R V E Y O R T R A J E C T O R I E S T O T H E M O O N 2 6 . • TRACKING AND COMUNICATION— TRAJECTORY 28-32 SURVEYOR A FLIGHT MISSION- 32-40 A t l a s P h a s e 3 2 . C e n t a u r P h a s e 3 2 - 3 3 I n i t i a l S u r v e y o r P h a s e 3 3 ' - 3 4 C a n o p u s A c q u i s i t i o n 3 4 r 3 5 M i d c o u r s e M a n e u v e r 3 5 - 3 7 Terminal Sequence 37-39 P o s t - l a n d i n g E v e n t s 3 9 - 4 o A T L A S - C E N T A U R A N D S U R V E Y O R T E A M S - 4 1 - 4 2 M A J O R S U B C O N T R A C T O R S 4 3 - 4 7 CHARACTERISTIC AC-10 LUNAR INJECTION PARAMETERS (Fold ou

-more- ?• A\r5&/rti national aeronautics and space administration wo 2-41 55 E W S WASHINGTON, D.C 20546 • WQ 3-6925

/X,. FOR RELEASE! THURSDAY P.M, MAY 26, 1966

RELEASE NO; 66-12?

FIRST SURVEYOR

TEST iyHSSION

SET FOR MAY 30

T h e U n i t e d S t a t e s i s p r e p a r i n g t o l a u n c h t h e fi r s t

e n g i n e e r i n g t e s t fl i g h t i n a s e r i e s o f S u r v e y o r m i s s i o n s

designed to achieve a soft-landing on the Moon.

The first spacecraft — Surveyor A — is scheduled for launch by the National Aeronautics and Space Administration from Cape Kennedy no earlier than May 30.

The launch vehicle will be the Atlas-Centaur (AC-IO) w h i c h w i l l b e m a k i n g i t s fi r s t o p e r a t i o n a l fl i g h t .

From launch to touchdown on the lunar surface, the

fl i g h t i s e x p e c t e d t o t a k e 6 l t o 6 5 h o u r s .

JLater spacecraft in the Surveyor series will have the,.

m i s s i o n o b j e c t i v e s o f g a t h e r i n g l u n a r s u r f a c e i n f o r m a t i o n

needed for the Apollo manned lunar landing program.

-more- 5/20/66 - 2 -

Primary objectives of Surveyor As - demonstrate the capability of the Atlas-Centaur 10, .

l a u n c h v e h i c l e t o i n j e c t t h e S u r v e y o r s p a c e c r a f t

s u c e s s f u l l y o n a l u n a r - i n t e r c e p t t r a j e c t o r y ^ - demonstrate the capability of the Surveyor spacecraft to perform successful midcourse and terminal maneuvers, and a soft landing on the Moon, and demonstrate the capability of the Surveyor communications

system and the Deep Space Network to maintain communi cations with the spacecraft during its flight and"after

the soft landing.

••• Surveyor will carry a single scanning television camera which is designed to photograph the Moon's surface and the crushable pads on-two of the landing legs to determine how. deeply the pads have penetrated the lunar surface.

A successful mission will prove the concept of a space craft capable of automatically decelerating from 6,000 miles per hour to a touchdown speed of about three and one-half ' miles per hour and functioning in the intense heat of the ' ;

l u n a r d a y.

To accomplish the critical terminal descent and soft • landing. Surveyor is equipped with a solid propellant retro- rocket and three throttleable liquid fuel vernier engines, a flight programmer and analog computer, and radars to ^ determine altitude and rate of descent.

-more- - 3 -

The main braking force is provided by the main retro.'' After it is jettisoned, data from the radars are processed by the computer to throttle the verniers automatically so that Surveyor achieves a soft landing.

At launch Surveyor will weigh 2,194 pounds. The retrd motor, which will be Jettisoned after burnout, weighs 1,377 pounds. After expenditure of liquid propellants and use of • attitude control gas, the landed weight of Surveyor on the.- Moon will be about 620 pounds.

More than 250 ground commands will be required to control Surveyor during flight and after a successful landing on ^ the Moon. About 300 persons will be involved in flight control a t p e a k t i m e s i n t h e m i s s i o n .

The Surveyor program is directed'by NASA's Office of Space Science and Applications, Project management is assigned to NASA's Jet Propulsion Laboratory operated by the California Institute of Technology, Pasadena. Hughes Aircraft Co., under contract to JPL, designed and built the- Surveyor space craft. NASA's Lewis Research Center, Cleveland, is responsible for the Atlas first stage booster and for the second stage ' Centaur, both developed by General Dynamics/Convair, San Diego,

Calif.

-more- - 4 -

Tracking and communication with the Suj?veyor is the responsibility of the NASA/JPL Deep Space Network (DSN). The stations assigned to the Surveyor program are Pioneer,• at Goldstone in California's Mojave Desert; Johannesburg, South Africa; and Tidbinbilla, Australia. Data from the •• stations. Will, be. transmi to JPL^s,.Space Flight Operations Facility in Pasadena, the command center for the mission.

(END OP GE^RAL RELEASE; BACKGROUND INFORMATION FOLLOWS)

-raore- o

F r a m e , M e c h a n i s m s a n d T h e r m a l C o n t r o l

The triangular aluminium frame of the Surveyor provides mounting surfaces and attachments for the landing gear^, 'main retrorocket, vernier engines and associated tanksj, thermal c o m p a r t m e n t s , a n t e n n a s a n d o t h e r e l e c t r o n i c a n d m e c h a n i c a l assemblies. ;

It is constructed of thin-wall alumin-um tubing, with the members interconnected to form the triangle. A mast, which supports the planar array antenna (high-gain) and single solar panel, is attached to the top of the frame. The basic fipame weighs less than 60 pounds and installation hardware weighs 23 pounds. The Surveyor stands about 10 feet high and, with its tri p o d l a n d i n g ' g e a r e x t e n d e d , c a n b e p l a c e d w i t h i n a l 4 - f o o t c i r c l e . A l a n d i n g l e g i s h i n g e d t o e a c h o f t h e t h r e e l o w e r corners of the frame and an aluminum honeycomb footpad is at- tached to the outer end-of each leg. An airplane-type shock a b s o r b e r a n d t e l e s c o p i n g s t r u t a r e c o n n e c t e d t o t h e f r a m e s o that the legs can be folded into the nose shroud during launch. Touchdown shock also is absorbed by the footpads and by the hydraulic shock absorbers which compress with the landing load. Blocks of crushable aluminum honeycomb. are attached to the • b o t t o m o f t h e s p a c e f r a m e a t e a c h o f i t s t h r e e c o r n e r s t o ' a b - sorb .part of the landing shock.

Tw o o m n i d i r e c t i o n a l , c o n i c a l a n t e n n a s a r e m o u n t e d o n t h e ends of folding booms which are hinged to the frame. The- booms remain folded against the frame during launch until-re leased by squib-actuated pin pullers and deployed by torsion springs. The antenna booms are released only after the land i n g l e g s a r e e x t e n d e d a n d l o c k e d i n p o s i t i o n . An antenna/solar panel positioner atop the mast supports and rotates the planar array antenna and solar panel in either d i r e c t i o n a l o n g f o u r a x e s . T h i s f r e e d o m o f m o v e m e n t a l l o w s orienting the antenna toward Earth and the solar panel toward the Sun.

Two thermal compartments house sensitive electronic'" ap paratus for which active thermal control is needed throughout the mission.

-more- JOLAR PANEL

OMNIDIRECTIONAL ANTENNA HIGH-GAIN SURVEY ANTENNA T V C A M E R A STAR CANOPUS SENSOR

OMNIDIRECTIONAL ANTENNA

THERMALLY CONTROLLED" COMPARTMENT If RADAR ALTITUDE- , \ ^ ^VERNIER PROPELLANT DOPPLER VELOCITY- ^ \ \ PRESSURIZING GAS ANTENNA \ \ (HELIUM) TANK \ VuXILIARY BATTERY VERNIER ENGINE V.ATTITUDE CONTROL GAS V (NITROGEN) TANK • ^RETRO ROCKET MOTOR ALTITUDE MARKING RADAR ANTENNA LANDING GEAR

•-raore - -7-

moT equipmentdistributes in each heat•compartment throughout is mounted the compartment. on a ther- An la? blanket, consisting of 75 sheets of aluminized-My- iS^iLrproiecWvfcovI?/^''' compartment's inner sheir-and maintains an internal temperature clivers two®t5anL?f?transmitters, degrees the main P., battery,contains battery two radio charge re- emulator, main power switch and some auxiliary equipment. housesCompartment the central B,command kept between decoder, zero boos?and 125 rSguilfor! decrees central F ' • processor, signal processing auxiliary, engineering signal processor, and low data rate auxiliary. Both compartments contain sensors for reporting temDera- ture measurements by telemetry to Earth, and heater assemblies t a b o v e t h e i r a l l o w a b l e m i n i m u m s • thecalt h e n si^itches S S 1 2 which 5 - d provide e g r e ae conductive m a x i m path u m to w the i t ra-h ' generateddiating surfaces heat. Compartment for automatic A dissipationcontains nLfthemafSwiShes of electricallv mentT?t1rSLn^menu A is 25 pounds, and compartment LlgSrof B, 18 pounds. c^mpS-t! Passive temperature control is provided all equiDment" .compartments through the use of paint'- p a t t e r n s a n d p o l i s h e d s u r f a c e s . •

CK the mechanisms,pyrotechnic switches devices and valves mechanically associated release with the or antennas, landing leg locks, roll actuator, ?eiro!?oSe? 2p- Sd thP SSSS nitrogen tanks, shock absorLrs from the detonator. Sone are actuated by command' tt?on i o n suage f r o m programmer . h e C e n t prior a u r , to o t spacecraft h e r s a r e separa w ! Lted by ground command.- cente- Sviti^S propellant, retrorocket fits withinwithin the the slowinc L? ^^®„£rame and supplies the main'thrustn Q + - ■ forPr\'r> •• attachedslovjin^ ohe at spacecraftthree points on on approach the frame to the near Moon the The landLriL unit i«? hinges with explosive nut separation points for ejection af- uer burnout. The motor case, made of high-strensth steeT and insulated with asbestos and rubber, is 36 inches in diameter Including the molybdenum nozzle, the unfueled engine weio-hs * or more than oO per cent of thethe weight total spacecraft Is aboSt J^STT weight. jSunds .

