Surveyor D Press Kit

8/8/2019 Surveyor D Press Kit

1/51

1NAIt '11IA IAl ItlAlilit AIt ) .I'A(l l)DMINISrIRATION ILLS Wr) ,

FOR RELEASE: TUESDAY A.M.W July 11, 1967RELEASE NO: 67-172-A

PROJECT: SURVEYOR D(To be launched no earlier9 P^,July 13, 196?)

CONTENTSGENERAL RELEASE ------------------------------------ l-5SURVEYOR CK- ROUN -------------------- ------------ :::85SURVEYOR D SPACECRAFT- --------------------------- -----9Frame, Mechanisms and Thermal Control--:-------------9-11Power Subsystemr--------------------------------------11-13Telecommunication a---------------------------------- 13-14Propulsion ------------------------------------------- 14-15Flight Control Subsystem----------------------------15-16Television ---------------------------------------- 17Surface Sampler Experiment- ------ -------------- 1819Magnetic Test ---------------------------------------19-20Engineering Instrumentation----------------------------20ATLAS-CENTAUR LAUNCH VEHICLE----------------------------21Launch Vehicle Fact Sheet---------------------------22Atlas-Centaur Flight Sequence-----------------------23TRACKING AND COMMUNICATION------------------------------ 41-25TRAJECTORY ---a---------------------------------------- 26-27W ATLAS-CENTAUR ll/SURVEYOR D FLIGHT PLAN----------------28Launch Periods - a---------------------------------------28Atlas Phase ------------------------------------------ 28-29Centaur Phase----a----------------------------------a-a--- 29First Surveyor Events-----------------------------29-30Canopus Acquisition---------------------------------31Midcourse Maneuver --------a ------------------------- 31-32Terminal Sequence ---------------------------------32-33Post-landing Events ----------------------------- - 34ATLAS-CENTAUR AND SURVEYOR TEAMS--------------------- -35-41

-end-7/5/67


2/51

NATIONAL AENONAUTICS AND SPACE ADMINISTRATION TELS WO 2 4155N EW S WASHINGTON, D.C. 2054 TELS W36925FOR RELEASE: TUESDAY A.M.July 11, 1967

RELEASE NO: 67-172 4NASA PREPARES

TO LAUNCHFOURTH SURVEYOR

The United States ia preparing to launch Surveyor D,another lunar soft-landing spacecraft, the fourth of thesories of seven Surveyors planned for lunar missions.

The launch by the National Aeronautics and Space Adminis-tration Is planned from Complex 36 at Cape Kennedy, Fla.,during the five-day period July 13-l7'. The launch vehicleis an Atlas-Centaur.

Like the three previous Surveyors, Surveyor D's missionwill be to perform a sort-landing in the Apollo area ofinterest on the Moon and take television pictvtres of thelunar surface around Its landing site.

Like Surveyor III, this spacecraft will carry a sur-face sampler to dig into the lunar surface under the eye ofthe television camera.

Although the Surveyor D mission is basically similarto that of Surveyor III, there are some differences.

-more- 7/5/67


3/51

-2-

Most Important is the target landing site rort Surveyor D.It will be aimed to soft-land in Sinus Medli (Central Bay) atalmost the dead center of' the front face of the Moon at 10 2U'West longitude and C!O 25' North latitude.

In generael, the Sinus Medli area is considerably rougherthan the sites of the two previous Surveyor landings butverification of' a site In the center or the Moon's visibleface is required by the Apollo program to provide a varietyof landing site options.

Surveyor D's soft landing will be further complicated bythe fact that it will approach the Moon at a greater angleto the vertical than its predecessors, thus requiring a, largergravity turn during the crucial terminal descent sequence.Surveyor D will approach the Moon at the beginning or itsdescent at an angle of 36 degrees from vertical; Surveyor I'sangle of approach was only six degrees and Surveyor III's was25 degrees.

Other differences from previous Surveyor missions:--Altas-Centaur 11 has a one-burn capability in its uecond

stage. This is the last of the direct ascent Centaurs and issimilar to the Surveyor I Centaur but unlike the two-burn Centaurwhich launched Surveyor III into a parking orbit from whichit was sent to the Moon.

-more-


4/51

-3---Modifioations have been made in this Surveyor's landing

radar electronic logla circuitry to prevent a repeat or III'sthree-bounoo landing that occurred when the three vernierengines were not out off Just prior to the first touchdown.See page 8,

--A small magnet will be Attached to a footpad in viewof the television camera to determine if there is magneticmaterial on the lunar surface. See page 19.

The Surveyor D flight will take about 65 hours from lift-off to lunar landing. A large solid propellant retrorocketand three small vernier rocket engines under radar controlwill slow Surveyor from a lunar approach speed of about 6,o0omiles per hour to about three miles per hour. The engines cutoff at the 14 -foot mark and the spacecraft free falls to thelunar surface, touching down at about 10 miles per hour.

On the first day of the launch period, July 13, the launchcan occur between 7:03 a.m. EDT to 7:07 a.m.

The Surveyor D target site is a 37%mile diameter circlein Sinus Medii about 190 miles north of the large craterPtolemaeus.

At launch, Surveyor D will weigh 2,290 pounds. The retro-motor, which will be Jettisoned after burnout, weighs 1,463pounds.

-more-


5/51

I

f 2

-5 '**

*11

n o - I

II

~J* 11

lain-4 I

-mo rc -


6/51

After expenditure of liquid propellants and attitudecontrol gas, the landed weight of Surveyor on the Moon will beabout 625 pounds.

In addition to data provided by the TV camera and surfacesampler, Surveyor D will also provide data on the radar re-flectivity, mechanical properties, and thermal conditions ofthe lunar surface.

Surveyor I soft-landed on the Moon June 2, 1966, andreturned 11,150 high-quality photographs of the lunar terrain.It survived eight months on the lunar surface during which timeit withstood eight cycles of extreme heat and cold. SurveyorII was launched Sept. 20, 1966, but the mission failed when oneof the three vernier engines failed to ignite during anattempted midcourse maneuver.

