Surveyor B Press Kit

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f NAII lNAI AIR rlAITIl(K AND SPA(C ADMINISTRATION WOr) -415,SVASfiIN(Ji()N D ( ?0'46 TELS WO )pFOR RELEASE: WEDNESDAY A.M.September 14, 1966

RELEASE NO: 66-248

PROJECT: SURVEYOR B(T o be launched no earlierE than Sept. 20, 1966)

ES CONTENTS

GENERAL RELEASE-------------------------------------1-4SURVEYOR BACKGROUND-----------------------------------5SURVEYOR B SPACECRAFT--------------------------------6Frame, Mechanisms and Thermal Control--------------6-8Power Subsystem-----------------------------------8-9Telecommunications---------------------------------10-11Propulsion-----------------------------------------11-12Flight Control Su bsy stem --------------- ------- 12-14Television--------------------------------------- 14Engineering Instrumentation------------------------15ATLAS-CENTAUR (AC-7) LAUNCH VEHICLE-------------------16-17LAUNCH VEHICLE FACT SHEET------------- -------------- 17

ATLAS-CENTAUR FLIGHT SEQUENCE-------------------------18TRACKING AND CO:vrUNICATION----------------------------19-20TRAJECTORY--------------- -------------- 21-23

Atlas Phase---------------------------------------- 24Centaur Phase------------------------------------ 25Initial Surveyor Phase-----------------------------25-26Canopus Acquisition--------------------------------27Midcourse Maneuver---------------------------------27-28Terminal Sequence----------------------------------28-29Post-Landing Events--------------------------------29-30ATLAS-CENTAUR AN D SURVEYOR TE A M S----------------------31-33MAJOR SUBCONTRACTORS----------------------------------34-38

T -End-9/9/66


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NATIONAL AERONAUTICS AND SPACE ADMINISTRATION WO 2-4155WASHINGTON, D.C. 20546 WO3-6925

September 14, 1966RELEASE NO: 66-2482N D SURVEYORLAUNCH SET

SEPTEMBER 20

The United States wil l continue its program of scoutingpotential astronaut landing sites on the Moon with th e laLuchof a sister spacecraft to th e highly successful Surveyor I dur-in g a four-day period beginning Sept. 20.

This will be th e second of seven Surveyor missions intendedto develop th e technology of soft-landing on th e Moon and toprovide scientific and engineering data to support th e Apollomanned landing program.

Two National Aeronautics and Space Administration space-craft have begun the manned landing site survey of th e Moon:

-- Surveyor I soft-landed on June 1 and returned more than11,000 high resolution television pictures of its landing areacentered at 2.5 degrees South latitude and 43 degrees West3ongitude.

-- Lunar Orbiter I photographed nine potential mannedlanding sites across th e equator from Aug. 18 to Aug. 29. Thesephotographs are currently being analyzed.

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This second Surveyor (designated Surveyor B) will be aimedto land in Sinus Medii, a maria at the center of the visibleface of the Moon. This area was the fifth selected site photo-graphed by Lunar Orbiter I.

Surveyor B will be launched by an Atlas-Centaur rocket fromComplex 36 at Cape Kennedy, Fla. The spacecraft will be injecteddirectly into a lunar trajectory for a 63-hour trip to the Moon.

At the Moon, Surveyor must accomplish the critical terminaldescent and soft landing. For this purpose it is equipped witha solid propellant retrorocket and three throttleable liquid fuelvernier engines; a flight programmer, autopilot and anolog com-puter; and radars to determine altitude and rate of descent.

The main braking force is provided by the retrorocket. Afterit is jettisoned, data from the radars are processed by the on-board computer to throttle the verniers automatically so thatSurveyor touches down softly on the lunar surface.

Surveyor B will face an additional factor not experiencedby Surveyor I in its terminal descent and landing. The SurveyorI landing site was chosen for a nearly vertical descent -- ap-proaching at an angle only six degrees off the perpendicular.

However, Surveyor B will approach the Moon an an angle of23 degrees from the vertical. Successful accomplishment of sucha soft landing will demonstrate the ability of the spacecraft tosoft-land in the eastern quadrant of the Moon.

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-3-Surveyor B will be equipped identically to Surveyor I,

carrying a survey television camera and engineering instrumen-tation. It will also obtain data on the radar reflectivity,mechanical properties, and thermal conditions of the lunarsurface.

At launch, Surveyor B will weigh 2,204 pounds. The retro-motor, which will be jettisoned after burnout, weighs 1,395pounds. After expenditure of liquid propellants and use ofattitude control gas, the landed weight of Surveyor on th eMoon will be about 620 pounds.

On the first possible launch date, Tuesday Sept. 20, th ewindow will open as early as 6:51 a.m. EDT and close at 8:33 a.m.This would make its arrival at the Moon about 9:30 p.m. EDT,Thursday Sept. 22.

The Surveyor program is directed by NASA's Office ofSpace Science and Applications. Project management is assignedto NASA's Jet Propulsion Laboratory operated by the CaliforniaInstitute of Technology, Pasadena. Hughes Aircraft Co., undercontract to JPL, designed and built ihe Surveyor spacecraft.NASA's Lewis Research Center, Cleveland, is responsible for theAtlas first stage booster and for the second stage Centaur, bothdeveloped by General Dynamics/Convair, San Diego, Cal. Launchoperations are directed by Kennedy Space Center, Fla.

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-4-Tracking and communication with the Surveyor is the re-

sponsibility of the NASA/JPL Deep Space Network (DSN). Thestations assigned to the Surveyor program are Pioneer, at Gold-stone in California's Mojave Desert; Johannesburg, South Africa;Ascension Island in the South Atlantic; and Tldbinbilla nearCanberra, Australia. Data from the stations will be trans-mitted to JPL's Space Flight Operations Facility in Pasadena,the command center for the mission.

(END OF GENERAL RELEASE; BACKGROUND INFORMATION FOLLOWS)


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-5-SURVEYOR BACKGROUND

Surveyor I accomplished the first fully-controlled softlanding on the Moon on June 1, 1966, after a 63-hour, 36-minuteflight from Cape Kennedy.

In the six weeks that followed, the spacecraft's surveytelevision camera took more than 11,000 high-resolution picturesof the lunar surface and transmitted them to Earth tracking sta-tions. Resolution in some of the closeups was one-half milli-meter, or about one-fiftieth of an inch.

From the pictures were derived representative colors ofthe Moon's surface, an accurate view of the terrain up to oneand one-half miles surrounding the Surveyor, the effect of land-ing a spacecraft upon the lunar surface and pictorial evidenceof the minor lunar environmental damage to the spacecraft itself.

America's first remote lunar observatory took a number ofpictures of the solar corona (the Sun's upper atmosphere), theplanet Jupiter and the stars Sirius and Canopus.

Surveyor I landed at a velocity of about 7.5 miles perhour at a position 2.411 degrees south of the lunar equatorand 43.345 degrees West longitude in the southwest portion ofthe Ocean of Storms.

The television pictures showed that the spacecraft cameto rest on a smooth, nearly level site on the floor of a ghostcrater. The landing site was surrounded by a gently rollingsurface studded with craters and littered with fragmental debris.The crestlines of low mountains were visible beyond the horizon.

By July 13, Surveyor I's 42nd day on the Moon, the space-craft had survived the intense heat of the lunar day (250 degreesF.), the cold of the two-week-long lunar night (minus 260 degreesF.), and a second full lunar day. Total picture count was: firstlunar day -- June 1 - 14 -- 10,338; second day -- July 7 - 13 --812.

Despite a faltering battery not expected to endure therigors of the lunar environment over an extended period, Sur-veyor continued to accept Earth commands and transmit TV pic-tures through the second lunar sunset. It acted upon more than100,000 Earth commands during the mission.

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SURVEYOR B SPACECRAFTFrame, Mechanisms and Thermal Control

The tr iangular aluminum frame of the Surveyor providesmounting surfaces and attachments fo r the landing gear, mainretrorocket, vernier engines and associated tanks, thermalcompartments, antennas and other electronic and mechanicalassemblies.