-more- -8-

Electrical harnesses and cables interconnect the space'r craft subsystems to provide correct signal and power flow. -The harness connecting the two thermal compartments is routed • through a thermal tunnel to minimize heat loss from the com partments, Coaxial cable assemblies^, attached to the frame by- brackets and clips, are used for high frequency transmission. Electrical connection with the Centaur stage is established through a 51-pin connector mounted on the bottom of the frame between two of the landing legs. The connector mates with -.the Centaur connector when the Surveyor is mounted on the launch vehicle. It carries pre-separation commands from the Centaur programmer and can handle emergency commands from the block-' house console. Ground power and pre-launch monitor circuits'- also pass through the connector.

Power Subsystem The power subsystfem collects and stores solar energy converts it to- usable electric voltage, and distributes it to the other spacecraft subsystems. This equipment includes the solar panel, a main battery and an auxiliary battery, an aux"- iliary batte^-^^ battery charge regulator, main power switch, boost regulator, and an engineering mechanisms auxiliary

during flight and during operationsspacecraft's in the primary lunar power day. sourc-e It con sists of 3^960 solar cells arranged on a thin, flat surface of approximately nine square feet. The solar cells are grouped, in 792 separate modules and connected in series-parallel to" guard against complete failure in the event of a single cell-, malfunctiono

panel is mounted at the top of the Surveyor ; mast. Winglike, it is folded away during launch and deployed aiter the spacecraft has been ejected into the •• l u n a r t r a n s i t t r a j e c t o r y. supply abouoppperly„ 89 waots oriented which during is most flight, of the power " solar, reauired panel forcan the average operating load of all on-board equipment. During operation on the lunar surface, the solar panel ' can be adjusted by Earth comman : r a c k t h e S u n w i t h i n a f e w degrees^ so that the solar cells remain always perpendicular t o t h e s o l a r r a d i a t i o n / ^ ^

-more-

On the Moon, the solar panel is designed to supply a

minimum of , 77 watts , power atJ . — a temperatureJ. of l40 degrees and O a mint v Mmum ^ -of P 57 C T watts^ 4 - at a^ temperatureu j of^ 239 degrees F/

A l4-cell rechargeable, silver-zinc main battery is the icecrafr's power reservoir. It is the sole source of power ^'ing lauuch; it stores electrical energy from the 'solar panel 'ing transit and lunar-day operations; and it provides a back- source to meet peak power requirements during both of those r'lods, ^ Rilly charged, the battery provides 3»800 watt-hours a discharge rate of 1.0 amperes. Battery output is approx- icely 22 volts direct current for all operating and envirdn-

^ital^conditions ^ S X* ® in temperatures from 4o degrees to ,125 de-r-

auxiliary battery is a non-rechargeable, silver-zinc ' oai:uery con^ained in a sealed magnesium cannister. It provides a power oacimp for both the main battery and the solar panel c o n d i t i o n s . T h i s b a t t e r y h a s a :y^of from 800 to 1^000 watt-hours depending upo'n power temner

are uhe two powercharge conditioning regulator elements and the of booster the spacecraft's regulator •••' '• .electrical power subsystem. The battery charge regulator = ! ! ! r b a t t e r y f o r m a x i m u m c o n - , , ty^ersion h e m and a m transmission b a t t e r y of a the t fsolar u l l energy c h a r gnecessary e . o o to i tkeeD e e p

^ 1- 3?eceives pox^er at the solar panel's varying output anc .terminal voltage. The battery chargebattery regulator at a constant includes battery sen sing pd logic circuitry for automatic battery charging when ever battery voltage drops below 27- volts. The booster regulator unit receives unregulated power

Che main1 , ^'*5 volts direct current from the solar panel. both,J , and deliversX aw . regulatedJ L O . 29 volts,"V V J J l L / O - direct current to the spacecraft's three main power trans- • • mission lines. These three lines supply all the spacecraft's-, power neeas, except for a 22-volt unregulated line which circuits wnich do not requirea c t u a regulated t o r s , s o l e power n o i d s aor n d provide e l e c t r o n their i c ; oivn regulation. -

-more- Telecommunications

C o m m u n i c a t i o n s e q u i p m e n t a b o a r d S u r v e y o r s e r v e s t h r e e , functions: providing transmission and reception of radio-,, s i g n a l s ; d e c o d i n g c o m m a n d s s e n t t o t h e s p a c e c r a f t ; a n d s e l e c t i n g a n d c o n v e r t i n g e n g i n e e r i n g a n d t e l e v i s i o n d a t a i n t p a f o r m s u i t a b l e f o r t r a n s m i s s i o n . •

T h e fi r s t g r o u p i n c l u d e t h e t h r e e a n t e n n a s : o n e h i g h r * " gain^ directional, antenna^ and tvjo lovj-gain;, omnidirection-.-'• . a n t e n n a s ; t w o ' t r a n s m i t t e r s a n d t w o r e c e i v e r s w i t h t r a n s p o n d e r i n t e r c o n n e c t i o n s . D u a l t r a n s m i t t e r s a n d r e c e i v e r s a r e u s e d , f o r r e l i a b i l i t y .

The high-gain antenna transmits 600-line television data. T h e l o w - g a i n a n t e n n a s r e c e i v e g r o u n d c o m m a n d s a n d t r a n s m i t " o t h e r d a t a i n c l u d i n g 2 0 0 - l i n e t e l e v i s i o n d a t a f r o m t h e s p a c e c r a f t , . E i t h e r l o w - g a i n a n t e n n a c a n b e c o n n e c t e d t o e i t h e r r e c e i v e r . T h e t r a n s m i t t e r s c a n " b e s w i t c h e d t o e i t h e r l o w - g a i n a n t e n n a o r t o t h e h i g h - g a i n , a n t e n n a a n d c a n o p e r a t e a t l o v ; o r h i g h p o ' w e r / l e v e l s . T h e r m a l c o n t r o l o f t h e t h r e e a n t e n n a s i s p a s s i v e ; - d e pendent on surface coatings to keep temperatures within accep- .:,table limits.^ • The command decoding group can handle up to 256 comm^ands b o t h d i r e c t ( w h i c h c o n t r o l o n - o ff o p e r a t i p n s ) a n d q u a n t i t a t i v e commands (which control time interval operations). Each incotnlng c o m m a n d i s c h e c k e d i n a c e n t r a l - - c o m m a n d d e c o d e r w h i c h w i l l r e - . ject a command, and signal the rejection to Earth if the-- s t r u c t u r e o f t h e c o m m a n d i s i n c o r r e c t . A c c e p t a n c e o f a c o m m a n d i s a l s o r a d i o e d t o E a r t h . T h e c o m m a n d i s t h e n s e n t t o subsystem decoders that translate the binary information Into a n a c t u a t i n g s i g n a l f o r t h e f u n c t i o n c o m m a n d s u c h a s s q u i b ; ; firing and change data modes. . •

Processing of most engineering data, (temperatures, vol t a g e s , c u r r e n t s , p r e s s u r e s , s w i t c h p o s i t i o n s , e t c . ) i s h a n d l e d b y t h e e n g i n e e r i n g s i g n a l p r o c e s s o r o r t h e a u x i l i a r y p r o c e s s o r . T h e r e a r e o v e r 2 0 0 e n g i n e e r i n g m e a s u r e m e n t s o f t h e s p a c e c r a f t . N o n e a r e c o n t i n u o u s l y r e p o r t e d . T h e r e a r e f o u r c o m m u t a t o r s i n t h e e n g i n e e r i n g s i g n a l p r o c e s s o r t o p e r m i t s e q u e n t i a l s a m p l i n g o f s e l e c t e d s i g n a l s . T h e u s e o f a c o m m u t a t o r i s d e p e n d e n t - o n the type and amount of information required during various• fl i g h t s e q u e n c e s . E a c h c o m m u t a t o r c a n b e c o m m a n d e d i n t o o p e r a t i o n a t a n y t i m e a n d a t a n y o f t h e fi v e b i t r a t e s : 1 7 . 2 , 1 3 7 - . 5 j 550, 11,100 and ^/!00 bits-per-second.

-more- -12-

Commutated signals from the engineering processors are converted to 10-bit data words by an analog-to-digital con verter in the central signal processor and relayed to the " t r a n s m i t t e r. T h e l o w - b i t r a t e s a r e n o r m a l l y u s e d v j i t h t r a n s missions over the low»-gain antennas and the low~power levels of the transmitters.

Video data from the TV cameras is fed directly to the transmitters only during high-power operation and requires the use of-high-gain antenna when in the 600-line mode. • ' •

Propulsion

The propulsion system consists of three liquid fuel- ver n i e r r o c k e t e n g i n e s a n d a s o l i d f u e l r e t r o r o c k e t . T h e v e r n i e r s a r e u s e d f o r t h e m i d c o u r s e m a n e u v e r a s w e l l a s i n t h e t e r m i n a l l u n a r l a n d i n g s e q u e n c e . ..

The vernier engines are supplied fuel by three fuel tanks and three oxidizer tanks. There is one pair of tanks^ fuel • a n d o x i d i z e r, f o r e a c h e n g i n e . T h e f u e l a n d o x i d i z e r i n / e a c h tank is contained in a bladder. Helium stored under pressure i s u s e d t o d e fl a t e t h e b l a d d e r s a n d f o r c e t h e f u e l a n d o x i d i z e r i n t o t h e f e e d l i n e s .