Surveyor III soft-landed on the Moon Apr. 19, 1967, re-turned 6,319 photographs and provided 18 hours of operationof the surface sampler.

The Surveyor program is directed by NASA's Office cfSpace Science and Applications. Project management is assignedto NASA's Jet Propulsion Laboratory operated by the CaliforniaInstitute of Technology, Pasadena. Hughes Aircraft Co.,under contract to JPL, designed and built the Surveyor space-craft and the surface sampler.

-moreo


7/51

-5-NASA's Lewis Research Center, Cleveland, is responsible

for the Atlas first stage booster and for the second stageCentaur, both developed by General Dynamics/Convair, San Diego,Calif. Launch operations are directed by Kennedy Space Center,Fla.

Tracking and communication with the Surveyor is theresponsibility of the NASA/JPL Deep Space Network (DSN). TheDSN stations assigned to the Surveyor program arc Pioneer, atGoldstone in California's Mojave Desert; Robledo, Spain;Ascension Island in the SouCh Atlantic; Tidbinbilla nearCanberra, Australia; and Johannesburg, South Africa. DataVrom the stations will be transmitted to the Space PlightOperations Facility In Pasadena, the command center for themission.

(END OP OENERAL RELEASEj BACKGROUND INFORMATION FOLLOWS)


8/51

-6-SURVEYOR BACKGROUND

Surveyor I performed the first fully-controlled softlanding on the Moon on June 1, 1966, after a 63-hour, 36-minute flight rrom Cape Kennedy.Surveyor I landed at a velocity of about 7.5 miles perhour at 2.45 degrees south of the lunar equator and 43.21 do-

groos West Longitude in the southwest portion of OceanusProcellarum (Ocean of Storms).During the six weeks following the perfect, three-point landlig, the spacecraft's survey television camera took11,150 high-resolution pictures of the lunar surface ror trans-mission to &Lrth receiving stations. Resolution in some or thecloseups was one-halt millimeter or about one-firtieth or aninch. These pictures showed details of the lunar surface amillion times riner than the best Earth telescope photos.From the pictures were derived the representative colors

or the Moon's surface, an accurate view of the terrain up toone and one-half miles surrounding the Surveyor, the erfect oflanding a spacecrart upon the lunar surrace and pictorialevidence or lunar environmental damage to the spacecraft itselr.A section of the mirrored glass radiator atop one of the elec-tronic equipment compartments was shown to be cracked in &photograph taken during the second lunar day.The spacecraft also took a number or pictures of thesolar corona (the Sun's upper atmosphere), the planet Jupiterand the first magnitude stars Sirius and Canopus,The television pictures showed that the spacecraft cameto rest on a sooth, nearly level site on the floor or a ghostcrater. The landing site was surrounded by a gently rollingsurface studded with craters and littered with frngmental de-bris, The crestlines of low mountains were visible beyond thehorison.By July 13, Surveyor I's 42nd day on the Moon, the space-craft had survived the intense heat of the lunar day (250 de-grees F), the cold of the two-week-long lunar night (minus 260degrees ) and a second full lunar day, Total picture countwas: first lunar day -- June 1 to June 14 -- 10,338i secondday -- July 7 to July 13 -- 812. The total operating time ofSurveyor I (time during which signals were received from thespacecraft) was 612 hours.

-more-


9/51

Despite a faltering battery not expected to endure therigors of the lunar environment over an extended period, Surveyorcontinued to accept Earth commands and transmit TV picturesthrough the second lunar sunset. It received and acted uponapproximately 120,000 commands during the mission.Communicaticns with Surveyor I were re-established atintervals through January 1967 but no TV pictures were obtainedafter the July 1966 activity. Important Doppler data on themotion of the Moon were acquired during the final months ofSurveyor operations.On Feb. 22, 1967, at 12:24 a.m. EST, Surveyor I was photo-graphed on the surface of the Moon by Lunar Orbiter III.Surveyor II was launched on Sept. 20, 1966, toward SinusMedii in the center of the Moon. An attempt to perform themidcourse maneuver was unsuccessful when one of the three liquidfuel vernier engines failed to fire. The thrust imbalancecaused the spacecraft to begin tumbling. Repeated attemptswere made to command all three engines to fire to regain control

of the spacecraft. When all attempts failed it was decidedto perform a series of engineering experiments to obtain dataon various subsystems concluding with the firing of the mainretrorocket. The spacecraft impacted the Moon southeast of thecrater Copernicus at a velocity of nearly 6,000 miles per hour.Intensive investigation into possible causes of theSurveyor II failure by a team comprised of propulsion expertsfrom the Jet Propulsion Laboratory, Hughes Aircraft Co.,Thiokol Chemical Corp,. and NASA did not result in the identi-fication of the exact cause. As a result of this investi-gation, however, a number of changes in testing procedures were

recommended for Surveyor III and subsequent spacecraft to pro-vide better diagnostic capability in the vernier propulsionsystem during preflight testing as well as during the mission.These changes are designed to minimize the possibjlity of re-currence of the Surveyor II problem.Surveyor III was launched April 17, 1967, and successfullysoft-landed on the Moon April 19, 1967, on the east wall offi650-foot dinmeter crater in the Ocean of Storms. The spacecrafttouched down three times in the landing when its vernierengines did not cut oft at the prescribed 14*oot mark butcontinued firing to the surface. A command from Earth shut down

the enignes after the second touchdown at 2.94 degrees'Southlatitude and 23.34 degrees West longitude. Surveyor III we;equippjd with a surface sampler instrument to provide data onlunar soil characteristics. The device dug four trenches, madesevrn bearing strength tests and 13 penetration tests during atotal of 18 hours of surface sampler operation from the secondday after touchdown through lunar sunset on May 3.-more-