It is constructed of thin-wall aluminum tubing, with th emembers interconnected to form th e tr iangle. A mast, whichsupports the planar array high-gain antenna, and single solarpanel, is attached to th e top of the frame. The basic frameweighs less than 60 pounds and installation hardware weighs23 pounds.

The Surveyor stands about 10 feet high and, with its tri-pod landing gear extended, can be placed within a 14-footcircle. A landing le g is hinged to each of the three lowercorners of th e frame and an aluminum honeycomb footpad is a t-tached to the outer end of each leg. An airplane-type shockabsorber and telescoping strut are connected to the frame sothat the legs can be folded into the nose shroud during launch.Touchdown shock also is absorbed by the footpads and by thehydraulic shock absorbers which compress with the landing load.Blocks of crushable aluminum honeycomb are attached to thebottom of th e spaceframe a t each of its three corners to ab-sorb part of th e landing shock.

Two omnidirectional, conical antennas are mounted on theends of folding booms which are hinged to th e frame. Thebooms remain folded against th e frame during launch until re-leased by squib-actuated pin pullers and deployed by torsionsprings. The antenna booms are released only after th e land-in g legs are extended and locked in posit ion.

An antenna/solar panel posit ioner atop the mast supportsand rotates th e planar array antenna and solar panel in eitherdirection along four axes. This freedom of movement enablesthe orientation of the antenna toward Earth and th e solarpanel toward th e Sun.

Two thermal compartments house sensitive electronic ap-paratus for which active thermal control is needed throughoutthe mission.

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SURVEYOR

SOLAR PANEL

OMNIDIRECTIONALANTENNA i HIGH-GAINSURVEY -- ANTENNATV CAMERA

STAR CANOPUSSENSOR

OMNIDIRECTIONALANTENNA

THERMALLYCONTROLLEDCOMPARTMENT

RADAR ALTITUDE- VERNIER PROPELLANTDOPPLER VELOCITY PRESSURIZING GASANTENNA (HELIUM) TANK

AUXILIARY BATTERYVERNIER ENGINE- ATTITUDE CONTROL GAS(NITROGEN) TANK

RETRO ROCKET MOTORALTITUDE MARKING RADARANTENNALANDING GEAR

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The equipment in each compartment Is mounted on a ther-mal tray that distributes heat throughout th e compartment.An insulating blanket of 73 sheets of aluminized Mylar issandwiched between each compartment's inner shell and th eouter protective cover. The compartment tops are coveredby mirrored glass to help radiate th e heat.

On Surveyor I, one square of this glais was found cracked,-- apparently by heat--after exposure to one lunar day and onelunar night.Compartment A, which maintains an internal temperature

between 40 degrees and 125 degrees F., houses the centralcommand decoder, boost regulator, central signal processor,signal processing auxillar,, engineering signal processor,and low data rate auxiliary.

Both compartmenlts contain sensors fo r reporting tempera-ture measurements by telemetry to Earth, an a heater assembliesto maintain th e thermal trayc above their allowable minimums.The compartments are kept below the 129-degree maximum withthermal switches which provide a conductive path to the ra-diating surfaces for Putomatic dissipation of electricallygenerated heat. Comi 'tment A contains nine thermal switchesand compartment B, six. The thermal shell weight of compart-ment A is 25 pounds, and compartment B, 18 pounds.

Passive temperature control is provided for all equipmentnot protected by th e compartments through th e use of paintpatterns and polished surfaces.

Twenty-nine pyrotechnic devices mechanically release orlock the switches and valves associated with th e antennas,landing leg locks, roll actuator, retrorocket separationattachments, helium and nitrogen tanks, shock absorbersand retromotor detonator. Some are actuated by command fromthe Centaur stage programmer prior to spacecraft separationfrom the Centaur, others by ground command.

A spherical solid propellant retrorocket fits within thecenter cavity of th e frame and supplies th e main thrust fo rslowing th e spacecraft on approach to th e Moon. The unit isattached a t three points on th e frame near th e landing leghinges, with explosive nut separation points for ejection af-ter burnout. The motor case, made of high-strength steel andinsulated with asbestos and rubber, is 36 inches in diameter.Including th e molybdenum nozzle, th e unfueled engine weighs142 pounds. With propellant, the weight is about 1 395 pounds,more than 60 per cent of th e total spacecraft weight.

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-8-Electrical harnesses and cables interconnect the space-

craft subsystems to provide correct signal and power flow. Theharness connecting the two thermal compartments is routedthrough a thermal tunnel to minimize heat loss from the com-partments. Coaxial cable assemblies, attached to the frameby brackets and clips, are used for high frequency transmis-sion.

Electrical connection with the Centaur stage is establishedthrough a 51-pin connector mounted on the bottom of the framebetween two of the landing legs. The connector mates with theCentaur connector when the Surveyor is mounted on the launchvehicle. It carries pre-separation commands from the Centaurprogrammer and can handle emergency commands from the block-house console. Ground power and prelaunch monitor circuitsalso pass through the connector.

Power SubsystemThe power subsystem collects and stores solar energy,

converts it to usable electric voltage, and distributes it tothe other spacecraft subsystems. This equipment includes thesolar panel, a main battery and an auxiliary battery, an aux-iliary battery control, a battery charge regulator, main powerswitch, boost regulator, and an engineering mechanisms auxiliary.

The solar panel is the spacecraft's primary power sourcedur-ng flight and during operations in the lunar day. It con-sists of 3,960 solar cells arranged on a thin, flat surface ofapproximately nine square feet. The solar cells are groupedin 792 separate modules and are connected in series-parallelto guard against complete failure in the event of a singlecell malfunction.

The solar panel is mounted at the top of the Surveyorspacecraft's mast. Winglike, it is folded away during launchand deployed after the space 2raft has been ejected into lunartrajectory.

When properly oriented during flight, the solar panelsupplies about 89 watts wiich is most of the power requiredfor the average operating load of all on-board equipment.

During operation on the lunar surface, the solar panelcan be adjusted by Earth command to track the Sun within afew degrees, so that the solar cells always remain perpen-dicular to the solar radiation.

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YROLL ATTITUDE JET NOZLZLE

OMNIDIRECTIONAL ANTENNA A

LANDING LEG I

POWER SUPPLY AND MODULATOR VERNIER THRUST CHAMBER I (GIMBALLEO)VERNIER THRUST CHAMBER FUEL TANK

VERNIER THRUST CHAMBER OXIDIZER TANKVELOCITY SENSING ANTENNA

AL'IMETER VELOCITY SENSING ANTENNA\ COMPARTMENT

COMPARTMENT AFLIGHT CONTROL SENSOR GROUP

VERNIER THRUST CHAMBER FUEL TANK < SIGNAL DATA CONVERTER 00VERNIER THRUST CHAMBER 2 (FIXED) VERNIER THRUST CHAMBER OXIDIZER TANKVERN IER TVRUST CTAMSER C |DL\.^

SOLAR COLLECTOR VERNIER THRUST C'IAMBER FUEL TANK

LANDING LEG 2 LANDING LEG 3

ACCELEROMETER AMPLIFIERSTRAIN GAGE AMPLIFIER

TV CAMERA 4 4VERNIER THRUST CHAMBER

OXIDIZER TANK TVCAMERA 3 / |TV PHOTOMETRIC CHART ATTITUDE CONTROL ITCH AND YAWATTITUDE JET NOZZLE (2)