T h e o x i d i z e r i s n i t r o g e n t e t r o x i d e w i t h 1 0 p e r c e n t n i t r i c o x i d e . T h e f u e l i s m o n o m e t h y l h y d r a z i n e m o n o h y d r a t e . A n . ' i g n i t i o n s y s t e m i s n o t r e q u i r e d - f o r t h e v e r n i e r s a s t h e f u e l . a n d - o x i d i z e r a r e h y p e r g o l i c ^ b u r n i n g u p o n c o n t a c t . T h e t h r o t t l e r a n g e i s 3 0 t o 1 0 4 p o u n d s o f t h r u s t . • • . The main retro is used at the beginning of the terminal descent to .the lunar surface and slows the spacecraft from .an ' approach velocity of about 6,000 mphto approximately 246\raph. It burns an aluminum, ammonium-perchorate and polyhydro carbon, c a s e - b o n d e d c o m p o s i t e * - t y p e p r o p e l l a n t . " ' The nozzle has a graphite throat and a laminated plastic e x i t c o n e . T h e c a s e i s o f h i g h - s t r e n g t h s t e e l i n s u l a t e d . w i t h a s b e s t o s a n d s i l i c o n d i o x i d e - fi l l e d b u n a - N r u b b e r t o m a i n t a i n the case at a low temperature level during firing.

Engine thrust varies from 8,000 to 10,000 pounds over a temperature range of 50 to 70 degrees P. Passive thermal;' • c o n t r o l , i n s u l a t i n g b l a n l c e t s a n d s u r f a c e c o a t i n g s , w i l l m a i n tain the grain above 50 degrees P, It is fired by a pyrogen igniter. The main retro weighs approximately 1,377 pounds a n d i s s p h e r i c a l s h a p e d , 3 6 i n c h e s i n d i a m e t e r . •

-more -13-

Flight Control Subsystem

F l i g h t - c o n t r o l o f S u r v e y o r ^ c o n t r o l o f i t s a t t i t u d e a n d velocity from Centaur separation to touchdovrn on the Mooh^- is provided by: primary Sun sensor^ automatic Sun acquisition s e n s o r, C a n o p u s s e n s o r ^ i n e r t i a l r e f e r e n c e u n i t ^ a l t i t u d e - marking radar, inertia burnout switch, radar altimeter and Doppler velocity sensors, flight control electronic, , and-- • three pairs of cold gas jets. Plight control electronics"in cludes a digital programmer, gating and switching, logic and a signal data converter for the radar altimeter and Doppl'er ■ v e l o c i t y s e n s o r s . The iniormation provided by the sensors is processed" through logic circuitry in the flight control electronics•to yield actuating signals to the gas jets and to the three'li quid fuel vernier engines and the solid fuel- main retromotor. The Sun sensors provide information to the flight control electronics indicating whether or not they are illuminated by _ uhe Sun, This information is used to order the gas jets to fire and maneuver the spacecraft until the Sun sensors are"on with the Sun, The primary Sun sensor consists /fv® cadmium sulphide photo-conductive cells. During •• Surveyor may deviate slightly off of pointing direct- ly the Suno Such deviations are continuously corrected*"by signals from^the primary sensor to the flight electronics or- dering the pitch and yaw gas jets to fire to again center the- Sun sensors on the Suno Sun acquisition is required before locking on to the star Canopus._ Gas jets are used to center the star sensor, on Canopus, so as to maintain roll axis attit^jide during c]?uise modes. If star or Sun lock is lost, control is automatically switched from optical sensors to gyros which sense changes in spacecraft attitude inertially. ; The inertial reference unit is also used during events when the optical sensors cannot be used — midcourse maneuver and descent to the lunar surface. This device senses changes in attitude of the spacecraft and in velocity with three gyros and an accelerometer. Information from the gyros is processed 5^-tain theelectronics desired attitude. to fire During gas jets lunar to descent change thrust or phases, niain- the inertial reference unit controls vernier engine thrust • levels by differential throttling for pitch and yaw control and swiveling one engine for roll control. The accelerometer c o n t r o l s t h e t o t a l t h r u s t l e v e l .

- m o r e - ' • . The altitude marking radar will provide the signal for iring of the main retroo It is located in the nozzle of the retro motor and is ejected when the motor ignites. The radar generate a signal at about 6o miles above the lunar sur- lace. ihe signal starts the programmer automatic sequence the progr^er tnen commands vernier(directed and by groundretro ignition command) and j.' turns on the radar altimeter and Doppler velocity sensors»

level of the main retro engineswitch drops will below close when3.5 g, thegenerating: thrust • programmer to command jettison- motor and switching to control by the radar altimeter and Doppler velocity sensors®

spacecraft after main retro burnout is • Twosted radar in the dishes radar are altimeter involved. and An Doppler altimetI?AeiSi?y velocitv sensors sensing■ radiates two beams and a velocity sensing antenna two Be^s .l, 2, and 3 can yield vertical or transverse '• S ! . ™ a l t i t u3 d eprovide o r s velocity l a n t data r a n byg e adding i n f o ther m a Dopjiier t i o n . vy (frequency shift due to velocity) of each beam in the is^f^d The converted range and velocity data tthe L thrust signals ? h r u to ? t the vernier c o engines, n t r o l " '

£^^Sh-t control electronics provides for processing: into telemetry and to actuate spacecraft-' mechanisms. It consists of control circuits^, a command de» coder and an AC/pc electronic conversion unit. The program- of main retro phase and generates pre cision time delays for attitude maneuvers and midcourse ve l o c i t y c o r r e c t i o n , . attitude jets provide attitude control to the space-' craft from Centaur separation to main retro burn. The Fas let system Is fed from a spherical tank holding 4.r^ouS o? nl! 5^S-^ pressure, regulating and dumping valves ? pai^s Ox opposed gas Jets with solenoid operated of each laeh of of the One three pair landing of Jets legs. is The located pair on at one the leg end • motion in a horizontal plane, imparting roll mo-

JiSd,nQ yaWo ^ spacecraft. The other two pairs control pitch

-more- i.

sumiEM

MIRROR

-MlRROf^ iVIiRROR AZIMUT ELEVAT.rON DRiVE lYiOTOR ^ D R i V E A S S E M B L Y

VARIABLE ) ' J F i L T E R W H E E L FOCAL LENGTH ASSEMBLY L E N S A S S E M B L Y

FOCUS POTENTJOiVlETER

IR!S POTENTiOMETER

• V I D I C O N T U B E SHUTTER ASSEiVlBLY

-ViDICON RADIATOR

- — 1 1 y

ELECTRICAL CONNECTOR -16-

Television

The Surveyor A spacecraft will carry one survey tele vision camera. The " camera is mounted nearly vertically. Do'int- ea^au a movable mirror. The mounting containing the mirrox' can vjhereswivel_350 it reflects degrees;, a portion and the of mirrora landing can leg tilt from to above a position the'v horizon,

leeGoo^ J. Ci^era infinity. can Its be focusedj,iris setting^ by Earth which command^ controls fromthe amount four 01 light entering the camera^ can adjust automatically to. .the varj.ablelignt^ level focal or can length De lens commanded which canfrom be Earth, adjusted The camera to either has nar- a rovj angle^ o 4 x 6,M- field of view, or to vjide-angle25.4 x 0.4 iield of view, A focal plane shutter provides an exposure time of 150 shutter can also be commanded open for-an indefinite length of time, A sensing device coupled to the shuouer will keep it,from opening if the light level is too intense. A too-high light level could occur from changes' in tne areaoi coverage by the camera, a change in the angle.of mirror, in the lens aperture, or by changes in Sun angle,"The same sensor controls the automatic.iris setting. The sensinp' d e v i c e c a n b e . o v e r r i d d e n b y g r o u n d c o m m a n d . • . • ■ The camera system can provide either 200 or 600-line ' pictiures. The latter requires that the high-gain directional anoenna and zne high power level of the transmitter are both working. The 600-line mode provides a picture each 3.6 seconds ana ohe 200-line mode every 6l,8 seconds.

A^filter wheel can be commanded to one of four positions p r o v i d i n g c l e a r, c o l o r e d o r p o l a r i z i n g fi l t e r s . Surveyor A also will carry a downward-looking television thisc^era camera mounted is not on the planned lower to frame be turned of the on spacecraft. during this However^ mission.

Engineering Instrumentation

Engineering evaluation of the Surveyor test flights will be made by an engineering payload including an auxiliary bat tery, auxiliary processor for engineering Information, and. in stpuinenoation consisting of extra temperature sensorso strain gauges for gross measurements of vernier engine response to . fligho control commands and shock absorber loading at touch down^ and extra accelerometers for measuring structural vi bration during main retro burn,

-more- -17-

The auxiliary battery will provide a backup for both "• emergency power and peak power demands to the main battery and the solarpanel^ It is not rechargeable. The auxiliary e n g i n e e r i n g s i g n a l p r o c e s s o r p r o v i d e s t w o a d d i t i o n a l t e l e - ' metry commutators for determining the performance of the space craft » ^ It processes the infomation in the same manner as' ! the engineering signal processor, providing additional sig-- • n a l c a p a c i t y a n d r e d u n d a n c y , ; •

-more- ATLAS-CENTAUR (AC-IO) LAUNCH VEHICLE _ • "

A t l a s - C e n t a u r ' s p r i m a r y o b j e c t i v e i s t o i n j e c t t h e . S u r v e y o r A s p a c e c r a f t o n a l u n a r - t r a n s f e r t r a j e c t o r y w i t h ' s u f fi c i e n t a c c u r a c y s o t h a t t h e t n i d c o u r s e m a n e u v e r c o r r e e - )n requi] ; o m e 2 0 h o u r s a f t e r l i f ' d o e s n o t e x c e e ( some loi^-feet-per-second or 111.85 miles-oer-hour.

T h e C e n t a u r s t a g e i s t h e n r e q u i r e d t o p e r f o r m a r e t r o - m a n e u v e r a f t e r s p a c e c r a f t s e p a r a t i o n . T h i s a l t e r s C e n t a u r ' s t r a j e c t o r y s u f fi c i e n t l y t o a v o i d i m p a c t i n g t h e M o o n a n d " also prevents Surveyor's star seeker from mistaking Centaur for Canopus on which Surveyor will focus for spacecraft-'.' orientation. •

C o n fi g u r a t i o n o f t h e A C - 1 0 v e h i c l e i s s i m i l a r t o t h a t o J AC-6., which on Aug. 11, 1965^ demonstrated Centaur's capa b i l i t y t o i n j e c t a S u r v e y o r s p a c e c r a f t o n a d i r e c t - a s c e n t s l u n a r - t r a n s f e r t r a j e c t o r y. F o r t h e A C - 1 0 v e h i c l e . C e n t a u r ' s inertial guidance system has been updated, four 50-pouhd ■ t h r u s t h y d r o g e n - p e r p x i d e e n g i n e s h a v e b e e n a d d e d f o r t h e retromaneuver, the. attitude control engines have been up-, rated, and some minor telemetry systems have been modified.