10/51

-8-Operation of the television camera yielded 6,315 pictures.These Included pictures of a solar eclipse as the Earth passedin front of the Sun, the lunar terrain, portions of the space-craft, surface sampler operations and the crescent of the Earth.Attempts to reactivate the spacecraft during the secondlunar day were unsuccessful.On Surveyor III a radar break-lock was commanded by thespacecraft landing radar's Internal logic as the radar beamscrossed a field of highly reflecting rocks as it neared thesur~ace. These looked to the radar much as a field of brokenmirrors would to a searchlight, giving unexpected high returnsback into the radar receivers. This caused the break-lock be-cauee the radar logic circuitry is designed so as to make theradar tracking circuits select the strongest signal if severalare present.This break-lool, feature is an intelligence which hasbeen designed into the radar to enable it to ignore reflectionsfrom antenna side lobes. This is very Important when theradar is first turned on and is searching for the Moon's surfacefrom a tilted spacecraft or if the radar accidently locks ontoa weak side lobe reflection initially.It iD not needed near the lunar surface when the radaris already locked on the proper reflections.The action taken to avoid recurrence of a similar break-lock on Surveyor D and future Surveyors, is to disable thebreak-lock logic when the spacecraft is near enough to bhe Moon'ssurface that highly reflective rocks oould be a problem. Inthis case, the logic will not be used below 1,000 feet.

-more-


11/51

-9-

SURVEYOR D SPACECRAFTSpaceframes, echanisms and Thermal Control

The spaceframe of the Surveyor is a triangular aluminumstructure which provides mounting surfaces and attachmentsfor the landing gear, main retrorooket engine, vernier enginesand associated tanks, thermal compartments# antennas and otherelectronic and mechanical assemblies.

The rrame is constructed of thin-wall aluminum tubing,with the frame members interconnected to form the triangle.A mast, which supports the planar array high-gain antennaand single solar panel, is attached to the top of the spaoefroe.The basic frame weighs less than 60 pounds and installationhardware weighs 23 pounds.The Surveyor stands about 10 feet high and, with Itstripod landing gear extended, can be placed within a 14-foot

circle. A landing loeg is hinged to each of the three lowercorners of the frame and an aluminum honeycomb footpad Isattached to the outer end of each leg. An airplane-type shookabsorber and telescoping look strut are connected to the frameso that the logs can be folded into the nose shroud duringlaunch.Blocks of crushable aluminus honeycomb are attached tothe bottom of the spaceframe at each of its three corners toabsorb part of the landing shock. Touchdown shook also Isabsorbed by the footpads and by the hydraulic shook absorberswhich compress with the landing load.Two onidirectional, conical antennas are mounted on theends of folding booms which aro hinged to the spacetraome. Thebooms remain folded against the frame during launch untilreleased by squib-actuated pin pullers and deployed by torsionsprings. The antenna booms are released only after tho landinglegs are extended and locked In position.Aft antenna/solar panel positioner atop the mast supportsand rotates the planar array antenna and solar panel in eitherdirection along four axoe. This freedom of movement allows theantenna to be oriented toward Earth and the solar panel toward

the Sun.

-more-


12/51

-98 -

SURVEYORSOLAR PANEL

OMNIDIRECTIONALANTENNA A

HIGH-GAIN ANTENNATHERMALLY CONTROLLEDCOMPARTMENT BTHERMALLY CONTROLLEDCOMPARTMENT A TV CAMERA

STAR CANOPUS+\- -Zi- .vzSENSORRADAR ALTITUDE-DOPPLER VELOCITY ONIECTI

FOOTPAD 3

FOOTPAD 2 - VERNIER ENGINE 3CRUSHABLE VERNIER PROPELLANTBSLOCK ePRESSURIZING SAS

LS;AMPLER TANK (HELIUM)AUXiLIARY BATTERYRETRO ROCKET NOZZLE

-mn. , .X-|


13/51

-10-

Two thermal compartments house sensitive electronicapparatus for which active thermal control is needed through-out the mission. The equipment in each compartment is mountedon a thermal tray that distributes heat throughout the com-partment. An insulating blanket, consisting of 75 sheets ofaluminized Mylar, is sandwiched between each compartment'sinner shell and the outer protective cover. The tops of thecompartments are covered by mirrored glass thermal radiatorsto dissipate heat.Compartment A, which maintains an internal temperaturebetween 40 degrees and 125 degrees F., contains two radio re-celvers, two transmitters, the main battery, battery chargeregulator, main power switch and some auxiliary equipment.Compartment B. kept between zero and 125 degrees F.,houses the central command decoder, boost regulator, centralsignal processor, signal processing auxiliary, engineeringsignal processor, and low data rate auxiliary.Both compartments contain sensors for reporting tempera-ture measurements by telemetry to Earth, and heater assembliesto maintain the thermal trays above their allowable minimums.the compartments are kept below the 125-degree maximum withthermal swithces which provide a conductive path to the radiating

surfaces for automatic dissipation of electrically generatedheat. Compartment A contains nine thermal switches and com-partment B, six. The thermal shell weight of compartment A is25 pounds, and compartment B, 18 pounds.Passive temperature control is provided for all equipment,not protected by the compartments, through the use of paintpatterns and polished surfaces.Twenty-nine pyrotechnic devices mechanically release orlock the mechanisms, switches and valves associated with theantennas, landing leg locks, roll actuator, retrorocket separa-tion attachments, helium and nitrogen tanks, shook absorbers

and the retromotor detonator. Some are actuated by command fromthe Centaur, and others are actuated by ground command.A solid propellant, spherical retrorocket fits within thecenter cavity of the triangular frame and supplies the mainthrust fo r slowing the spacecraft on approach to the Moon.The unit is attached at three points on the spacetrame near thelanding leg hinges, with explosive nut separation points forejection after burnout. The motor case, made of high-strengthsteel and insulated with asbestos and rubber, is 36 inches indiameter. Including the molybdenum nozzle, the unfueled motorweighs 144 pounds. With propellants the weight Is about 1,444pounds, or more than 60 per cent of the total spacecraft weight.