PRESSURIIAT RYNANK (Na) T H T CH\RTA TAN ( VERNIER THRUST CHAMBER 3 (FIXED)TV PHOTOMETRIC CHART

VERNIER FUEL SYSTEM OMNIDIRECTIONAL ANTENNA BPRESSURIZATION TANK (HI) O 5 10 IS 20 25 3SO 5 40 45 50 SS 40SCALE INCHES

MIDCOURSE CONFIGURATIONANTENNA AND SOLAR PANNEL POSITIONEROMITTED FROM VIEW FORCLARITY

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-9-On the Moon, the solar panel is designed to supply aminimum of 77 watts power at a temperature of 140 degrees F.,and a minimum of 57 watts at a temperature of 239 degrees F.A 14-cell rechargeable, silver-zinc main battery is thespacecraft's power reservoir. It is the sole source of powerduring launch; it stores electrical energy from the solar panel

during transit and lunar-day operations, and it provides a back-up source to meet peak power requirements during both of thoseperiods. Fully charged, the battery provides 3,800 watt-hoursat a discharge rate of 1.0 amperes. Battery output is approx-imately 22 volts direct current for all operating and environ-mental conditions in temperatures from 40 degrees to 125 de-grees F.The auxiliary battery is a non-rechargeable, silver-zincbattery contained in a sealed magnesium cannister. It providesa power backup for both the main battery and the solar panelunder peak power loading or emergency conditions. This bat-tery has a capacity of from 800 to 1,000 watt-hours, dependingupon power load and operating temperature.The battery charge regulator and the booster regulatorare the two power conditioning elements of the spacecraft'selectrical power subsystem. The battery charge regulatorcouples the solar panel to the main battery for maximum con-version and transmission of the solar energy necessary tokeep the main battery at full charge.It receives power from the solar panel's varying outputvoltage and delivers this power to the main battery at a con-stant battery terminal voltage. The battery charge regulator

includes sensing and logic circuitry for automatic batterycharging whenever battery voltage drops below 27 volts.The booster regulator unit receives unregulated powerfrom 17 to 27.5 volts direct current from the solar panel,the main battery, or both, and delivers a regulated 29 voltsdirect current t- the spacecraft's three main power trans-mission lines. These three lines supply all the spacecraft's

power needs, except for a 22-volt unregulated line whichserves heaters, switches, actuators, solenoids and electroniccircuits which do not require regulated power or providetheir own regulation.

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-10-"elecommunicatlons

Communications equipment aboara Surveyor serves threefunctions: providing transmission and reception of radiosigna.s; decoding commands sent to thie spacecraft: and se-lecting and converting engineering ana televi:;l.tn data intoa form suitable for transmission.The first group includes the three pntennas: ,- hign-gain, directional anterL.. and two low-gain, omnidirectionalantennas; two transmitters; and two receivers with transponderinterconnections. Dual transmitters and receivers are usedfor reliaollity.The high-gain antenna transmits 600-line television data.The low-gain antennas receive ground comnmand3 and transmitother data including 200-line television data from the space-craft. Either lo -gain antenna can be connected to eitherreceiver. The transmitters can be switched to either low-gainantenna or to tne high-gain antenna and can operate at lowor high power levels. Thermal control of tn e ci.ree antennasis passive, dependent on surface coatings to keep temperatures.-itnirt acceptable l imits .The command decoding group can handle up to 25b commandseither direct (which control on-off operations) or quantita-tive commands (which control time interval operations). Eacnincoming command is checked in a central command decoderwhich will reject a command, and signal the rejection to Earthif the structure of the command is incorrect. Acceptarce ofa command is also radioed to Earth. The command is tnen sentto subsystem decoders that translate the birary informationinto an actuating signal for the function command sucn assquib firing or changing data moues.Processing of most engineering data, (temperatures, vol-tages, currents, pressures, switch positions, etc.) is handledoy the en!ineering signal processor or the auxiliary processor.Ther/e are more than 200 engineering measurements of t,,e space-craft. None are continuously reported. There are four com-mutators in the engineering signal processor to permit sequ.n-tial sampling of selected signals. The use of a commutatordepends on the type and amount of informacion required duringvarious flight sequences. Each commutatoir can be commanded'nto ooeration at any time and at any of five bit rates: 17.2

137., 550, 1,100 or 4,400 bits-per-second.

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Commutated signals from trie engineering processorsare converted to 10-oit data woras oy an analog-to-digitalconverter in trie centra] signal processor and relayed tothe transmitter. Tne low-bit rates are normally used withtransmissions over the low-gain antennas and the low-cowerlevels of the transmitters.

Video data from the television camera are fed directlyto the transmitters only during nigh-power operation andrequire the use of the hign-gain antenna when in the oOO-line mode.

PropulsionThe propulsion system consists of three liquid fuel

vernier rocket engines and a solid fuel retrorocket. Theverniers are used for the midcourse maneuver as well as inth e terminal lunar landing sequence.

The vernier engines are supplied by three fuel tankra:..d three oxidizer tanks. There is one pair of tainks, fueland oxidizer, for each engine, The fuel and oxidizer in eachtank is contained in a bladder, helium stored under pressiureis used to deflate the bladders and force the fuel and oxi-dizer into the feed lines.

The oxidizer is nitrogen tetroxide with 10 per centnAtric oxide. The fuel is monomethy1hydrazine monohydrate.An ignition system is not required for the verniers as thefuel aid oxidizer are hypergolic, i.e., they burn on contact.The throttle range is 3C to 104 pounds of thrust.

The main recrorocket is used at the beginning of theterminal descent to the lunar surface and slows the space-craft from an approacn velocity of about 6,000 mph to approxi-mately 250 mph. On the Surveyor 1 mission, a 38-second burnof Its retromotor slo'.ed the spacecraft to 267 mph,

The retro burns an aluminum, ammonium-perchlorate andpolyhydro carbon, case-bonded composite-type propellant. Thenozzle has a graphite throat and a laminated plastic exit cone.The case is of high-strength steel insulated with asbestosand silicon dioxide-filled buna-N rubber to maintain the caseat a low temperature level during firing.

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Engine thrust varies from 8,000 to 10,000 pounds over atemperature range of 50 to 70 degrees F. Passive thermalcontrol, insulating blankets and surface coatings, will main-tain the grain above 50 degrees F. It is fired by a pyrogenigniter. The main retro weighs approximately 1,395 poundsand is spherical in shapes 36 inches in diameter.

Flight Control SubsystemFlight control of Surveyor, control of its attitude and

velocity from Centaur separation to touchdown on the Moon,is provided by: primary Sun sensor, automatic Sun acquisitionsensor, Canopus sensor, inertial reference unit, altitudemarking radar, inertia burnout switch, radar altimeter andDoppler velocity sensors, flight control electronics, andthree pairs of cold gas jets. Flight control electronicsincludes a digital programmer, gating and switching, logicand a signal data converter for the radar altimeter and Dop-pler velocity sensors.

The information provided by the sensors is processedthrough logic circuitry in the flight control electronics toyield 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 controlelectronics indicating whether or not they are illuminated bythe Sun. This information is used to operate the gas jets tomaneuver the spacecraft until the Sun sensors are on a directline with the Sun. The primary Sun sensor consists of fivecadmium sulphide photo-conductive cells. During flight,Surveyor may deviate slightly from pointing directly at theSun. Such deviations are continuously corrected by signalsfrom the primary sensor to the flight electronics activatingthe pitch and yaw gas jets to again center the sensors on theSun.

Sun acquisition is required before locking on the starCanopus. Gas jets are used to center the star sensor onCanopus, so as to maintain roll axis attitude during cruisemodes. If star or Sun lock is lost, control is automaticallyswitched from optical sensors to gyros which sense changes inspacecraft attitude inertially.

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The inertial reference unit is also used during eventswhen th e optical sensors cannot be used--midcourse maneuverand descent to the lunar surface. This device senses changesin attitude of th e spacecraft and in velocity with three gyrosand an accelerometer. Information from th e gyros is processedby the control electronics to operate gas jets to change ormaintain the desired attitude. During lunar descent thrustphases, th e inertial reference uni t controls vernier enginethrust levels by differential throttling fo r pitch and yawcontrol and swiveling one engine for roll control. The ac -celerometer controls th e total thrust level.

The altitude marking radar will provide th e signal fo rfiring of th e main retro. It is located in the nozzle of th eretromotor and is ejected when th e motor ignites. The radarwill generate a signal a t about 60 miles above th e lunar sur-face. The signal starts the programmer automatic sequenceafter a pre-determined period (directed by ground command);th e programmer then commands vernier and retro ignition andturns on the radar alt im eter and Doppler velocity sensors.

The inertia burnout switch will close when th e thrustlevel of the main retromotor drops below 3.5 g, generatinga signal which is used by th e programmer to command jettison-in g of th e retromotor and switching to control by th e radaralt imeter and Doppler velocity sensors.