T h e C e n t a u r l a u n c h v e h i c l e i n c l u d e s a n LV- 3 C A t l a s , booster combined with a Centaur second stage. Both stages are 1( . e e t i n d i a m e t e r a n d a r e c o n n e c t s b y a n i n t e r

T h e A t l a s fi r s t s t a g e i s 7 5 f e e t h i g h , i n c l u d i n g t h . e interstage adapter, and uses a' standard MA-5 propulsion . system. It consists of two booster engines and a sustaihe] engine, developing a total of 388,000 pounds of thrust.' Two vernier engines of 670 pounds thrust each provide roll control.

The Centaur upper stage, including the nose fairing which surrounds Surveyor, is 48 feet long. Centaur is powered by two high-energy RL-10 hydrogen-oxygen engines, e a c h w i t h 1 5 , 0 0 0 p o u n d s t h r u s t . T h e R L - 1 0 w a s t h e fi r s t ' high-energy engine developed for the space program and the fi r s t t o b e fl o w n s u c c e s s f u l l y i n s p a c e . C e n t a u r ' s t a n k i s c o n s t r u c t e d■o f s t a i n l e s s s t e e l , O . O ; i n c h e s t h i c k . A t l a s i s a l s o f a b r i c a t e d o f s t a i n l e s s s t e e l

-more- ' V ' l i \; LH

, ^/(h-AWV^^ ■^Mx- ■/

a %

■ X. \

V \ \ \ -—

Artist's concept shows jettisoning of insulation panels and nose fairings as Atlas-Centaur vehicle leaves'atmosphere

•more- -20-

The Centaur stage is surrounded by thermal insulation maintainedpanels_to minimize at -423 degrees the boiloff P. Theof liquid four hydrogen panels are which'is jettisoned after the vehicle leaves the atmosphereo The nose ^fairing:, constmjcted of honeycombed fiberglass, surrounds the payload and guidance and electronic equiotiient packages mounted on Centaur and provides thermal and aerody namic protection during flight through the atmosphere.', 'The clamshell lairings are jettisoned shortly after the in-sula- tion panels. . Atlas and Centaur are separated in flight by a linear- shaped charge which severs the interstage adaoter. Eight' retrorockets mounted on the aft.end of Atlas are fired to increase the rate of separation. In addition to its primary propulsion system, the Cen taur stage uses hydrogen-peroxide attitude control rockets of 3.5 and 6 pounds thrust and- four 50-pound thrust hydrogen- peroxide thrusters which are used during the retromane.uver.

Pre-flight Checkout Atlas-Centaur vehicles are subjected to rigorous pre- flight checkout procedures prior to shipment to Cape iCennedy for erection and subsequent launch. The Atlas-Centaur vehicle and its Surveyor payload • rehearse the lunar mission in a unique facility designed to ground-test all stages--including the payload--of a space vehicle. * . This flight simulation is done in a Combined Systems Test Stand (CSTS) by Convair and Hughes personnel in San Diego. CSTS, operated for NASA by Convair, is designed 'to reduce vehicle preparation time at Cape Kennedy. During Atlas-Centaur-Surveyor testing, personnel are present'from NASA, Convair, JPL and Hughes. In combined systems testing, the Atlas-Centaur-Sur'veyor combination simulates.electronically all aspects of a 'lunar mission. Recording equipment in the CSTS operations room is similar to that at Cape Kennedy and countdown procedures used are the same as for an actual launch. Tests are run to' coincide with launch-on-time conditions.

-more- -21-

Centaur's. RL-10 engines undergo at least thi^ee test firings prior to each mission. During its development' and- operational program^ the RL-10 has accumulated about 8pdO ' firings—Including test firings and Centaur and Saturn I •. m i s s i o n s . ToTotal t a l fi r i n firim g t i m e f o r t h e R L - 1 0 h a s o a s s e d seconds Centaur's inertial guidance system, which issues all flight control commands follov/ing Atlas booster engine cut- of Iis checked out at the contractor's facility prior to acceptance for a Centaur flight vehicle, . This system is". b u i l t b y H o n e y w e l l , I n « Petersburg,■ Pla., facility:

^oems Once have the^vehicles, satisfactorily spacecraft, passed combined their systems systems and testing,' subsys- they are shipped to Cape Kennedy for erection on the Centaur launch complex. The Atlas booster for AC-10 v/as erected at Pad 36-A' ' on March 21, followe'd by the Centaur stage on March 31, and the Surveyor•spacecraft on April 17. The vehicle successfully completed a tankino- inkins Atlas andO Centaur / N propellants^ X T ------^ on April C H J 20'o U This was followed-by a Joint Plight Acceptance Test (J-FACT) on April 2o. A final Combined Readiness Test (CRT) is scheduled for May 26. The latter test confirms that the vehicle-spacecraft combination is in a launch-ready condition.

The main test program was conducted at Convair Kearney Mesa plant, the Sycamore Canyontest test facility and^at^pL^Loma in San Diego, Additionaldditional "cesting testing includes includesf a c i l i at a y two-year a n d serieseries Ox Qynamic^tests at the the NASA NASA Lewis Lewis Research Research Center's Plum ' Brook Station with a complete Atlas-Centaur/Surveyor, simu lated high-altitude testing in Lewis • Space Pox^er Chamber .and oerseparation^and at Lewis, located nose fairing in Cleveland, jettison tests in a vacuum chaiji-

C e n t a u r F l i g h t H i s t o r y The Centaur vehicle has completed its single-burn, direct-ascent development program and was declared operationa" lor lunar and planetary missions, following the successful AC-6 mission last August. During the AC-6 mission, a dynamic model 01 Surveyor was injected toward a target in space, ' called an imaginary Moon, with sufficient accuracy that • •' nad a Surveyor spacecraft been directed to a landing on the" Moon, a mLdcourse velocity correction of only 9,5 miles per h o u r w o u l d h a v e b e e n r e q u i r e d . Yet to be demonstrated in the Centaur development pro g r a m i s a r e s t a r t c a p a b i l i t y w h i c h w i l l p r o v i d e g r e a t e r • ' • fl e x i b i l i t y i n v e h i c l e l a u n c h o p e r a t i o n s b y w i d e n i n g l a u n c h - windows--periods during which lunar or planetary payloads • m u s t b e l a u n c h e d t o i n t e r c e p t t h e t a r g e t — f r o m m i n u t e s t o ' h o u r s . E a r t h p a r k i n g o r b i t s a l s o w o u l d p e r m i t S u r v e y o r . , l a u n c h e s t o b e a t t e m p t e d d u r i n g w i n t e r m o n t h s w h e n l u n a r l i g h t i n g c o n d i t i o n s a r e u n f a v o r a b l e f o r d i r e c t - a s c e n t t r a - ' jectories. ' ' •

T h e C e n t a u r p r o j e c t w a s i n i t i a t e d b y t h e A d v a n c e d Research Projects Agency in 1958 as the nation's first high- e n e r g y r o c k e t v e h i c l e . U s i n g l i q u i d h y d r o g e n w i t h a l i q u i d inoxygen^oxidizerJ performance over Centaur vehicles provides using about conventional a 40 per kerosene- cent incr&ase type fuels. The project was transferred to NASA's Marshall Space.' Flight Center in I96O and later to the agency's Lewis Re-' s e a r c h C e n t e r i n l a t e 1 9 6 2 . The exact cause of the depletion of hydrogen-peroxide' fuel on the AC-8 mission has not been determined. A similar v e h i c l e d e v e l o p m e n t f l i g h t — l a s t i n t h e s e r i e s o f C e n t a u r ' • ^ v e h i c l e t e s t s — i s - s c h e d u l e d l a t e r t h i s y e a r . • • Other Atlas-Centaur vehicles are scheduled to carry . Surveyor spacecraft to the Moon and Mariner spacecraft to.. Mars during the I969 launch opportunity.

-more- -23-

ATLAS-CENTAUR FACT SHEET

( A l l fi g u r e s a p p r o x i m a t e )

Liftoff Weight: 303,000 lb£

Liftoff Height: 113 feet

Launch Complex:

A t l a s B o o s t e r C e n t a u r S t a g e

Weight 263,000 lbs. 37,500 lbs, (less payload)

leight 75 feet (including 48 feet (with interstage adapter f a i r i n g ) ■ Thrust 388,000 lbs, (sea 30,000 lbs. (at level) altitude)

Propellants R P - 1 ( f u e l ) a n d l i q u i d Liquid hydrogen oxygen (oxidizer) ( f u e l ) a n d l i q u i d o x y g e n ( o x i d i z e r )

Propulsion. M A - 5 s y s t e m ( 2 - 1 5 5 , 0 0 0 Two RL-10 engines l b . t h r u s t b o o s t e r e n gines, 1-57,000 lb. s u s t a i n e r e n g i n e , a n d 2 - 6 7 0 l b . v e r n i e r e n gines)

Velocity 5560 mph at BECO 23,500 mph-at in 7700 mph at SECO jection

Guidance Preprogrammed auto Inertial pilot through BECO

-more- 3 ■ ■■ )

ATLAS-CENTAUR FLIGHT SEQUENCE

EVENT NOMINAL ALTITUDE^ S U R F A C E R A N G E VEL/MPH

TIME^ SEC & S T A T U T E M I „ S T A T U T E M I .