-more-


14/51

-11 -Electrical harnesses and cables interconnect the space-craft subsystems to provide correct signal and power flow.The harness connecting the two thermal compartments is routedthrough a thermal tunnel to minimize heat lose from the com-partments. Coaxial cable assemblies, attached to the space-frame by brackets and clips, are used for high frequencytransmission.Electrical interface with the Centaur stage is establishedthrough a 51-pin connector mounted on the bottom of the space-frame between two of the landing legs. The connector mateswith the Centaur connector when the Surveyor Is mounted tothe launch vehicle. It carries pro-separation commands fromthe Centaur programmer and can handle emergency commands fromthe blockhouse console. Ground power and prelaunch monitoralso pass through the connector.

Power Subsystem

The power subsystem collects and stores solar energy,converts it to usable electric voltage, and distributes it tothe other spacecraft subsystems. The subsystem consists of thesolar panel, a main battery and an auxiliary battery, an auxi-liary battery control, a battery ci;- 'ge regulator, main powerswitch, boost regulator, and an eng.ieering mechanisms auxiliary.The bolar panel is the spacecr--.'s primary power sourceduring flight and during operations in the lunar day. It consistsof 3,960 solar cells arranged on a thin, flat surface approxi-mately nine square feet in area. The solar cells are groupedin 792 separate modules and connected in series-parallel toguard against complete failure in the event of a single cellmalfunction.The solar panel is mounted at the top of the Surveyorspacecraft's mast. Wing-like, it is folded away during launchand deployed by Earth-command after the spacecraft has been in-jected into the lunar transit trajectory.When properly oriented duringflight, the solar panelcan supply about 89 watts, most of the power required for theaverage operating load of all on-board equipment.During operation on the lunar surface, the solar panel can

be adjusted by Earth-command to track the Sun within a fewdegrees, so that the solar cells remain always perpeauicularto the solar radiation.

-more-


15/51

-12-

In this lunar-surface mode, the solar panel is designedto supply a minimum of 77 watts power at a temperature of 140degrees F., and a ninimum of 57 watts at a temperature of 239degrees F.A 14-cell rechargeable, silver-zinc main battery is thespacecraft's power reservoir. It is the sole source of power

during launch; it stores electrical energy from the solar panelduring transit and lunar-day operations; and it provides abackup source to meet peak power requirements during both ofthose periods.Fully charged, the battery provides 3,800 watt-hoursat a discharge rate of 1.0 amperes. Battery output is approxi-mately 22 volts direct current for all operating and environ-mental conditions in temperatures from 40 degrees to 125 degreesF.The auxiliary battery is a non-rechargeable, silver-zinc

battery 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.The battery has a capacity of from 800 to 1,000 watt-hours,depending upon 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 regulator couples the sclar panel tothe main battery for maximum conversion and transmission ofthe solar energy necessary to keep the main battery at fullcharge.It receives power at the solar panel's varying outputvoltage, and it delivers this power to the main battery at aconstant battery terminal voltage.The battery charge regulator indludes sensing and logiccircuitry for automatic battery charging whenever battery voltagedrops below27 volts direct current. Automatic battery chargingalso maintainsbattery manifold pressure at approximately 65pounds per square inch.Earth-command may override the automatic charging func-tion of the battery charge regulator.

-more-


16/51

-13-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 to the spacecraft's three main power transmissionlines, These three lines supply all the spacecraft's powerneeds, except for a 22-volt unregulated line which servesheaters, switches, actuators, solenoids and electronic circuits

which do not require regulated power or provide their ownregulation.

TelecommunicationsCommunications equipment aboard Surveyor has three func-tions: to provide for transmission and reception of radio sig-nals; to decode commands sent to the spacecraft; and to selectand convert engineering and television data into a form suit-able for transmission.The first group includes the three antennas: one high-gain, directional antenna and two low-gain, omnidirectionalantennas, two transmitters and two receivers with transponderinterconnections. Dual transmitters and receivers are usedfor reliability.The high-gain antenna transmits 600-line television data.The low-gain antennas are designed for command reception andtransmission of other data including 200-line television datafrom the spacecraft. The low-gain antennas are each connectedto one receiver. The transmitters can be switched to eitherlow-gain antennas or to the high-gain antenna and can operateat low or high-power levels. Thermal control of the threeantennas is passive, dependent on surface coatings to keeptemperatures within acceptable limits.The command decoding group can handle up to 256 commandseither direct, (on-orf) or quantitative (time-intorvals). Eachincoming command is checked in a central command decoder whichwill reject a command, and signal the rejection to Earth, ifthe structure of the command is incorrect, Acceptance of acommand is also radioed to Earth. The command is then sent tosubsystem decoders that translate the binary information intoan actuating signal for the function command such as squibfiring or changing data modes.

-more-

{4j


17/51

Processing or most engineering data, (temperatures,voltages, currents, pressures, switch positions, etc.) ishandled by the engineering signal processor or the auxiliaryprocessor. There are over 200 engineering measurements ofthe spacecraft. None are continuously reported. There arefour commutators in the engineering signal processor to permitsequential sampling of selected signals. The use of a commutatoris dependent on the type and amount of information requiredduring various flight sequences. Each commutator can be com-manded into operation at any time and at any of the five bitrates: 17.2, 137.5, 550, 1100 and 4,400 bits per second.

Commutated signals from the engineering processors areconverted to 10-bit data words by an analog-to-digital conver-ter in the central signal processor and relayed to the transmitter.The low bit rates are normally used for transmissions over thelow gain antennas and the low power levels of the transmitters.

PropulsionThe propulsion system consists of three liquid fuelvernier rocket engines and a solid fuel retromotor.The vernier engines are supplied propellant by threefuel tanks and three oxidizer tanks. There is one pair oftanks, fuel and oxidizer, for each engine. The fuel and oxidi-zer in each tank is contained in a bladder. Helium storedunder pressure is used to deflate the bladders and force thefuel and oxidizer into the feed lines. Tank capacity is 170.3

pounds each.The oxidizer is nitrogen tetroxide with 10 percent nitricoxide. The fuel is monomethylhydrazine monohydrate. An igni-tion dystem is not required for the verniers as the fuel andoxidizer are hypergolic, burning upon contact. The throttlerange is 30 to 104 pounds of thrust.The main retro is used at the beginning of the terminaldescent to the lunar surface and slows the spacecraft from anapproach velocity of about 6,000 miles per hour to approximately250 miles per hour. It burns an aluminum, ammornium-percholorate

and polyhydrocarbon, case bonded composite type propellant witha conventional grain geometry.The nozzle has a graphite throat and a laminated plastic exitconed The case is f high strength steel insulated with asbestosand silicon dioxide-fllled buna-N rubber to maintain the caseat a low temperature level during firing.