Control of th e spacecraft after main retro burnout is byth e radar altim eter and Doppler velocity sensors. Two radardishes are involved. An altim eter/velocity sensing antennaradiates two beams and a velocity sensing antenna radiatestwo beams. Beams 1, 2, and 3 give vert ical or transversevelocity. Beam 4 provides altitude or slant range informa-t ion. Beams 1, 2, and 3 provide velocity data by adding th eDoppler shift (frequency shift due to velocity) of each beamin th e signal data converter. The converted range and velocitydata is fed to th e gyros and gating logic which in turn con-trol the thrust signals to th e vernier engines.

The flight control electronics provides fo r processingsensor information into telemetry and to actuate soacecraftmechanisms. It consists of control circuits, a comland de-coder and an AC/DC electronic conversion unit. The program-mer controls timing of main retro phase and generates 're-cision time delays for attitude maneuvers and midcourse ve-loolty correction.

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The attitude jets provide attitude control to the space-craft from Centaur separation to main retro burn. The gas jetsystem is fed from a spherical tank holding 4.5 pounds of ni-trogen gas under high pressure, regulating and dumping valvesand three pairs of opposed gas jets with solenoid operatedvalves for each jet. One pair of jets is located at the endof each of the three landing legs. The pair on one leg con-trol motion in E horizontal plane, imparting roll motion tothe spacecraft. The other two pairs control pitch and yaw.

TelevisionThe Surveyor B spacecraft will carry one survey tele-vision camera. The camera is mounted nearly vertically,pointed at a movaole mirror. The mirror can swivel 360 de-grees and can tilt from a position where it reflects a por-tion of a landing leg to above the horizon.The camera can be focused, by Earth command, from fourfeet to infinity. its iris setting, which controls 6;3amount of light entering the camera, can adjust automaticallyto the light level or can be commanded from Earth. The camerahas a variable focal length lens whicrh an be adjusted toeither narrow angle, 6.4 X 6.4 field of view, or to wide-angle, 25.4 x 25.4 field of view.A focal plane shutter provides an exposure time of 150milliseconds. The shutter can also be commanded open for anindefinite length of time. A sensing device coupled to theshutter will keep it from opening if the light level is toointense. A too-high light level could occur from changes inthe area of coverage by the camera, a change in the angle ofmirror, in the lens aperture, or by changes in Sun angle.

The same sensor controls the automatic iris setting. Thesensing device can be overridden by ground command.The camera system can provide either 200- or 600-linepictures. The latter require that the high-gain directionalantenna and the high power level of the transmitter are bothworking. Tbhe 600-line mode provides a picture each 3.6seconds and the 200-line mode every 61.8 seconds.A filter wheel can be commanded to one of four positionsproviding clear, colored or polarizing filters.Surveyor B, like Surveyor I, will carry a downward-looking television camera mounted on the lower frame of thespacecraft. However, this camera is not planned to be turned

on during this mission.

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-!4a-SURVEYOR SURVEY TV CAMERA

HOOD MIRROR

-MIRRORMIRROR AZIMUTH ELEVATIONDRIVE MOTOR DRIVE ASSEMBLY

VARIABLE FILTER WHEELFOCAL LENGTH ASSEMBLYLENS ASSEMBLYFOCUSPOTENTIOMETER

IRISPOTENTIOMETER

S TVIDICON TUBESHUTTERASSEMBLY

VIDICONRADIATORELECTRONICCONVERSIONUNIT

ELECTRICALZ CONNECTOR


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-15-Engineering Instrumentation

Engineering evaluation of the Surveyor test flightswill be made by an engineering payload including an auxiliarybattery, auxiliary processor for engineering information, andinstrumentation consisting of extra temperature sensors,strain gauges for gross measurements of vernier engine re -sponse to flight control commands and shock absorberloadingat touchdown, and extra accelerometers for measuring structuralvibration during main retro burn.

The auxiliary battery will provide a backup for bothemergency power and peak power demands to the main batteryand the solar panel. It is not rechargeable.The auxiliary engineering signal processor provides twoadditional telemetry commutators for determing the performanceof the spacecraft. It processes the information in the samemanner as the engineering signal processor, providing addi-tional signal capacity and redundancy.

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-16-ATLAS-CENTAUR (AC-7) LAUNCH VEHICLE

The Atlas-Centaur has been developed by NASA to launchmedium-weight scientific spacecraft on lunar and interplanetarymissions. The vehicle has a current payload capability of about2,500 pounds for direct-ascent missions to the Moon and 1,300pounds for missions to Venus and Mars.

Centaur was declared operational by NASA in 1965 for direct-ascent lunar missions. The vehicle scored a complete success onits first operational mission, Surveyor I, which was launchedfrom Cape Kennedy by the AC-10 vehicle on May 30, 1966.

Surveyor I was injected on its lunar-transfer trajectorywith such accuracy that the mid-course velocity correction re-quired by the spacecraft to land within 10 miles of its pre-selected target was only about 8 mph. (Surveyor has a maximum"lunar miss" correction capability of 111.85 mph). Even withouta mid-ccurse correction, Surveyor I would have landed only 250miles from its target.

Configuration of the AC-7 vehicle is the same as the Atlas-Centaur 10.

Yet to be completed in the Centaur vehicle development pro-gram is complete demonstration of a two-burn capability whichwill permit Centaur to fly into a circular Earth orbit, coastfor a brief period, then restart its engines and inject a space-craft on a lunar or planetary trajectory.

Although some payload capability is sacrificed using theEarth parking orbit method -- due to added equipment and theloss of liquid oxygen vented during the coast phase -- two dis-tinct advantages are gained: (1) Surveyor launches can be con-ducted during winter months when lunar lighting conditions areunfavorable for direct-ascent missions, and (2) launch windows(periods during which the payload must be launched to intercepta target) are widened considerably.

It is expected this dual-burn capability will be demon-strated during the last planned Centaur vehicle developmentflight -- AC-9 -- scheduled later this year. Following thatmission, several Surveyoi spacecraft are scheduled to be launchedto the Moon from an Earth parking orbit.

An improved Atlas (SLV-3C), will increase the Atlas-Centaur'spaylc d capability to about 2,900 pounds for lunar missions and1,800 pounds for Venus and Iars. The JLV-3C is schedlied to beused initially on the AC-13 mission.

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SURVEYOR 1 -Nose fairing

1 ,Electronic packages-LH 2 tank

------ Insulation panelsCENTAUR STAGE


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Major modifications to Atlas-Centaur to increase its pay-load capability include lengthening of the Atlas by four feet,which will increase total propellant capacity by some 20,000pounds, and uprating of the Atlas booster and sustainer engines.

LAUNCH VEHICLE FACT SHEET(All figures approximate)

Liftoff Weight: 303,000 lbs.Liftoff Height: 113 feetLaunch Complex: 36-A

Atlas Booster Centaur StageWeight (at liftoff) 263,000 lbs. 37.500 lbs.

(less payload)Height 75 feet (including 48 feet (with

interstage adapter) fairing)Thrust 389,000 lbs. (sea 30,000 lbs. (at

level) altitude)Propellants RP-1 (fuel) and Liquid hydrogen

liquid oxygen (fuel) and liquid(oxidizer) oxygen (oxidizer)

Propulsion MA-5 system (2-165,000 Two RL-10 engineslb. thrust booster en-gines, 1-57,000 lb.sustainer engine, and2-1,000 lb. vernierengines)

Velocity 5560 mph at BECO 23,700 mph at in-7600 mph at SECO jection

Guidance Pre-programmed auto- Inertialpilot through BECO

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ATLAS-CENTAUR FLIGHT SEQUENCEEVENT NOMINAL ALTITUDE SURFACE RANGE VEL/MPH

TIME, SEC. STATUTE MI. STATUTE MI.1. Liftoff 0 0 0 02. Booster engine cutoff 142 37 49 5,5603. Booster, engine jettison 145 39 54 5,6304. Jettison insulation panels 176 58 100 6,2005. Jettison nose fairing 203 75 144 6,7306. Sustainer engire cutoff 237 97 205 7,600

S 7. Atlas-Centaur separation 239 98 210 7,6008. Centaur engine start 24 8 104 228 7,600 o9. Centaur engine cutoff 688 147 1740 23,700

10. Spacecraft separation 754 115 2160 23,70011. Cenaur Reorientation 759 113 2190 23,70012. Centaur retrothrust 994 202 3680 23,700

(Launch vehicle mission completed at T plus 21 minutes)Fii ;res used are approximate but typical of potentia ltrajectories fo r AC-7 depending on day of launch.