1. Liftoff 0 0 0 0 ' 3 6 2. B o o s t e r E n g i n e C u t o f f 142 49 5560

B o o s t e r E n g i n e J e t t i s o n 3. 145 i 39 54 5630

4. J e t t i s o n I n s u l a t i o n P a n e l s 1 7 6 58 , 100 6150

5. Jettison Nose Pairing 203 74 144 6700

6. S u s t a l n e r E n g i n e C u t o f f 240 97 212 7600

7. A t l a s - C e n t a u r S e p a r a t i o n 2 4 2 98 215 7600

8. C e n t a u r E n g i n e S t a r t 251 104 234 7 6 0 0 ^ o ■ tr CD 9. C e n t a u r E n g i n e C u t o f f t 685 144 1740 2 3 , 5 0 0 ' ! 10. S p a c e c r a f t S e p a r a t i o n ^ 757 111 2200 23,500

11. Centaur Reorientation 762 109 2200 23,500

12, C e n t a u r R e t r o t h r u s t 997 207 3700 23,500

(launch vehicle mission completed at T p l u s 21 minutes)

F i g u r e s u s e d a r e a p p r o x i m a t e b u t typical of potential t r a j e c t o r i e s f o r A C - 1 0 , d e p e n d i n g o n d a y o f launch.

"... '■ m o r e - : • • . ' • • • t/5 ^ 0£ Q X 2 Z ^ o p O t: CO ID X 3 O ( J C £ *7 u Z'^ < o 5 ^ to < 3 UJ N O 5g--i Z £Q < 2S j< u < U CO

< CO z O a! H; U z 00 Z X 5 5 ^ i u o < g '

-more - -27-

TRACKING AND COMMUNICATION' The flight of the' Surveyor spacecraft from injection to the end of the mission will be monitored and controlled by the Deep Space Network (DSN) and the Space Plight Opera^' tions Facility (SFOF) operated by the Jet Propulsion Labor- • atory. Deep Space Network consists of six permanent space conmiunications stations in Australia^, Spain^, South Africa, and the California Mojave Desert^ a spacecraft monitoring . station at Cape Kennedy; and a spacecraft guidance and com-• mand station at Ascension Island in the South Atlantic. The DSN facilities assigned to the Surveyor project are Pioneer at G-oldstone^, Calif,; and those at Johannesburg, South Africa, and Tidbinbilla in the Canberra Complex, Australia, • " The G-oldstone facility is operated by JPL with the assistance of the. Bendix Field Engineering Corp. The Tid binbilla facility is operated by the Australian Department 'of Supply. The Johannesburg facility is operated by the South • African government through the Counsel of Scientific and ' O Industrial Re search... and the National Institute for Telecommun i c a t i o n s R e s e a r c h . The DSN uses a ground communications system for operational control and data transmission between these stations. The ground communications system is a part of a larger net (NASCOM) which links all of the NASA stations around the world. This ' net is under the technical direction of the Goddard Space Flight Center, C-reenbelt, Md. The DSN supports the Surveyor flight in tracking the spa'ce- craft, receiving telemetry from the.spacecraft, and sending • commands to all of NASA's unmanned lunar and planetary space craft from the time they are injected into planetary orbit until t h e y c o m p l e t e t h e i r m i s s i o n s . Stations of the DSN receive the spacecraft radio signals, ampliiy them, process them to separate-the data from the carrier wave and transmit required portions of the data to .the command center via" high-speed data lines, radio links, and ' teletype. The stations are also linked with the center by 'voice lines. All incoming data are recorded on magnetic tape.

-more- -28-

±il ,tion transmitted f o 3 the DSN spo:F is e s larg cale computer systems the d ig into en gineering units. sepa: pertine: i ven subsystem o n the spacecr; dis;pi ay t in the SFOP to present the : the e ng the project. All incomi:ng d;ata are again recordec c omputer memor y s y stem. and a r < demand. iquipment lor monitoring television reception from surveyor spacecraft is located in the SPOF,

of^the decisions equipment on iscommanding designed tothe provide camera quick-lookto change set uings_^ change ^uhe field of view from narrow angle to ide angleJ change focus, or to move the camera either horizontally or vertically. Television monitors display the picture being received. The pictures are received line bv tube un.il ohe picour^eheld is complete. on a long A special persistance camera television system' j : - —J.C: proaucesproduces prints prints of of the ohe pictures pictures fc for quick-look analysis. '• Other equipm.ent will produce better Quality pictures' f>-om negatives produced by a precision film recorder. Coromanas to operate the camera will be prepared in advance onThe?^Si?? Lders" forwarded Sorthrspof to the the stations-of DSN the-DSN. station

^ technicalIS teams responsible support for determining the Surveyor the mission trajectory in of the launchS requirements, including determination generation of commands of launch for periodsthe midcourse and ' and terminal maneuvers; the second is responsible for continuou' dat^Zt f radioed.'^1 condition to Earthj T:heof the third spacecraft is' responsible frL for ei^neerSr' evaluation spacecraft and for generating commands controlling spacecraft operations.

TRAJECTORY durin^i eacn day, and the Earth-Moonpossible launch trajectories days, specific for the Sur times veyor spacecraft is based on a number of factors -29-

A p r i m a r ; t a s c e n t l a u n c h a £ opposed to the parking orbit technique. A parking orbit "is more complex in that it requires the Centaur second stage to fi r e i t s e n g i n e s t o a c h i e v e t h e i n i t i a l c i r c u l a r ' o r b i t ^ c o a s t in orbit about the Earth and then to fire its engines the •' second time to accelerate the spacecraft to the required•lunar transit velocity.

I n i t s fi r s t o p e r a t i o n a l m i s s i o n s t h e C e n t a u r w i l l n o t b e required to perform the complex double burn. After separation from the Atlas booster^ the Centaur will ignite its engines . w h i c h w i l l c o n t i n u e t o b u r n - u n t i l t h e l u n a r t r a n s i t v e l o c i t y . h a s b e e n r e a c h e d . T h i s v e l o c i t y v a r i e s s l i g h t l y w i t h l a u n c h d a y a n d ^ t l m e b u t i s a p p r o x i m a t e l y 2 4 ^ , 5 0 0 m p h . ' Use of the direct ascent trajectory limits each monthly launch period to those days when the Moon is at negative d e c l i n a t i o n s - - t h a t i s ^ i n p o s i t i o n s ^ r e l a t i v e t o E a r t h , . b e l o w the Earth*s'equator..

The days of the -month available for launching ai?e determined by the attainable range in the flight path arigle of the Centaur at injection -- that point in time when the Centaur engines, c e a s e fi r i n g a n d t h e r e q u i r e d v e l o c i t y f o r a l u n a r fl i g h t ' h a s been reached. The flight path angle is the angle at which C e n t a u r i s m o v i n g r e l a t i v e t o a h o r i z o n t a l p l a n e o f t h e E a r t h below. Changes in* this angle compensate for the daily change in the position of the Moon.

The attainable range in the angle is determined by the" fuel available;in. the Atlas-Centaur combination/ as both vehicles are involved in the angle of Centaur~at injection. Any devia t i o n f r o m a h o r i z o n t a l fl i g h t p a t h a t i n j e c t i o n r e q u i r e s m o r e fuel to inject a given spacecraft x-jeight. at the required • ' velocity. The time span during each day that Surveyor can be laionbhed. ■ the launch window — is determined by the requirement that -the launch site at launch time and the Moon at arrival time be con t a i n e d i n t h e E a r t h - M o o n t r a n s f e r o r b i t p l a n e . W i t h t h e l a u n c h site moving eastward as the Earth revolves^, acceptable conditions occur only once each, day for a given plane. However^ by .alter ing the plane as a result of changing the launch azimuth., or direction of launch from the launch site, between an allowable 80 to 115 degrees-j, East of North, the launch window can be e x t e n d e d u p t o a s m u c h a s t w o h o u r s . -30 The lamch azimuth constraint of 8o to II5 degrees is imposed by the range safety consideration of allowing the initial launch phase only over the ocean^ not over land masses. The time of flight, or the time to landing, about 6l to 55 hours, is determined by the fact that Surveyor must reach the Moon during the viewing period of the prime Deep Space Net s t a ' c i o n a t G o I d s t o n e .

_ The trajectory is also influenced by the landing site seieccion. ^his selection is based on several considerations, one that a limitation is imposed on the first Surveyor flights 20ohe^spacecraft's aegrses off angle vertical. of approach There is to essentially the Moon must only not one'point exceed on one Moon for each launch day that a spacecraft can land vertically. . 20-degree consideration then, in effect, draws a con- thatf v a ro circle. u n d t h i s p o i n t . . S u r v e y o r m u s t l a n d . w i t h i n ® landing sites are further limited by the curvature of curvature of thejMoon. i-he trajectory engineer cannot pick a site, even If it Xalls fal v/ithinTatt "f-.'h -? ■ his 20-degree circle, if the curvature of the Moon vfilo. interfere with a direct communication line between the spacecraft and the Earth. Two other factors in landing site selection are smoothness 01 terrain and a requirement for Surveyor to land in the land ing area selected for the Apollo manned lunar mission.

L i g h t i n g c o n d i t i o n s o n Moon on arrival of the space- craft at a given landing site are determined by the launch day wnich, in turn, is controlled by the use of direct ascent tra jectories which limits the launch days available. In later missions using a parking orbit, the launch day can be picked to provide optimum, light conditions» Thus the trajectory engineer must tie together the direct ascent chapeteristics, the landing site location, the de'clln- flight time, in determining when tb' launch, in which direction, and at v;hat velocity. chosen trajectory also must not allow Surveyor to ^ Earth's shadow. Too long a period could 2 com.ponents or subsystems. In addition; The velocity of the spacecraft v/hen it arrives at the M o o n m u s t a l s o f a l l w i t h i n d e fi n e d , l i m i t s . T h e s e l i m i t s a r e defined by the retrorocket capability. The velocity relative to the Moon is primarily correlated with the flight time and the Earth-Moon distance for each launch day.