18/51

-15-

Engine thrust varies from 8,ooo to 10,000 pounds overa temperature range of 50 to 70 degrees F. Passive thermalcontrol, insulating blankets and surface coatings will main-taln the grain above 50 degrees F. It is fired by a pyrogenigniter. The main retro weighs approximately 1,444 pounds andis spherical shaped, 36 inches in diameter.

Flight Control SubsystemFlight control of Surveyor, control of its attitudeand 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, and threepairs of cold gas jets. Flight control electronics includes adigital programmer, gating and switching, logic and signaldata converter for the radar altimeter and Doppler velocity

sensor.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 liquidfuel vernier engines and the solid fuel main retro motor.The Sun sensors provide information to the flight controlelectronics indicating whether or not they are illuminated bythe Sun. This information is used to order the gas Jets tofire and maneuver the spacecraft until the Sun sensors areon a direct line with the Sun. The primary Sun sensor consists

of five cadmium sulphide photo conductive cells. During flightSurveyor will continuously drift off of Sun lock in a cycle lessthan 0.2 0.3 degrees. The drift is continuously corrected bysignals from the primary sensor to the flight electronics order-ing the pitch and yaw gas Jets to fire to correct the drift.Locking on to the sbar Canopus requires prior Sun look-on.Gas Jets fire intermittently to compensate for drift to main-tain Canopus look-on and thus control spacecraft roll duringcruise modes. If star or Sun look is lost, control is automati-cally switched from optical sensors to inertial sensors (gyros).The inertial reference unit is also used during missionevents when the optical sensors cannot be used. These eventsare the midcourse maneuver and descent to the lunar surface.This device senses changes in attitude and in velocity of thespacecraft with three gyros and an accelerometer. Informationfrom the gyros is processed by the control electronics to order

-more-


19/51

gas jet firing to change or maintain the desired attitude.During the thrust phases the inertial reference unit controlsvernier engine thrust levels, by differential throttling Jorpitch and yaw control and swiveling one vernier engine for rollcontrol. The accelerometer controls the total thrust level.The altitude marking radar will provide the signal forfiring of the main retro. It Is located in the nozzle of theretromotor and Is ejected when the motor ignites. The radarwill generate a signal at about 60 miles above the lunar surface.The signal starts the programmer automatic sequence after a pre-determined period (direoted by ground command); the programmerthen commands vernier and retro ignition and turns on the RadarAltimeter and Doppler Velocity Sensor (RADVS).The inertia burnout switch will close when the thrustlevel of the main retromotor drops below 3.5 gs generating asignal which is used by the programmer to command jettisoningof the retromotor and switching to RADWS control.Control of the spacecraft after main retro burnout isvested in the radar altimeter and Doppler velocity sensor.There are two radar dishes for this sensor. An altimeter/velo-city sensing antenna radiates two beams and a velocity sensingantenna two beams. Beams 1, 2, and 3 give vertical and trans-verse velocity. Beam 4 provides altitude or slant range infor-mation. Beams l, 2, and 3 provide velocity data by summing inthe signal data oonverter of the Doppler shift (frequency shiftdue to velocity) of each beam. The converted range and velocitydata is fed to the gyros and circuitry logic which in turn con-trol the thrust signals to the vernier engines.The flight control electronics provide for processingsensor information into telemetry signals and to actuate space-craft mechanisms. It consists of control cirouits, a commanddecoder and an AC/DC electronic conversion unit. The programmercontrols timing of main retro phase and generates precisiontime delays for attitude maneuvers and midcourse velocity cor-rection.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 nitro-gen gas under high pressure. The system includes regulatingand dumping valves and three pairs of opposed gas jets withsolenoid-operated valves for each jet. One pair Of Jets is loca-

ted at the end of each of the three landing legs. The pair onleg number one control motion in a horizontal plane, impartingroll motion to the spacecraft. Pairs two and three controlpitch and yaw.

-more-


20/51

-17-Television

The Surveyor spacecraft carries one survey televisioncamera. The camera is mounted nearly vertically, pointed ata movable mirror. The mounting containing the mirror can swivel360 degrees, and the mirror can tilt down to view a landing legto up above the horizon.The camera can be focused, by Earth command, from fourfeet to infinity.. Its iris setting, which controls the amountof light entering the camera, can adjust automatically to thelight level or can be commanded from Earth. The camera has avariable focal length lons which can be adjusted to narrow angle,6.4 x 6.4 field of view, to wide angle, 25.4 x 25.4 field ofview.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 too

intense. A too-high light level could occur from changes on thearea of coverage by the camera, a change in the angle of mirror,in the lens aperture, or by changes in Sun angle. The samesensor controls the automatic iris setting. The sensing devicecan be overridden by ground command.The camera system can provide 200 or 600-line uictures.The 600-line pictures require that the high gain directionalantenna and the high power level of the transmitter are bothoperating. The 600-line mode provides a picture each 3.6. sec-onds and Vhe 200 line mode every 61.8 seconds.A filter wheel can be commanded to one of four positionsproviding clear, colored or polarizing filters.Two flat beryllium mirrors are mounted on the spacecraftframe near leg number one to provide additional coverage ofthe area under the spacecraft for the television camera. Thelarger mirror is 10 inches x 9 inches; the smaller is 3* inchesx 9* inches.The large mirror provides a view of the lower portion ofcrushable block number three and the area under vernier enginenumber three. The small mirror provides avie. f the areaunder vernier engine number two.The purpose is to provide pictures of the lunar soildisturbed by the spacecraft landing and the amount of damageto the crushable block itself.Principal television investigator is Dr. Eugene Shoemaker,U. S. Geological Survey.