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SURVEYOR FLIGHT PROFILE

SEPARAliDN ATLAUNCH PLUS12 1 M'. .-A

SCANOPUS ACQUISITIONN ABOUT LAUNCH PLUS 6 HRSSCOMPLETES CRUISE ATTITUDE PRE-RETRO MANEUVER

" STABILIZATION 30 MIN. BEFORE LANDING

SUN --- -

SUN ACQUISITION IABOUT LAUNCH STAR 6j1 HR S OCPLUS I HR CANO.US S 1 H SUN AND CANOPUS REACQUISITION

IMMEDIATELY AFTER MIDCOURSEMIDCOURSE CORRECTION CORRECTIONABOUT LAUNCH PLUS 15 HRS 4 HRS

O/24 HRS

/ MOONAT LAUNCH


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TRACKING AND COMMUNICATIONThe flight of th e Surveyor spacecraft from injection tothe end of the mission will be monitored and controlled by the

Deep Space Network (DSN) and the Space Flight Operations Facil-ity (SFOF) operated by the Jet Propulsion Laboratory.

Some 300 persons will be involved in Surveyor flight moni-toring and control during peak times in the mission. On theSurveyor I flight more than 100,000 ground commands were re-ceived and acted on by the spacecraft during flight and afterth e soft landing.

The Deep Space Network consists of six permanent space com-munications stations in Australia, Spain, South Africa, and Cal-ifornia; a spacecraft monitoring station at Cape Kennedy; and aspacecraft guidance and command station at Ascension Island inthe South Atlantic.

The DSN ."fcilities assigned to the Surveyor project arePioneer at 'oldstone, Cal.; Johannesburg, South Africa; Tidbin-billa in ti,. Canberra Complex, Australia; and Ascension Island.

The Goldstone facility is operated by JPL with the assist-ance of the Bendix Field Ernineering Corp. The Tidbinbilla fa-cility is operated by the Australian Department of Supply. TheJohannesburg facility is operated by the South African govern-ment through the Council for Scientific and Industrial Researchand the National Institute for Telecommunications Research. TheAscension Island DSN facility is operated by JPL with Bendixsupport under a cooperative agreement between the United King-dom and the U.S.

The DSN uses a ground communications system for operationalcontrol and data transmission between these stations. The groundcommunications system is a part of a larger net (NASCOM) whichlinks all of the NASA stations around the world. This net isunder the technical direction of NASA's Goddard Space FlightCenter, Greenbelt, Md.

The DSN supports the Surveyc- flight in tracking the space-craft, receiving telemetry from the spacecraft, and sending itcommands. The DSN renders this support to all of NASA's un-manned lunar and planetary spacecraft from th e time tney areinjected into planetary orbi t until they complete their missions.

Stations of the DSN receive the spacecraft radio signals,amplify them, process them to separate the data from the carrierwave and transmit required portions of the data to the commandcenter via high-speed data lines, radio links, and teletype. Thestations are also linked with the center by voice lines. All in-coming data are recorded on magnetic tape.

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The information transmitted from the DSN stations to theSFOF is fed into large scale computer systems which translatethe digital code into engineering units, separate informationpertinent to a given subsystem on the spacecraft, and drivedisplay equipment in the SFOF to present the information tothe engineers on the project. All incoming data are again re-corded in the computer memory system and are available on demand.

Equipment for monitoring television reception from a Sur-veyor spacecraft is located in the SFOF.Some of the equipment is designed to provide quick-look

information for decisions on commanding the camera to changeiris settings, change the field of view from narrow angle towide angle, change focus, or to move the camera either hori-zontally or vertically. Television monitors display the pic-ture being received. The pictures are received line by lineand each line is held on a long persistence television tube un-til the picture is complete. A special camera system producesprints of the pictures for quick-look analysis.

Other equipment will produce better quality pictures fromnegatives produced by a precision film recorder.

Commands to operate the camera will be prepared in advanceon punched paper tape and forwarded to the stations of the DSN.They will be transmitted to the spacecraft from the DSN stationon orders from the SFOF.

Three technical teams support the Surveyor television mis-sion in the SFOF: one is responsible for determining the tra-jectory of the spacecraft including determination of launchperiods and launch requirements, generation of commands for themidcourse and terminal maneuvers; the second is responsible forcontinuous evaluation of the condition of the spacecraft fromengineering data radioed to Earth; the third is responsible forevaluation of data regarding the spacecraft and for generatingcommands controlling spacecraft operations.

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TRAJECTORYThe determination of possible launch days, specific timesduring each day, and th e Earth-Moon trajectories for th e Sur-veyor spacecraft is based on a number of factors.A primary consideration is th e direct ascent launch as op-posed to th e parking orbit technique. A parking orbit is morecomplex in that it requires the Centaur second stage to fire itsengines to achieve the initial circular orbit, coast in orbitabout th e Earth and then to fire its engines the second time toaccelerate the spacecraft to the required lunar transit velocity.In these first operational missions Centaur will not be re-quired to perform the double burn. After separation from theAtlas booster, the Centaur will ignite its engines which willcontinue to burn until the lunar transit velocity has beenreached. This velocity varies slightly with launch day andtime but is approximately 24,500 mph.Use of the direct ascent trajectory limits each monthly

launch period to those days when the Moon is at negative de-clinations -- that is, in positions, relative to Earth, belowthe Earth's equator.The days of the month available for launching are deter-minted oy the attainable range in the flight path angle of theCentaur at injection -- that point in time when the Centaurengines cease firing and the required velocity for a lunarflight has been reached. The flight path angle is the angleat which Centaur is moving relative to a horizontal plane of theEarth below. Changes in this angle compensate for the dailychange in the position of the Moon.The attainable range in the angle is determined by thefuel available in the A'las-Centaur dombination, as both ve-hicles are involved in the angle of Centaur at injection. Anydeviation from a horizontal flight path at injection requiresmore fuel to inject a given spacecraft weight at the requiredvelocity.The time span during each day that Surveyor can be launched-- the launch window -- is determined by the requirement thatthe launch site at launch time and the Moon at arrival time becontained in the 7arth-Moon transfer orbit plane. With thelaunch site moviing eastward as the Earth revolves, acceptableconditions occur only once each day for a given plane. However,

by altering the plane as a result of changing the launch azi-muth, or direction of launch from the launch site, between anallowable 85 to 115 degrees, East of North, the launch windowcan be extended as much as two hours.-more-


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SURVEYOR TRAJECTORIES TO THE MOON

PARKING ORBIT TRAJECTORYON DIRECT ASCENT LAUNCH WITH 2 FIRINGS OF SECOND STAGE ENGINES,END OF SECOND STAGE ENGINES' AND COAST PHASE BETWEEN, SURVEYOR CANSINGLE FIRINC ALWAYS ENDS REACH ANY MOON POSITION ABOVE OR BELOWNEAR CAPE ABOVE EQUATOR EARTH'S EQUATOR

DIRECT ASCENT TRAJECTORY*

COAST PHASE 1

ON PARKING ORBIT LAUNCH _END OF SECOND FIRING OF /SECOND STAGE ENGINES CANOCCUR BELOW EQUATOR BY .INCREASING COAST TIMEBETWEEN FIRINGS -

DOTTED LINES SHOW MAXIMUM AMOUNT DIRECT ASCENTTRAJECTORY CAN BE ADJUSTED TO REACH DIFFERENTMOON POSITIONS .-

MOON S ORBIT'EARLY SURVEYORS WILL BE LAUNCHED ON DIRECTASCENT TRAJECTORIES


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The launch azimuth constraint of 85-115 degrees is imposedby the range safety consideration of allowing the initial phaseonly over the ocean, not over land masses.