So,SoJ? a further f-arther requirementCD hQ on the trajectory engineer'.' is the amoui amountnt of oi fu fuel.el available to slow the Surveyor from its luna r a p p r o ach speed o zero v e locit y 1 3 f e et , trajectory must not yi - t a r e b e y o n d t h e . designed c apabilitie s 1

A1so i ncluded in le influence on the flight path and of the • • gravitaL u ation u i o nal a i a uattracti( - c r a c c i o n o i p r i m a r i l y t h e E a r t h a n d M o o n - a n d to .a lesser l e sser degreedegree thethe Sun^, Mercury^ Venus^ Mars, and Jupiter, lu is not expected that the launch can be Performed vfith buiiicxeno accuracy ro impact the Moon in exactly the desired area witnout a midcourse maneuver. The uncertainties invo'lved in a launch usually yield a trajectory or an injection velocity tnao vary slightly from the desired values. These uncertain- the^ies launch are due vehicleo to inherent To compensate, limitations lunar in the and guidance deep space"space- system of craxt have Lhe capability of performing a midcourse maneuver or ^rajectory correction. To alter the trajectory of a space- crai u it Is necessary to apply thrust in a specific direc'tlon to change^its velocityo The trajectory of a body at a point in space is basically determined by its velocity. For example, a simple midcourse maneuver might involve correcting a too high injection velocity. To correct for ' this the spacecraft would be commanded to turn in space until Its midcourse engines were pointing in its direction of travel. Tnrusb from the engines would slow the craft. Generally, " hov7ever, uhe midcourse is far more complex- and vjill involve changes Doth in velocity and its direction of travel. A certain amount of thrust applied in a specific direction can achieve both changes. Surveyor will use its thi-ee liquid luel vernier engines to alter its flight path in the midcourse maneuver, It will^be commanded to roll and then to pitch'or yaw j.n order zo point the three engines in the required-dlrec- tion. The engines then burn long enough to apply the change in v e l o c i t y r e q u i r e d t o a l t e r t h e t r a j e c t o r y. -32-

The change in the trajectory is very slight at this point and a tracking period of about 20 hours is required to determine the new trajectory. This determination also provide the data required to predict the spacecraft's an^-le ' ■•-of approach to the Moon, time of arrival, and its velocity as i t a p p r o a c h e s t h e M o o n . •

SURVEYOR A PLiailT MISSION Surveyor will be launched by an Atlas first stage and " Centaur second stage into a direct ascent lunar trajectory' A parking orbit will not be used in order to simDlify the de mands on the Centaur in its first operational mission.

A t l a s P h a s e All five of the Atlas engines — three main engines arid t w o v e r n i e r c o n t r o l e n g i n e s - - a r e i g n i t e d j u s t b e f o r e l i f t o f f . For the first two seconds, the Atlas-Centaur rises vertically and then for 13 seconds rolls to the desired flight plane ' . azimuth of from 85 to"115 degrees depending upon launch tiliie. After 15 seconds of flight, the vehicle begins pitching o v e r t h e d e s i r e d fl i g h t t r a j e c t o r y w h i c h c o n t i n u e s t h r o u g h o u t the Atlas-powered phase of :ne flight, AX, 14^ seconas axter liftoff, booster engine cutoff (BEC occurs vjhen an acceleration level bf |:).7 Gs is sensed. ThreeffiCO) seconds later the boosters are jettisoned and the sustainer- engine continues to propel the vehicle and- Centaur guidance s t a r t s s t e e r i n g t h e A t l a s . , After 176 seconds of flight, the four insulation panel around "cne H o a u r s o a g e a r e j e o u i s o n e d a n d . 2 7 s e c o n d s l a t e r t h e i i u t o e i d . x r.no* x a g H I R S IP jttisoned. e i ; i ; i s o n e a . Atlas A r i a s s u s t a i n e r e n g i n e c u t o f f - an(SECO)^occurs altitude of about at fuel 97 depletion miles. Two after seconds 240 seconds later. Atlas of flight and at C e n t a u r s e p a r a t e . ■ • •

C e n t a u r P h a s e

ofthe Centa 'Pel• l a n t s t o a e g r e e i - . l i q u i d hlydr y d r o' O g g e e n n a a s s i i t e n t e r s t h e t u r b o p u m p s ; Initial prechilliiig vjas performed. p e rformed on 0: the ground prior" to lift off using liquid helium I at a t■ -452 -452 degrees deg: Po, in order to mini mize in-flight ,nt propellantuse. use, • ,•

-more- -33-

A t 2 5 1 s e c o n d s a f t e r l i f t o f f a t a n a l t i t u d e o f a b o u t - . ' 104 mlleS;, Centaur's two engines are ignited for a planned- burn of 434 seconds. Shutdown occurs at about 685 seconc^s w h e n t h e g u i d a n c e s y s t e m s e n s e s t h a t t h e v e h i c l e h a s a t t a i n e d p r o i o e r v e l o c i t y .

Shortly after cutoff^ the programmer commands extension o f S u r v e y o r ' s l e g s a n d t w o o m n i d i r e c t i o n a l a n t e n n a s a n d o r d e r s t h e s p a c e c r a f t ' s t r a n s m i t t e r t o h i g h p o w e r. T h e programmer then commands separation of Surveyor from Centaur after some 757 seconds of flight at an altitude of 111 mil-es. Three spring-loaded cylinders force Centaur and Surveyor • apart. Five seconds later^ Centaur is rotated I80 degrees by its attitude control system in order to perform a retro- ' • m a n e u v e r t o i n s u r e t h a t s u n l i g h t r e fl e c t e d f r o m C e n t a u r w i l l not confuse SurveyorJ.s optical sensors and to prevent Centaur f r o m i m p a c t i n g t h e M o o n , Residual propellants are blown through Centaur^s engines for about four minutes resulting in Centaur and Surveyor being separated Dy ,at least 200 miles some five hours after launch, At liftoff plus 21 minutesJ Atlas-Centaur has completed aits^part highly of elliptical the mission. Earth orbits The Centaur extending stage more continues than 25O/OOO in miles into space and circling theEarth once each 11 days .with an orbital inclination of about 33,6 degrees. •

I n i t i a l S u r v e y o r P h a s e After separation from Centaur^ Surveyor gives an auto matic command to fire explosive blots to unlock the solar panel. A stepping motor moves the panel to a prescribed • ■ position. Solar panel deployment can also be commanded from the ground if the automatic sequence fails.

Surveyor then pex^forms an automatic Sun-seeking maneuver to stabilize the pitch and yaxv axes and to align its solar p a n e l w i t h t h e S u n f o r c o n v e r s i o n o f s u n l i g h t t o e l e c t r i c i t y to pov;er the spacecraft. Prior to this event the - spacecraft's m a i n b a t t e r y i s p r o v i d i n g p o w e r .

\ -more- The Sun acquisition sequence begins immediately after separation from Centaur simultaneously with the solar panel deplojrment^ The nitrogen gas jet systemj, which is activated at separation^ will first eliminate pitch;, roll and yaw . m o t i o n s r e s u l t i n g f r o m s e p a r a t i o n f r o m C e n t a u r. T h e n a ' s e q u e n c e o f c o n t r o l l e d r o l l a n d y a w t u r n i n g m a n e u v e r s i s commanded for Sun acquisitiono Sun sensors aboard Surveyor provide signals to the attitude control gas jets to stop'" t h e s p a c e c r a f t v / h e n i t i s p o i n t e d a t t h e S u n o O n c e l o c k e d ' • on the Sun^ the gas Jets pulse intermittently to control pjjxoLJxi i t c h a an n d y a w a t t i t u d e . P a i r s o f a t t i t u d e c o n t r o l J e t s a r e locatedted on each of the three landing legg s o f t h e s p a c e c r a f t , j . n t h e e v e n t ' t h e s p a c e c r a f t d o e s n o t p e r f o r m t h e S u n - seeking maneuver automatically, this sequence can be commanded f r o m t h e g r o u n d .

T h e n e x t c r i t i c a l s t e p f o r S u r v e y o r i s a c q u i s i t i o n ' o f its radio signal by the Deep Space Net tracking station at Johannesburg, South"Africa, the first DSN station to see S u r v e y o r a f t e r l a u n c h . 11 / i s c r i t i c a l a t t h i s p o i n t t o e s t a b l i s h t h e c o m m u n i c a t i o n s link with the .spacecraft to receive telemetry to quickly-determine the condition of...the spacecraft, for command capability to assure control, and for Doppler measurements from which velocity and t r a j e c t o r y a r e c o m p u t e d . . , '

'ansmitre r csan o n l y o p e r a t e athi■gh power f o r ' ' w i l y o n e hour .thout overheati:ng. It is expected. at the ground station will lO'ckon to the s p a c e - io signal V,rithin 40 minutes a fter launch and i.f i s i n d icat;ed. the transmitte:r c anbe co:mmanded ;o low

^ihe next major spacecraft event, after the Sun has been acquired is Canopus acquisition. Locking on the star Ca-nopus p r o v i d e s a f i x e d i n e r t i a l r e f e r e n c e f o r t h e ' r o l l a x i s . ; •

^ l a n j p u s A c q u i s i t i < Canopus acquisition is commanded from the ground about craisix^hours 1/ at after0.5 degree-per-second. launch. The gas When jets firethe sensor to roll sees .the the* sp'ace- predicted brightnessu i - x g j i i u u e s a of u i . Canopus o c i r i o j j u s (the ^ . u n e brightest D r i g n r e s t ; star s ' c a r in i n the t h e Southern Hemisphere) it orders the roll to stop and locks-' on oo the star. The brightness of the light source it is ■ ' telemetered to Earth to vex-ify that ^it is locked. Oxi \-/S.nopuis o Vopxx ob^TI 3.1SC 00 ppovicieci ^oy 3, gpouiict coirmand ordering a 3S0-degree roll and the plotting of each s e e s t h a t i s i r i t h e s e n s i t i v i t y - r a n g e o < a v e Q ^ D Te i Tnis o r e l a star u n c h map t o v can e r i i ' y be t h a compared t t h e s p a c v^rith e c r a f t a i s map'-pre- l o c k e d o i Canopus. .. -35-

Nov; properly oriented on the Sun and CanopuS:, Surveyor i s i n t h e c o a s t p h a s e o f t h e t r a n s i t t o t h e M o o n . S u r v e y o r is transmitting engineering data to Earth and receiving' commands via one of its omnidirectiona1 a n t e n n a s " Tracking data is obtained f r o m t■he pointing; d i rection of g r o u n d a n t e n n a and observed frCD CD o o P3 ,nge (Doppler). T h e s o l a r p a n e l ' a n d a d d i t : i s p r o viding el.ectrical po'Wer i o n a l p o w e r f o r p e a k demands is be in■ g p r o v i d e d by one of two b a t t e r i e s a b o a r d . The gas jet s a r■ e p u l s i n g i ntermittently to keep the ci aft . aligned onthe Sun and Can,opus. The engineering and tracking information is being received from Surveyor at one of the stations of the Deep Space Net. T h e d a t a i s c o m m u n i c a t e d t o t h e S p a c e P l i g h t O p e r a t i o n s ' F a c i l i ty at JPL v/here the flight path of the spacecraft is being c a r e f u l l y c a l c u l a t e d a n d t h e c o n d i t i o n o f t h e s p a c e c r a f t • c o n - \ t i n u o u s l y m o n i t o r e d . •

Midcourse Maneuver

Tracking data is used to determine hov; large a trajec tory correction must be made to land Surveyor in a given • t a r g e t a r e a . - T h i s t r a j e c t o r y c o r r e c t i o n / c a l l e d t h e m i d - c o u r s e m a n e u v e r / ' i s r e q u i r e d b e c a u s e o f u n c e r t a i n t i e s i n - t h e launch operation that prevent absolute accuracy in placing a s p a c e c r a f t o n a t r a j e c t o r y t h a t w i l l i n t e r c e p t t h e M o o n .