-more-


21/51

-17a -SURVEYOR SURVEY TV CAMERA

HOOD -MIRROR

,,l - a MIRRORMIRROR AZIMUTH k L ELEVATIONDRIVE MOTOR DRIVE ASSEMBLY

VARIABLE SFILTER WHEELFOCAL LENGTH ASSEMBLYLENS ASSUVMBLYFOCUSPOTENTIOMETERIRISPOTENTIOMETER

VIDICON TUBESHUTTER -ASSEMBLY- VIDICONRADIATOR

ELECTRONICCONVERSIONUNIT

ELECTRICALWi,/ ONNECTOR

- mno r -


22/51

Surface Sampler Experiment

Paylc-d of the Surveyor D spacecraft includes a surfacesampler mechanism flown for the first time on the Surveyor IIImission. The metal claw digger provided scientific data fordetermination of the bearing strength of the lunar surface andsoil characteristics. The device can dig a trench to a depthof 18 inches, perform penetration tests by dropping it fromvarious heights, and bearing strength tests by pressing down onthe lunar surface.

The device is a scoop about five inches long and two incheswide attached to an extendable arm hinged horizontally andvertically to the spacecraft. The flexible arms to which thescoop is rigidly attached, is made up of tubular aluminum crossmembers which operate mechanically in a scissor fashion to extended,retracted, or partially retracted position by a metal tape, oneend attached to the scoop and the other wound on a motor spindleat the base. Extension and retraction of thu arm is controlledby commands to the motor to reel or unreel the tape. Maximumextension is about five feet from the spacecraft frame.

Two other motors, which can be operated in either direction,will allow the ai.U t. pivot 112 degrees in a horivontal arc andto elevate or lower the scoop over a range of some 40 inchesabove to about 18 inches below a level lunar surface. Surfacearea available to the sampler totals about 24 square feet.A fourth motor, located in the scoop, opens and closesa two-by-four-inch door on the scoop. All four motors operateon 22 volts of unregulated direct current from the spacecraftbattery. They operate for either of two time periods, a singlecommand pulsing the motor for one-tenth of a second or for twoseconds. Selection of the motor to be operated, motor directionand the time period is made by ground command.The instrument will be used in conjunction with the surveyTV camera. The scoop will be positioned in view of the camera,then activated to perform picking, digging or trenching opera-tions. Visual data combined with a determination of the forcedeveloped during the digging is expected to indicate strength,texture and cohesive characteristics cf the soil.

-more-


23/51

z~

I

I

U

.


24/51

-19-

A single telemetry channel from the Surveyor will monitorthe electric current being drawn by the motor in operation.By using pre-flight calibration data, this measurement can beused in analyzing the force necessary to scrape or dig thesurface and break small rocks or clods.In the event of a camera failure, where the surfacesampler must be used in the blind, the force measurements willbe of some, but less value, in analyzing the operation of theinstrument. For maximum success of the experiment, the surfacesampler is dependent upon visual data from the TV camera.The scoop, arm, motors, and housing for the device totalabout 8.4 pounds. The instrument's electronics unit, locatedin a separate thermal-control compartment, weighs about 6.3pounds.Principal scientific investigator for the surface samplerexperiment is Dr. Ronald F. Scott of the California Instituteof Technology. The instrument was designed and built by theHughes Aircraft Company.

Magnetic TestThe purpose of this test, utilizing a small magnet attachedto a footpad, is to determine whether magnetic particles arepresent in the surface layer of lunar soil.The magnet is a bar, two inches long by j inch wide by1/8 inch thick, mounted vertically on footpad #2 in view ofthe television camera. Photographs of the bar taken at variousSun angles would show magnetic particles attracted to the magnetit there are any on the lunar surface.

-more-


25/51

PARALLEL TOLEG CENTER LINE

at a

NON-MAGNETIC BARBRACKET MAGNETIC BAR

2 x1/2x1/8 IN .


26/51

1-20-

A second bar --nonmagnetic-- is also mounted on the foot-pad to serve as a control tor the test by permitting a comparisonof the amount of material adhering to the nonmagnetic bar, if any,with the amount adhering to the magnetic bar.

The magnet is made of an iron-nickel-cobalt-aluminumalloy. The control bar is an alloy of iron-nickel-cobalt whichhas a very low magnetic permeability. The two bare are screwedto a mounting bracket which is attached to the footpad. Weightof the entire assembly is about two ounces. The bars andmounting are painted dull light blue for contrast to dark lunarmaterial.

Engineering InstrumentationEngineering evaluation of the Surveyor flight will beaugmented by an engineering payload including an auxiliarybattery, auxiliary processor for engineering information, and

instrumentation consisting of extra temperature sensors, straingauges for gross measurements of vernier engine response toflight control commands and shock absorber loading at touch-down, and extra accelerometers for measurements of vernier engineresponse to flight control commands and shock absorber loadingat 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 determining the performanceof the spacecraft. It processes the information in the samemanner as the engineering signal processor, providing additionalsignal capacity and redundancy.

-more-


27/51

-21-ATLAS-CENTAUR LAUNCIH VEHICLE

Atlas-Centaur 11 will be the fourth in a series ofoperational launch vehicles designed to launch and injectSurveyor spacecraft on lunar mission trajectories. Twoprevious Surveyors (I and II) were launched via direct-ascent trajectories and one (III) using the parking orbitmethod.The Atlas-Centaur vehicle has been developed by NASA tolaunch medium-weight scientific spacecraft on lunar and inter-planetary missions. The vehicle has a current payload capa-bility of about 2,350 pounds for direct-ascent missions to theMoon.An improved Atlas, called SLV-3C. will increase Atlas-Centaur's payload capability to about 2,700 pounds fordirect-ascent lunar missions. The SLV-3C Centaur vehicle, willbe used initially later this year to boost the Surveyor Espacecraft to the Moon.In addition to its Surveyor launch assignment, the Atlas-Centaur combination has been selected to launch two Marinerspacecraft on missions to Mars in 1969 three Orbiting Astro-nomical Observatories beginning in 1966, and two ApplicationsTechnology Satellites also starting in 1968.