The time of flight, or the time to landing, about 63 hours,is determined by the fact that Surveyor must reach the Moon dur-ing the viewing period of the prime Deep Space Net station atGoldstone.

The trajectory is also influenced by the landing site se-lection. This selection is based on several considerations, onethat a limitation is imposed on the first Surveyor flights thespacecraft's angle of approach to the Moon must not exceed 25 de-grees off vertical. There is essentially only one point on theMoon for each launch day that a spacecraft can land vertically.

The 25-degree consideration then, in effect, draws a con-straining circle around this point. Surveyor must land withinthat circle.

The landing sites are further limited by the curvature ofthe Moon. The trajectory engineer cannot pick a site, even ifit falls within his 25-degree circle, if the curvature of theMoon will interfere with a direct communication line between thespacecraft and the Earth.

Two other factors in landing site selection are smoothnessof terrain and a requirement for Surveyor to land in the landingarea selected for the Apollo manned lunar mission.

Lighting conditions on the Moon on arrival of the spacecraftat a given landing site are determined by the launch day which,in turn, is controlled by the use of direct ascent trajectorieswhich limits the launch days available. In later missions usinga parking orbit, the launch day can be picked to provide optimumlight conditions.

Thus the trajectory engineer must tie together the directascent characteristics, the landing site location, the declina-tion of the Moon and flight time, in determing when to launch,in which direction, and at what velocity.

His chosen trajectory also must not allow Surveyor to re-main too long in the Earth's shadow. Too long a period couldresult in malfunction of components or subsystems. In addition,the Surveyor must not remain in the shadow of the Moon beyondgiven limits.

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The velocity of the spacecraft when it arrives at the Moonmust also fall within defined limits. These limits are definedby the retrorocket capability. The velocity relative to the Moonis primarily correlated with the flight time and the Earth-Moondistance for each launch day.

So, a further requirement on the trajectory engineer is theamount of fuel available to slow the Surveyor from its lunar ap-proach speed of nearly 6000 miles per hour to nearly zero velocity13 feet above the Moon's surface. The chosen trajectory must notyield velocities that are beyond the designed capabilities of thespacecraft propulsion system.

Also included in trajectory computation is the influence onthe flight path and velocity of the spacecraft of the gravita-tional attraction of primarily the Earth and Moon and to a lesserdegree the Sun, Mercury, Venus, Mars, and Jupiter.

It is not expected that the launch can be performed withsufficient accuracy to impact the Moon in exactly the desiredarea without a midcourse maneuver. The uncertainties involvedin a launch usually yield a trajectory or an injection velocitythat vary slightly from the desired values. These uncertaintiesare due to inherent limitations in the guidance system of thelaunch vehicle. To compensate, lunar and deep space spacecrafthave the capability of performing a midcourse maneuver or tra-jectory correction. To alter the trajectory of a spacecraft itis necessary to apply thrust in a specific direction to changeits velocity. The trajectory of a body at a point in space isbasically determined by its velocity.

For example, a simple midcourse maneuver might resolvecorrecting a too high injection velocity. To correct for thisthe spacecraft would be commanded to turn in space until itsmidcourse engines are pointing in its direction of travel.Thrust from the engines would slow the craft. Generally, how-ever, the midcourse is far more complex and will involve changesboth in velocity and its direction of travel.

A certain amount of thrust applied in a specific directioncan achieve both changes. Surveyor will use its three liquidfuel vernier engines to alter its flight path in the midcoursemaneuver. It will be commanded to roll and then to pitch oryaw in order to point the three engines in the required direc-tion. The engines then burn long enough to apply the change invelocity required to alter the trajectory.

The change in the trajectory is very slight at this pointand a tracking period of about 20 hours is required to determinethe new trajectory. This determination will also provide thedata required to predict the spacecraft's angle of approach tothe Moon, time of arrival, and its velocity as it approaches theMoon.

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-24-SURVEYOR B/ATLAS-CENTAUR FLIGHT PLAN

Surveyor B will be launched by Atlas-Centaur 7 into adirect-ascent lunar trajectory.The primary task for Atlas-Centaur 7 on the Surveyor Bflight is to inject the Surveyor spacecraft on a lunar-transfer trajectory with sufficient accuracy so that themidcourse maneuver correction required some 15 to 20 hoursafter liftoff does not exceed 165-feet-per-second or 111.85

miles-per-hour.The Centaur stage also is required to perform a retro-maneuver to avoid impacting the Moon and to prevent Surveyor'sstar seeker from mistaking the spent Centaur for its orientingstar, Canopus.

Atlas PhaseAll five of the Atlas engines--three main engines and twovernier control engines--are ignited prior to liftoff. Forthe first two seconds the Atlas-Centaur will rise verticallyand then roll for 13 seconds to the desired flight planeazimuth of 83 to 115 degrees depending upon time of launch.After 15 seconds of flight, the vehicle begins pitchingover to the desired flight trajectory which continues through-out the Atlas-powered phase of the flight.At T plus 142 seconds, booster engine cutoff (BECO) occurswhen an acceleration level of 5.7 g is sensed. Three seconds laterthe booster engine package is jettisoned. The sustainer enginecontinues to propel the vehicle and Centaur inertial guidancebegins its steering functions.After 176 seconds of flight, the four insulation panelswhich surround the Centaur tank are jettisoned. These panelsare used to minimize boiloff of the liquid hydrogen duringflight through the atmosphere. Twenty-seven seconds later, thenose fairing which surrounds the Surveyor spacecraft is jettisoned.Atlas sustainer engine cutoff (SECO) occurs after 237

seconds of flight at an altitude of about 97 miles. Twoseconds later Atlas and Centaur are separated by a flexibleshaped charge which severs the interstage adapter. Eightretrorockets on the Atlas are fired to increase the rateof separation.

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Centaur PhaseAt T plus 248 seconds, Centaur's two hydrogen-oxygenRL-10 engines are ignited for a planned burn of 440 seconds.Centaur ignition occurs about 104 miles altitude when thevehicle is 228 miles down range traveling at a velocity of7,600 mph.After 688 seconds of flight, Centaur's propulsion systemis shut down when the guidance system senses that the vehiclehas attained proper velocity. Injection velocity varies withtime and day of launch, but is approximately 23,700 mph.Shortly after Centaur engine shutdown, the programmercommands Surveyor's legs and two omnidirectional antennas toextend, and orders the spacecraft's transmitter to high power.At T plus 754 seconds and an altitude of 115 miles, the pro-grammer commands separation of Surveyor from Centaur. Threespring-loaded cylinders force the spacecraft and vehicle apart.Five seconds after spacecraft separation, Centaur isrotated 180 degrees by its attitude control system in order toperform a retromaneuver. Unused propellants are then blownthrough the rocket thrust chambers to increase separation ofCentaur and Surveyor--the result is that some five hours laterthey are at least 200 miles apart. This eliminates thepossibility that Surveyor's star tracker will mistakenly lockon Centaur. Centaur's trajectory is thereby altered to preventit from impacting the Moon.At liftoff plus 21 minutes, Atlas-Centaur will have.com-pleted its mission and the Centaur stage will continue in ahighly elliptical Earth orbit, extending more than 276,000 milesinto space and circling the Earth once each 12 days.

Initial Surveyor PhaseAfter separation from Centaur, Surveyor gives an auto-matic command to fire explosIve bolts to unlock the solarpanel. A stepping motor moves the panel to a prescribed po-sition. Solar panel deployment can also be conmanded from theground if the automatic sequence fails.Surveyor then performs an automatic Sun-seeking maneuverto stabilize the pitch and yaw axes and to align its solarpanel with the Sun for conversion of sunlight to electricityto power the spacecraft. Prior to this event the spacecraft'smain battery is providing power.