T h e m i d c o u r s e i s t i m e d t o o c c u r o v e r t h e G P l d s t o n e • station of the DSNj the tracking station nearest the SFGP at JPL,

The thrust f o r t h e m i d c o u r I ' s e i s p r•ovided by the spa .oCD eraft's three 1 iquid fuel vernie r e n g i n.es, Thlis wil1 b e'the fir' S t m idcourse m a n e u v e r t o b e performed w^ith th1 s t ype ■ of pro sion pul system. Total thrust 1evel is con•trolled toy an-ac- eelerometer at ^a c o n s t a n t a c c e l eration equal t0 0 ,1 Earth. g. Pol err nting ors a r e s e n s e d b y gy . r o s v ; h i ch can cau se the in- dividual engines t o c h a n g e t h r u st level to cor'rec t p itch and error s a yaw nd swivel one engine t o c o r rect r o■11 errors.

P l i g h t c o n t r o l l e r s d e t e r m i n e t h e r e q u i r e d t r a j e c t o r y c h a n g e t o b e a c c o m p l i s h e d b y t h e m i d c o u r s e m a n e u v e r . I n order to align the engines in the proper direction to .apply thenthrust^to pitch change or yaw the to trajectory. achieve this Surveyor alignment. is commanded Normally,-.two to roll, m a n e u v e r s a r e r e q u i r e d , a r o l l - p i t c h o r ' a r o l l - y a w .

-more-

-37-

T h e d u r a t i o n o f t h e f i r s t m a n e u v e r i s r a d i o e d t o t h e ; • s p a c e c r a f t ^ s t o r e d a b o a r d a n d r e - t r a n s m i t t e d " b a c k t o E a r t h f o r v e r i fi c a t i o n . A s s u r e d t h a t S u r v e y o r h a s r e c e i v e d t h e ■p r o p e r i n f o r m a t i o n ^ g r o u n d c o n t r o l l e r s c o m m ^ a n d i t t o p e r f o r m t h e fi r s t m a n e u v e r . T h e s e c o n d m a n e u v e r i s h a n d l e d i n t h e - s a m e f a s h i o n . W h e n t h e m o t o r s a r e p r o p e r l y a l i g n e d ^ t h e • ' n u m b e r o f s e c o n d s o f r e q u i r e d t h r u s t i s t r a n s m i t t e d t o t h ' e ; - s p a c e c r a f t s s t o r e d , v e r i f i e d a n d t h e n e x e c u t e d . . . •

I n t h e e v e n t o f a f a i l u r e o f t h e a u t o m a t i c t i m e r a b o a r d " t h e s p a c e c r a f t w h i c h c h e c k s o u t t h e d u r a t i o n o f e a c h m a n e u v e r turn and firing period, each step in the sequence can be per f o r m e d b y c a r e f u l l y t i m e d g r o u n d c o m m a n d s .

A f t e r c o m p l e t i o n o f t h e m i d c o u r s e m a n e u v e r , . S u r v e y o r r e a c q u i r e s t h e S u n a n d C a n o p u s . A g a i n S u r v e y o r i s i n t h e c r u i s e mode and the next critical event will be the terminal maneu ver. "

Terminal Sequence

T h e fi r s t s t e p s t a r t s a b o u t . 1 0 0 0 m i l e s a b o v e t h e M o o n ^ S ' s u r f a c e . T h e e x a c t d e s c e n t m a n e u v e r s d e p e n d o n t h e fl i g h t . " p a t h a n d o r i e n t a t i o n o f t h e S u r v e y o r v ; i t h r e s p e c t t o t h e M o o r i a n d t h e t a r g e t a r e a . N o r m a l l y t h e r e w i l l b e a r o l l f o l l o w e d , b y a y a w o r a p i t c h t u r n . A s i n t h e m i d c o u r s e m a n e u v e r , . t h e d u r a t i o n t i m e s o f t h e m a n e u v e r s - a r e r a d i o e d t o t h e s p a c e c r a f t a n d t h e g a s j e t s fi r e t o e x e c u t e t h e r e q u i r e d r o l l a n d p i t c h a n d y a w . T h e o b j e c t o f t h e m a n e u v e r s i s t o a l i g n t h e m a i n . • r e t r o r o c k e t w i t h t h e a p p r o a c h v e l o c i t y v e c t o r . T o p e r f o r m t h e m a n e u v e r s , t h e s p a c e c r a f t b r e a k s i t s l o c k o n t h e S u n a r i d C a n o p u s . A t t i t u d e c o n t r o l i s m a i n t a i n e d b y i n e r t i a l s e n s o r s » G y r o s s e n s e c h a n g e s i n t h e a t t i t u d e a n d o r d e r t h e g a s j e t ' s , t o fire to maintain the correct attitude -until the retrorocket i s i g n i t e d ,

With the main retro aligned, the altitude marking radar i s a c t i v a t e d b y g r o u n d c o m m a n d a t a p p r o x i m a t e l y 2 0 0 m i l e s a b o v e t h e M o o n ' s s u r f a c e . A l l s u b s e q u e n t t e r m i n a l e v e n t s - a r e a u t o m a t i c a l l y c o n t r o l l e d b y r a d a r a n d t h e P l i g h t C o n t r o l P r o g r a m m e r . T h e a u x i l i a r y b a t t e r y i s c o n n e c t e d t o h e l p t h e m a i n b a t t e r y. s u p p l y t h e h e a v y l o a d s r e q u i r e d d u r i n g d e s c e n t .

-more- -^38-

SURVEYOR TERMINAL' DESCE

CSUISE ATTITUDE TO LUNAR SURFACE (Approximate AlHtudes and Velocities Given)

PRE-RETRO MANEUVER 30 MIN. BEFORE TOUCHDOV/N ALIGNS MAIN RETRO WITH FLIGHT PATH

MAIN RETRO START BY ALTITUDE MARKING RADAR WHICH EJECTS FROM NOZZLE, CRAFT STABILIZED BY VERNIER ENGINES AT 60 Ml. ALTITUDE, 6,100 MPH

MAIN RETRO BURNOUT AND EJECTION, jOQmh VERNIER RETRO SYSTEM TAKEOVER AT 25,000 FT, 240 MPH

Kr- VERNIER ENGINES SKUTOFF AT 13 FT, 3'A MPH

TOUCHDOWN AT 10 MPH -39-

At approxima t e l y 6 0 m i.1es siant r a ng e f r o m t h e :Moon' s- surface t he marking radar s tarts t;he F1ight Control Program- mer whic h then co u n t s d o v m a previo'usly stored delay time and comma ad s i gnltion o f t h e t hiree liquid fueled, throttleable veraler en glnes and then th.e solid propellant main retro'.' ... The veraier engines maintain a c onstant spacecraft attit'u d e d u r i n g the maia r etro t :riod in a m a hrusting pe J n n e r s i m i l a r to that employed d-uring midcourse thrusfcing. T h e s p a c e c r a f t i s t r a v e l Ip.g at a PProximat e l y 6 ^ 0 0 0 m iles pe:r h o u r. The main retro burn s 0 u z in 40 s e c o n d s a t a bout 25 miles a b o v e t h e surface afte r r 0 Qucing the velocity toabOU't 2 5 0 m i l e s p e r h 'our, -The casing of the main retro is separated from the spacecraft -".on command from the programmer 12 seconds after burnout by ex p l o s i v e b o l t s a n d f a l l s f r e e . After burnout the Plight Control Programmer controls .. • the thrust level of the vernier engines until the Radar Al'- timeter and Doppler Velocity Sensor (RADVS) locks up on its r e t u r n s i g n a l s f r o m t h e M o o n ' s s u r f a c e , '

Deseen t i s t h e n c o ntrolled by t h e R . A . D V S a n d the vernier

ineso eng S i g n a l s f r o m RADVS are pr'ocesse d . b y t h e flight "con- tro1 e l ect r o n i c s t o t h r ottle the th.ree ve r n i e r e ng i n e s r e d u c - veloci ing t y a s t h e a l t i tude decreases, At 14 feet above the surface . si U r v e y o r i s s l owed to five feet p e r s e c o n d . A t . t h i s point the e n g i n e s a r e s h u t o ff and the. spacecraft free falls to the surface.

The 1anding impact i s c iushioned b y crushable foot pads and shocka b s o r b e r s o n e .ach 'of the three l e g s a n d b y c r u s h a - Die honeyeo m b a l u m i n u m block,s u n d e r the ,frame, in -case of an • exceptional l y h a r d l a n d i ng.