'-more- w

.wi.Ji


28/51

Launch Vehicle Fact Sheet(All figures approximate)

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

Atlas Booster Centaur StageWeight (a t 1.U.Cqff) 263,000 lbs. p7,600 lbs.

less payload)Height 75 feet (including 48 feet (withinterstage adapter) fairing)Thrust 388,ooo lbs. (sea 30,0QU lbs. (atlevel) altitude)Propellants RP-1 (fuel) and Liquid hydrogenliquid oxygen (fuel) and liquid(oxidizer) oxygen (oxidizer)Propulsion MA-5 system (2- Two RL-10 engines165,000 lb. thrustbooster engines, 1-57,000lb. sustainer engine, and2-670 lb. vernier engines)Velocity 5,560 mph at BECO 23,700 mph at

7,800 mph at SECO injectionGuidance Pre-programmed auto- Inertialpilot thrpugh BEC0

-more-


29/51

Atlas-Centaur Flight Sequence

MMEvOMINAL ALTITUE SURFACE RANGE VTEIPHTDIE, SEC. SMibE I. STATUTE MI.1. Liftoff o 0 0 02. Booster engine cutoff 144 37 51 5,5603. Booster engine Jettison 147 39 55 5.7304. Jettison insulation paels 178 57 101 6,3005. Jettison nose fairing 205 73 147 6,9306. Sustainer engine cutoff 239 90 213 7T,8007. Atlas-Centaur sePation 2 41 91 216 7,800 ,8. Centaur engine start 250 96 236 7,8009. Centaur engi" cutorf 685 112 1,750 23,70010. Spacecraft separation 756 107 2,200 23,70011. Centaur reorientation 761 106 2,240 23,70012. Centaur retrothrust 996 232 3,7463 23,700

(Launch vehIcle mson completed at T plus 21 minutes)FIgures used are appro te but typical of potentialtrajectories fo r AC-li depending on day or launch.

M-- - -


30/51

-24-TRACKING AND COMMUNICATION

The flight of the Survevor spacecraft from injection tothe end of the mission will be monitored and controlled bythe Deep Space Network (DSN) and the Space Flight OperationsFacility (SPOF) operated by the Jet Propulsion Laboratory.Some 300 persons will be involved in Surveyor flightmonitoring and control during peak times in the mission. Onthe Surveyor I flight more than 100,000 ground commands werereceived and acted on by the spacecraft during flight andafter the soft landing.The Deep Space Network consists of six permanent spacecommunications stations in Australia, Spain, South Africa andCalifornia; a spacecraft monitoring station at Cape Kennedy;and a spacecraft guidance and a command station at AscensionIsland in the South Atlantic.The DSN facilities assigned to the Surveyor project arePioneer at Goldstone, Calif.; Robledo, Spain; Tidbinbilla inthe Canberra complex, Australia; Ascension Island; andJohannesburg, South Africa.The Goldstone facility is operated by JPL with theassistance of the Bendix Field Engineering Corp. TheTidbinbilla facility is operated by the Australia Departmentof Supply. The Robledo facility is operated by JPL under anagreement with the Spanish government and the support ofInstituto Nacional de Tecnica Aeroespacial (INTA) and theBendix Field Corp. The Ascension Island DSN facility isoperated by JPL with Bendix support under a cooperative agree-ment between the United Kingdom and the U.S.The DSN uses a ground communications system fo r operationalcontrol and data transmission between these stations. Theground communications system is a part of a larger net (NASCOM)which links all of the NASA stations around the world. Thisnet is under the technical direction of NASA's Goddard SpaceFlight Center, Greenbelt, Md.The DSN supports the Surveyor flight in tracking thespacecraft, receiving telemetry from the spacecraft, and sendingit commands. The DSN renders this support to all of NASA'sunmanned lunar and planetary spacecraft from the time they areinjected into planetary orbit until they complete their

missions.Stations of the DSN receive the spacecraft radio signals,amplify them, process them to separate the data from thecarrier wave and transmit required portions of the data to

-more-


31/51

-25-

the command center via high-speed data lines, radio links, andteletype. The stations are also linked with the center by voicelines. All incoming data are recorded on magnetic tape.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 to the

engineers on the project. All incoming data are again recordedin the computer memory system and are available on demand.Equipment for monitoring television reception fromSurveyor is located in the SFOF,Some of the equipment is designed to provide quick-lookinformation 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 eitherhorizontally or vertically. Television monitors display thepicture being received. The pictures are received line byline and each line is held on a long persistence televisiontube until the picture is complete. A special camera systemproduces prints 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 inadvance on punched paper tape and forwarded to the stationsof the DSN. They will be transmitted to the spacecraft fromthe DSN station on orders from the SFOF.Three technical teams support the Surveyor televisionmission in the SFOF: one is responsible for determining thetrajectory of the spacecraft including determination of launchperiods and launch requirements, generation of commands forthe midcourse and terminal maneuvers; the second is responsiblefor continuous evaluation of the condition of the spacecraftfrom engineering data radioed to Earth; the third is responsiblefor evaluation of data regarding the spacecraft and forgenerating commands controlling the spacecraft operations.

-more-


32/51

-26-

T]{AJ:;C8.O YThu dtermnnatilo:, of po-irblu launch das , speci.flc timesdur.!nri each day and 1he iEarth-Moon truajectorles fo r the Sur-ve.;or spacecralt arc bascd cii a Fiumier ol factors, orconstraints.A primary constraint is the time span during each day theSurveyor can be launched -- the launch window -- which i.s de-termined ty the requirement that the launch site at. launch timeand the Moon at arrival time be contained in the Earth-Moontransfer orbit plane. Wit;h the launch site moving eastward asthe Earth revolves, acceptable conditions occur only once eachday for a given plane.