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The Sun acquisition sequence begins immediately afterseparation from Centaur simultaneously with the solar paneldeployment. The nitrogen gas je t system, which is activatedat separation, will first eliminate pitch, roll and yaw motionsresulting from separation from Centaur. Then a sequence ofcontrolled roll and yaw turning maneuvers is commanded forSun acquisition. Sun sensors aboard Surveyor provide signalsto the attitude control gas jets to stop the spacecraft whenit is pointed at the Sun. Once locked on the Sun, the gasjets pulse intermittently to control pitch and yaw attitude.Pairs of attitude control jets are located on each of the threelanding legs of the spacecraft.In the event the spacecraft does not perform the Sun-seeking maneuver automatically, this sequence can be commandedfrom the ground.The next critical step for Surveyor is acquisition of itsradio signal by the Deep Space Net tracking stations atAscension Island and Johannesburg, South Africa, the first

DSN stations to see Surveyor after launch.It is critical at this point to establish the communicationslink with the spacecraft to receive telemetry to quicklydetermine the condition of the spacecraft, for command capa-bility to assure control, and for Doppler measurements fromwhich velocity and trajectory are computed. Johannesburgacquired Surveyor I about 28 minutes after launch.The transmitter can only operate at high power forapproximately one hour without overheating. It is expected,however, that a ground station will lock on to the spacecraft'sradio signal within 40 minutes after launch and if overheating

is indicated, the transmitter can be commanded to low power.The next major spacecraft event after the Sun has beenacquired is Canopus acquisition. Locking on the star Canopusprovides a fixed inertial reference for the roll axis.

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Canopus AcquisitionCanopus acquisition is commanded from the ground aboutsix hours after launch. The gas jets roll the spacecraftat 0.5 degree-per-second. When the sensor sees the pre-dicted brightness of Canopus (the brightest star in the South-ern Hemisphere) it orders the roll to stop and locks on the

star.The brightness of the light source it is seeing istelemetered to Earth to verify that it is locked on Canopus.

Verification can also be provided by a ground command orderinga 360-degree roll and the plotting of each light source thesensor sees that is in the sensitivity range of the sensor.This star map can be compared with a map prepared before launchto verify that the spacecraft is locked on Canopus.Now properly oriented on the Sun and Canopus, Surveyoris in the coast phase of the transit to the Moon. Surveyor

transmits engineering data to Earth and receives commands viaone of its omnidirectional antennas. Tracking informationis obtained from the pointing direction of ground antennaand observed frequency change (Doppler). The solar panel pro-vides electrical power, and additional power for peak demandsis provided by one of two batteries aboard. The gas jetS pulseintermittently to keep the craft aligned on the Sun and Canopus.Engineering and tracking information is received fromSurveyor at one of the stations of the Deep Space Network. Thedata are communicated to the Space Flight Operations Facilityat JPL where the flight path of the spacecraft is calculatedand the condition of the spacecraft is continuously monitored.

Midcourse ManeuverTracking information is used to determine how large atrajectory correction must be made to land Surveyor in agiven target area. This trajectory correction, called themidcourse maneuver, is required because of uncertainties inthe launch operation that prevent absolute precision in placinga spacecraft on a trajectory that will intercept the Moon.The midcourse is timed to occur over the Goldstonestation of tr DSN, the tracking station nearest the SFOF at

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SURVEYOR MIDCOURSE CORRECTION

CRUISE ATTITUDE

' - 4 YAW (OR PITCH) TURN

Q STARCANOPUS

SUN AND CANOPUSSREACQUISITIONROLL TURN ,

VERNIER ENGINES BURN OFI r/o-


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The thrust for the midcourse is provided by the space-craft's three liquid fuel vernier engines. Total thrustlevel is controlled by an accelerometer at a constantacceleration equal to 0.1 Earth g. Pointing errors aresensed by gyros which cause the individual engines to changethrust level to correct pitch and yaw errors and swivelone engine to correct roll errors.

Flight controllers determine the required trajectorychange to be accomplished by the midcourse maneuver. Inorder to align the engines in the proper direction to applythrust to change its trajectory, Surveyor is commanded toroll, then pitch or yaw to achieve this alignment. Normally,two maneuvers are required, a roll-pitch or a roll-yaw.

The duration of the first maneuver is radioed to thespacecraft, stored aboard and re-transmitted to Earth forverification. Assured that Surveyor has received the properinformation, ground controllers command it to perform thefirst maneuver. The second maneuver is handled in the samefashion. When the motors are properly aligned, the number ofseconds of required thrust is transmitted to the spacecraft,stored, verified and then executed.

In theevent of a failure of the automatic timer aboardthe spacecraft which checks out the duration of each maneuverand firing period, each step in the sequence can be performedby carefully timed ground commands.

After th e midcourse maneuver is completed, Surveyor re-acquires the Sun and Canopus. Again Surveyor is in th e cruisemode and the next critical event will be the terminal maneu-ver.

Terminal SequenceThe first step starts about 1000 miles above th e Moon's

surface. The exact descent maneuvers depend on the flightpath and orientation of Surveyor with respect to the Moonand the target area. Normally there will be a roll followedby a yaw or a pitch turn. As in the midcourse maneuver, theduration times of the maneuvers are radioed to the spacecraftand the gas jets fire to execute the required roll and pitchand yaw. The object of the maneuvers is to align the mainretro rocket with the approach velocity vector. To performthe maneuvers, the spacecraft breaks its lock on the Sun andCanopus. Attitude control is maintained by inertial sensors.Gyros sense changes in the attitude and order the gas jets tofire to maintain the correct attitude until the retrorocket isignited.

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SURVEYOR TERMINAL DESCENTTO LUNAR SURFACECRUISE ATTITUDE -(Approximate Altitudes and Velocities Given)

PRE-RETRO MANEUVER 30 MIN.BEFOR. TOUCHDOWN ALIGNSMAIN RETRO WITH FLIGHT PATH

, MAIN RETRO START BY ALTITUDEMARKING RADAR WHICH EJECTSFROM NOZZLE, CRAFT STABILIZEDBY VERNIER ENGINES AT52 MI. ALTITUDE, 5,900 MPH

I

S MAIN RETRO BURNOUT AND EJECTION,VERNIER RETRO SY.TEM TAKEOVER AT37,000 FT, 400 MPH

SIVERNIER ENGINES SHUTOFF -AT 14 FT , 31/2 MPH

' TOUCHDOWN AT 8 MP H


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With the main retro aligned, the altitude marking radaris activated by ground command about 200 miles above the Moon'ssurface. All later terminal events are controlled automaticallyby radar and the flight control programmer. The auxiliarybattery is connected to help the main battery supply theheavy loads required during descent.At approximately 60 miles slant range from the Moon's

surface, the marking radar starts the flight control programmerwhich counts down a previously stored delay time and thencommands ignition of the three liquid fueled, throttleable ver-nier engines and the solid propellant main retro. The vernierengines maintain a constant spacecraft attitude during the mainretro thrusting period, in a manner similar to that employedduring midcourse thrusting.The spacecraft is traveling at approximately 6,000 milesper hour. The main retro burns out in 40 seconds at about 25miles above the surface of the Moon after reducing thevelocity to about 250 miles per hour. The casing of the mainretro is separated from the spacecraft on command from the

programmer 12 seconds after burnout by explosive bolts, andfalls free.After burnout the flight control programmer controls thethrust level of the vernier engines until the Radar Altimeterand Doppler Velocity Sensor (RADVS) locks onto its return sig-nals from the Moon's surface.Descent is then controlled by the RADVS and the vernierengines. Signals from RADVS are processed by the flight con-trol electronics to throttle the three vernier engines,reducing velocity as the altitude decreases. At 14 feet above

the surface, Surveyor is slowed to three miles per hour. Atthis point the engines are shut off and the spacecraft fallsfree to the surface.The landing impact is cushioned by crushable foot padsand shock absorbers on each of the three legs and by crush-able honeycomb aluminum blocks under the frame in case of anexceptionally hard landing.

Post-landing EventsOf prime interest to Surveyor engineers is the telemetryreceived during the descent and touchdown. Touchdown is

followed by periods of engineering telemetry to determine thecondition of the spacecraft.

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If the spacecraft is in operational condition on thesurface, flight control power is turned off to conservebattery power and a series of wide angle 200-lines TV picturesare taken.The solar panel and high gain planar array antenna arealigned with the Sun and Earth. If the high gain antenna issuccessfully operated to lock on Earth, transmission of 600

line television pictures will begin. If it is necessary tooperate through one of the low gain, omnidirectional antennas,additional 200 line pictures will be transmitted.The lifetime of Surveyor on the surface will be determinedby a number of factors such as the power remaining in thebatteries in the even the Sun is not acquired by the solar panel,or spacecraft reaction to the intense heat of the lunar day.