Post-lan

-more- 40-

T h e s o l a r p a n e l a n d h i g h g a i n p l a n a r a r r a y a n t e n n a . a r e aligned with the Sun and Earth. If the high gain antenna;''is s u c c e s s f u l l y. o p e r a t e d t o l o c k o n E a r t h , t r a n s m i s s i o n o f " 6 0 0 l i n e t e l e v i s i o n p i c t u r e s w i l l b e g i n . I f i t „ i s n e c e s s a r y - t o operate throiAgh one of the lox^ gain/ omnidirectional antennas, a d d i t i o n a l 2 0 0 l i n e p i c t u r e s w i l l b e t r a n s m i t t e d . ' •

T h e l i f e t i m e o f S u r v e y o r o n t h e . s u r f a c e w i l l b e d e t e r m i n e d b y a n u m b e r o f f a c t o r s : t h e p o w e r r e m a i n i n g i n > , h - e . b a t t e r i e s i n t h e e v e n t t h a t t h e S u n i s n o t a c q u i r e d b y t h e s o l a r p a n e l , s p a c e c r a f t r e a c t i o n t o t h e i n t e n s e h e a t o f . t h . e l u n a r d a y , e t c . T h e fi r s t S u r v e y o r s a r e n o t e x p e c t e d t o l a s t t h r o u g h a l u n a r n i g h t .

-Qore- ATLAS-CENTAUR AND SURVEYOR TEAMS

NASA HEADQUARTERS, WASHINGTON, D,C

D r . H o m e r E . N e w e l ! Associate Administrator for Space Science and Applications

Robert P. Garbarinl D e p u t y A s s o c i a t e A d m i n i s t r a t o r for Space Science and Applica tions (Engineering)

Oran VJ, Nicks

Benjamin Milwitzky Surveyor Program Manager v. L, Johnson Director, Launch Vehicle and Propulsion Programs

R. Duff Ginter Centaur Program Manager

JET PROPULSION LABORATORY, PASADENA, CALIF,

D r , W i l l i a m " H . P i c k e r i n g Director

D e p u t y D i r e c t o r . •

Surveyor Project Manager Deputy Project Manager for ;Hughes Aircraft Co. Operations v i a i K e r E . G ; Deputy Project Manager for Mission Requirements, Plans and Operations

eonard Jaff. Project Scientist

)erhardt Rechtin A s s i s t a n t L a b o r a t o r y D i r e c t o r f o r uisition

S u r v e y o r Tr a c k i n g a n d D a t a Systems Manager

Larkin J P L E n g i n e e r i n C h a r g e . , G o l d s t o n e

Bucklev P i o n e e r S t a t i o n M a n a g e r, G o l d s t o m

-more- Fahnestock JPL DSN Resident in Australia

Tidbinbilla Station Manager."

o. Teroecic JPL DSN Resident in South 'Africa

Johannesburg Station Manager

J-.EWIS RESEARCH CENTER, CLI

Abe Sixverstein Director

Luna in Associate Director for Development imund R. Jonash Centaur Project Manager

KENNEDY SPACE CENTER.

R, Debu Director

Robert H. Gray Director, of Unmanned Launch' Operations

HUGHES AIRCRAFT COMPANY^ CUjLVER CITY, CALIF,

Dr. Fred P. Adler Vice President and Manager S p a c e S y s t e m s D i v i s i o n

PrRMi^.RAT. n'YNAMlCS/CONVAIR, SANDIEGO. CALIF,

Grant L. Hansen V i c e P r e s i d e n t J L a u n c h Ve h i c l e Programs

PRATT AND VJHITNEY AIRCPJIFT DIVISION OF UI-JITED AIRCRAFT CO V'/EST PALP.i BEACH, FLA: ^^

Richard Anchutze Rii-lO Engine Project MiYianager'

HONEYVJELL, INC,, ST. PETERSBURG, FLA.

R. B. Foster jntaur Guidance Program Manage]

-more- MAJOR SUBCONTRACTORS

SURVEYOR

AiResearch Division Gro-und support equipment Garrett Corporation Torrance^ Calif.

Nitrop^en tanks SegundOj Calif,

A i r ' c e K D i v i s i o n Propellant tanks Fansteel Hetallureical Corp. J orap t on J Calif,

Atnuex Tape recorder

XteaV;OOQ i CUlo i t y , C a l :

Astrodata Time clocks Santa Ana, Calij

B e l l & H o w e l l C o m p a n y Camera lens Chicago, Illo

B e n d i x C o r p , " l i a n d i n g d y n a m i c s s t a b i l i t y P r o d u c t s A e r o s p a c e D i v i s i o n South Bend, Indo

Borg-Warner Tape recorder Santa Ana, Calif

Branson Optical alignment equipment. K a n s a s C i t y , K a n ,

Carleton Controls H e l i u m r e g u l a t o r Buffalo, N,Y,

E a g l e - P i c h e r C o m p a n y A u x i l i a r y b a t t e r i e s Joplin, Mo.

E l e c t r i c S t o r a g e B a t t e r y Main batteries Raleign, N.C,

Electro-Developm'ent. Corp. Strain gage electronics Seattle, V/ash.

Electro-Mechanical Research )ecommutators Sarasota, Pla.

Endevco Corporation Accelerometei Pasadena, Calif,

-more- General Electro Dynamics Vidicon tuti( G a r l a n d J Te x .

Heliotek > o l a r r a o d u l e i Sylniar^ Calif

H i - S h e a r C o r p . S e p a r a t i o n d e v i c e ' Torrance, Calif,

lokanson Mob. temperature control unil S a n t a M o n i c a ^ C a l i f ,

Squibs Hollister^ Calif

Honeywell Tape recorder/reproducer - / O S A n g e l e s J C a l i f .

Kearfott Division Gyros General Precision Company Little Falls, N.J, i^inet:ics M a i n p o w e r s w i t c h Solana Beach, Calif.

L e a r S i e g l e r T«V. photo recorder Santa Monica, Calif,

Menasco G a s t a n k s L o s A n g e l e s , C a l i f ,

Met; com Magnetron assembly Salem, Mai

Motorola, Inc. Subcarrier' oscillatorE M i l i t a r y E l e c t r o n i c s D i v i s i o n Scottsdale, Ariz,

N a t i o n a l W a t e r L : L a n d i n g s h o c k a b s o r b e r Kalamazoo, Mich,

N o r t h r o p / N o r a i r „ Hawthorne, Calif,

Ryan Aeronautical Co, R a d a r a l t i t u d e D o p p l e r v e l o c i t y San Diego, Calif, sensor

-more- - 4 5 - ; '•

Sanborn L. F, oscillograph ' " V/altham^ Mass.

Scientific-Atlanta S y s t e m t e s t s t a n d Atlanta, Ga.

J • S i n g e r - M e t r i c s F. M. calibrator Bridgeport, Mass.

Thiokol Chemical Corp. Main retro engine ' . Elkton Division Elk ton:, Md.

Thiokol Chemical Corp. V e r n i e r p r o p u l s i o n s y s t e m R e a c t i o n M o t o r s D i v i s i o n Denville/No J.

Telemetries Simulator Santa Ana^ Calif.

United Aircraft Corp. S u b c a r r i e r o s c i l l a t o r . " • Norden Division S o u t h a m p t o n J P e n n .

Vector • S u b c a r r i e r o s c i l l a t o r S o u t h h a m p t o n J P e n n .

A T L A S . •

R o c k e t d y n e D i v . o f MA-5 propulsion system North American Aviation Inc. (associate prime) C a n o g a P a r k ^ C a l i f .

Thiokol Chemical Corp. L O X a n d f u e l s t a g i n g v a l v e s R e a c t i o n M o t o r s D i v .

H a d l e y C o . I n c . V a l v e s r e g u l a t o r s a n d d i s c o n nect coupling •

F l u i d g e n i c s I n c . Regulators

General Precision Inc. D i s p l a c e m e n t g y r o s Kearf ott Dlv S a n M a r c o s J C a l i f .

Honey v;e 11 Inc. Rate gyros Aeronautical Div.

-more- -46-

Pt -p-f-v,h D n-; i r a e n s i o n I n c Commutatorj B e n d i x C o r p . B e n d i x P a c i f i c D i v „ Te l e p a k s a n d o s c i l l a t o r

Pairchild-Hiller LOX fuel and drain valve; S t r a t o s V / e s t e r n D i v

) r ^ n T > o n Transuoers and potentiotneters

Wa s h i n g t o n S t e e l C o S t a i n l e s s s t e e l Washington, Pa.

CENTAUR

General Dynaoiics/Pt. Worth Insulation panels and nose' •Uiv. J Ft. V-/orth, T'ex» fairing • P e s c o P r o d u c t s D i v ^ o f Boost pumps for RL-10 engines Borg-Warner Corp. Bedford, Ohio

B e l l A e r o s y s t e m s C o . - o f Attitude control system' Bell Aerospace Corp. B u f f a l o , N , . y .

Liquidometer Aerospace Div. Propellant utilization system Siraraonds Precision Products, Inc. Long Island, N.Y.

General Precision Inc. Computer for inertial guidance Aerospace Gp,, Kearfott s y s t e m . • Div., San Marcos, Calif.

G o o d y e a r A e r o s p a c e D i v. o f Handling trailer Goodyear Tire and Rubber Co, Akron, Ohio Systems ana Instrumen".s Div. Destructors of Bulova Watch Co . Flushing, N.Y.

Consolidated Controls Corp S a f e a n d a r m i n i t i a t o r E l S e g u n d o , C a l i f .

-more- -47-

V

: B o r g - W a r n e r C o n t r o l s D i v , o f I n v e r t e r B o r g - W a r n e r C o r p . Santa Ana^ Calif.

Sippican Corp. M o d u l e s f o r ' p r o p e l l a n t u t i l i Marion, Mass. z a t i o n s y s t e m , '

G e n e r a l E l e c t r i c C o , Turbine L y n n J M a s s .

V i c k e r s D i v . o f H y d r a u l i c p u m p s S p e r r y R a n d C o r p . T r o y J M i c h .

Edcliff Instruments, Inc T r a n s d u c e r s a n d s w i t c h e s ' Monrovia, Calif.

Rosemount Engineering Co, Transducers Minneapolis, Minn.'

S c i e n t i fi c D a t a S y s t e m s Computers Santa Monica, Calif.

¥o 0. Leonard,Inc Hydrogen and oxygen vent Pasadena, Calif. valves

r>