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ATLAS-CENTAUR AND SURVEYOR TEAMSNASA HEADQUARTERS, WASHINGTON, J..C.Dr. Homer E. Newell Associate Administrator for SpaceScience and ApplicationsRobert F. Garbarini Deputy Associate Administrator forSpace Science and Applications

(Engineering)Oran W. Nicks Director, Lunar and Planetary ProgramsBenjamin Milwitzky Surveyor Program ManagerVincent L. Johnson Director, Launch Vehicle and Pro-pulsion ProgramsR. Duff Ginter Centaur Program ManagerJET PROPULSION LABORATORY, PASADENA, CALIF.Dr. William H. Pickering DirectorGen. A. R. Luedecke Deputy DirectorRobert J. Parks Surveyor Project ManagerHoward H. Haglund Deputy Project Manager for Hughes

Aircraft Co. OperationsWalker E. Giberson Deputy Project Manager for Mission

Requirements, Plans and OperationsDr. Leonard Jaffe Project ScientistDr. Eberhardt Rechtin Assistant Laboratory Director for

Tracking and Data AcquisitionDr. Nicholas A. Renzetti Surveyor Tracking and Data Systems

ManagerW. E. Larkin JPL Engineer in Charge, GoldstoneJ. Buckley Pioneer Station Manager, Goldstone

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R. J. Fahnestock JPL DSN Resident in AustraliaR. A. Leslie Tidbinbilla Station ManagerR. C. Terbeck JPL DSN Resident in South Africai. Hogg Johannesburg Station ManagerAvron Bryan Ascension Station ManagerLEWIS RESEARCH CENTER, CLEVELANDDr. Abe Silverstein DirectorBruce T. Lundin Associate Director for DevelopmentEdmund R. Jonash Centaur Project ManagerKENNEDY SPACE CENTER, FLA.

Dr. Kurt R. Debus DirectorRobert H. Gray Director of Unmanned Launch

OperationsJohn D. Gossett Chief, Centaur OperationsHUGHES AIRCRAFT COMPANY, CULVER CITY, CAL.Dr. Robert L. Roderick Surveyor Program Manager, Assistant

Manager -- Lunar ProgramsRobert E. Sears Associate Program ManagerDr. Frank G. Miller Assistant Program ManagerRichard R. Gunter Assistant Program ManagerGENERAL DYNAMICS/CONVAIR, SAN DIEGO, CAL.Grant L. Hansen Vice President, Launch Vehicle

Programs

G. Deane Davis Centaur Program Manager

Dan Sa okon Complex 36 Site Manager

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-33-PRATT AND WHITNEY AIRCRAFT DIVISION OF UNITED AIRCRAFT, CO.,

WEST PALM BEACH, FLA.Richard Anchutze RL-10 Engine Project ManagerHONEYWELL, INC., ST. PETERSBURG, FLA.R. B. Foster Centaur Guidance Program Manager

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-34-MAJOR SUBCONTRACTORS

SurveyorAiResearch Division Ground support equipmentGarrett CorporationTorrance, Cal.Airite Nitrogen tanksEl Segundo, Cal.Airtek Division Propellant tanksFansteel Metallurgical Corp.Compton, Cal.Ampex Tape recorderRedwood City, Cal.Astrodata Time clocksSanta Ana, Cal.Bell & Howell Company Camera LensChicago, Ill.Bendix Corp. Landing dynamics stabilityProducts Aerospace Division studySouth Bend, Ind.Borg-Warner Tape recorderSanta Ana, Cal.Brunson Optical alignment equipmentKansas City, Kan.Carleton Controls Helium regulatorBuffalo, N. Y.Eagle-Picher Company Auxiliary batteriesJoplin, Mo.Electric Storage Battery Main batteriesRaleigh, N.C.Electro-Development Corp. Strain gage electronicsSeattleElecLro-Mechanica]. Rcsearch Decommutator:;Sarasota, Fla.


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Endevco Corporation AccelerometersPasadena, Cal.General Electrodynamics Vidicon tubesGarland, Tex.General Precision, In-. GyrosKearfott DivisionLittle Falls, N.J.General Precision, Inc. Spacecraft TV ground data handlingLink Group systemPalo Alto, Cal.Heliotek Solar modulesSylmar, Cal.Hi-Shear Corp. Separation deviceTorrance, Cal.C. G. iHokanson Mob. temperature control unitSanta Monica, Cal.Holex SquibsHollister, Cal.Honeywell Tape recorder/reproducerLos AngelesKinetics Main power switchSolana Beach, Cal.Lear Siegler TV photo recorderSanta Monica, Cal.Menasco Gas tanksLos AngelesMetcom Magnetron assemblySalem, Mass.Motorola, Inc. Subcarrier oscillatorsMilitary Electronics DivisionScottsdale, Ariz.

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National Water Lift Co. Landing shock absorberKalamazoo, Mich.Northrop/Norair Landing gearHawthorne, Cal.Ryan Aeronautical Co. Radar altitude Doppler velocitySan Diego, Cal. sensorSanborn L. F. oscillographWaltham, Mass.Scientific-Atlanta System test standAtlanta, Ga.Singer-Metrics F. M. calibratorBridgeport, Mass.Thiokol Chemical Corp. Main retro engineElkton DivisionElkton, Md.Thiokol Chemical Corp. Vernier propulsion systemReaction Motors DivisionDenville, N.J.Telemetrics SimulatorSanta Ana, Cal.United Aircraft Corp. Subcarrier oscillatorNorden DivisionSouthampton, Pa.Vector Subcarrier oscillatorSouthampton, Pa.

AtlasRocketdyne Div. of MA-5 propulsion systemNorth American Aviation Inc.Canoga Park, Cal.Thiokol Chemical Corp. LOX and fuel staging valvesReaction Motors Div.Denville, N.J.Hadley Co. Inc. Valves, regulators and discon-

nect coupling

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Fluidgenics Inc. RegulatorsGeneral Precision Inc. Displacement gyrosKearfott Div.San Marcos, Cal.Honeywell Inc. Rate gyrosAeronautical Div.Fifth Dimension Inc. CommutatorsBendix Corp. Telepaks and oscillatorsBendix Pacific Div.Fairchild-Hiller LOX fuel and drain valvesStratos Western Div.Bourns Inc, Transducers and potentiometers

Washington Steel Co. Stainless steelWashington, Pa.Centaur

General Dynamics/Ft. Worth Insulation panels and noseDiv., Ft. Worth, Tex. fairingPesco Products Div. of Boost pumps for RL-10 enginesBorg-Warner Corp.Bedford, OhioBell Aerosystems Co. of Attitude control systemBell Aerospace Corp.Buffalo, N.Y.Liquidometer Aerospace Div. Propellant utilization systemSimmonds Precision Products,Inc.Long Island, N.Y.General Precision Inc. Computer for inertial guidanceAerospace Gp., Kearfott systemDiv., San Marcos, Cal.Goodyear Aerospace D.v. of Handling trailerGoodyear Tire and Ri Lber Co.Akron, Ohio

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Systems and Instruments Div. Destructorsof Bulova Watch Co.Flushing, N.Y.Consolidated Controls Corp. Safe and arm initiatorEl Segundo, "al.Borg-Warner Controls Div. Inverterof Borg-Warner Corp.Santa Ana, Cal.Sippican Corp. Modules for propellant utili-Marion, Mass. zation systemGeneral Electric Co. TurbineLynn, Mass.Vickers Div. of Hydraulic pumpsSperry Rand Corp.Troy, Mich.Edcliff Instruments, Inc. Transducers and switchesMonrovia, Cal.Rosemount Engineering Co. TransducersMinneapolisScientific Data Systems ComputersSanta Monica, Cal.W. 0. Leonard, Inc. Hydrogen and oxygen ventPasadena, Cal. valves

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Surveyor B Press Kit