The launch azimuth constraint of 78 to 115 degrees is im-posed by the range safety consideration of allowing the initiallaunch phase only over the ocean, not over land masses.The time of flight, or the time to landing, about 61-65hours, is determined by the constraint placed upon the trajec-tory engineer that Surveyor must reach the Moon during the view-ing period of the prime Deep Space Net station at Goldstone inthe California Mojave Desert.Landing sites are further limited by the curvature of theMoon. The trajectory engineer cannot pick a site, even if itfalls within the acceptable band, if the curvature of the Moonwill 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 areas se-lected for the Apollo manned lunar mission.Thus the trajectory engineer must tie together the launchcharacteristics, the landing site location, the declination ofthe Moon and flight time, in determining when to launch, Inwhich direction, and at what velocity.His chosen trajectory also must not violate constraints onthe time allowable that the Surveyor can remain in the Earth'sshadow. Too long a period can result in malfunction of com-ponents or subsystems. In addition, the Surveyor must not re-main in the shadow of the Moon beyond given limits.

-more-


33/51

SURVEYOR TRAJECTORIES TO THE MOON

PARKWO ORSIT TRAJECTORYON DIOECT ASCENT LAUNCH WITH 2 FIRINGS Of SECOND STAGE ENGINES,END Of SECOND STAGE EKGINES' AN D COAST PHASE SETWEEN. SURVEYOR CA NSiNGLE fRNG ALWAYS ENDS REACH ANY MOON POSITION ABOVE OR ELOWNEAR CAPE ABOVE EQUATOR EARTHS EOUATORDIRECT ASCENT TRAJECTORY'WITH SINGtE fIRING OP SECOND STAGE ENGINESSURVEYOR CA N REACH MOON ONLY WHEN MOONIS BELOW EARTH'S EOUATXl

COAST PHSE -/\D II

ON4 PRKING OlUT LAU"NCH -END OF SECOND flUING Of-- - - /SECOD STAGE ENGINES CAN-- - ----- /OCCUR ELOW EOUATOR BY - ----EINCRAIG COAST TWAFBEWE FINGS ----

DOTTED LINES SHOW MAXIMUM AMO0UNT DIPECT ASCENT ---TRJECTOEY CAN BE ADJUTD TO REACH T - -E--ENTMOON POSITONS

'EARLY SUfVEYORS WILL BE LUNCHED ON DIRECTASCEFST TRAJECTORIES


34/51

II-27-

The velocity cf the spacecraft when it arrives at the Moonmurt also fall within defined 11imits. These limits are definedby the retrorocket capability. The velocity relative to theMoon is primarily correlated with the flight time and the Earth-Moon distance for each launch day.So, a further requirement on the trajectory engineer is theamount 6f fuel available to slow the Surveyor from its lunar ap-proach speeo of 6,000 mph to nearly zero velocity,13 Zlet abovethe Moon's surface. The chosen trajectory must not yield velo-citiea that are beyond the designed capabilities of the space-craft 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 ad to a lesserdegree the Sun, Mercury, Venus, Mars, arid Jupiter.It is not expected that the launching can be performed withsufficient acturacy to Impact the Moon in exactly the desiredarea. The uncertainties Involved in a launch usually yield a

trajectory or an Injection valociVy that vary slightly from thedesired values. The uncertainties are due to inherent limita-tions in the guidance system of the launch vehicle. To compen-sate, luutr arne deep space spacecraft have the capability of per-forming a mldcourse maneuver or trajectory correction. To alterthe tra1ectory of a spacecraft it is necessary to apply thrust,or energy, in a specific direction to change its velocity. Thetrajectory of a lody at a point in space being basically deter-mined by its velocity.For example, a simple midcourse mij~ht involve correcting atoo high injection velocity. To correct for this the spacecraft

would be commanded to turn in space until its midcourse engineswere pointing in its direction of travel. Thrust from the en-ginres would slow the craf't. However. in the general case themidcourse is far acre cmplex and wllh involve changes both invelocity and its 'iirection of travel.A certain iwnunt of thrust applied in a specific directioncan achleve both changea. Surveyor will use its three 'liquidfuel vernier andines to alter its flight path in the midcoursemaneuver. It will be commanded to roll and then to pitch or yawin order t9 point the three engine&m in the required direction.The engines then burn long enough to apply the change in velocity

requil'ed to alter the trajectoryeThe change in the trajectory In very slight at this pointand a tracking period of about 2') hours is required to determine

Wie now trajectory. This determination will also provides the datarequired to predict the spacecraft's angle of approach to theMoon, time of arrival, and its velocity as it approaches the Moon.___rc


35/51

-28-FGH

Surveyor D will be launched by Atlas-Centaur 11 into adirect-ascent lunar trajectory.The primary taak for Atlas-Centaur 11 on the Surveyor Dflight is to inject the Surveyor spacecraft on a lunar-transfertrajectory with sufficient accuracy so that the midcoursemaneuver correction required some 15 to 2 0 hours Gfter liftoffdoes not exceed 50 iweters/oecond or 111.85 m.les-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,

Launch Periods

Arrival TimeLaunch Window (Based on earliestDate Open -Flose -Date launch time)13 7:03 a.m. 7:07 a.m. 16 12:18 a.m.14 7:53 a.m. 8:30 a.m. 16 lC:21 p,m,15 8:43 a.m. 10:01 a.m. 17 10:25 p.m,16 9:43 a.m. 11:05 a.m. 18 11:42 p.m.17 10:44 a.m. 12:08 p,m. 20 12:46 a.m.

Atlas PhaseAll flive of the Atlas enginee -- three main engines andtwo vernier control engines -- are ignited prior to 1Jftoff.For the first two seconds the Atlas-Centavr will rise verticallyand then roll for 13 seconds to the desired flight plane azimuthof 80 to 115 degrees depciding upon time of launch.After 15 seconds of flight, the vehicle begins pitchingover to the desired flight trajectory which continues throughoutthe Atlas-powered phase of the flight.At T plus 144 seconds, booster engine cutoff (BECO) occurswhen an acceleration level of 5.7 g is sensed. Three secondslater the booster engine package Is jettisoned. The sustainerengine continues to propel the vehicle and Centaur inertialguidance begins its steering functions.

-more-


36/51

SURVEYOR FLIGAT PROFIE

STPAAIN ATLAUNCH R"-

CANOPUS ACQUISITIOMASOUT LAUNiC PLUS 6 HSC)MFITUS CMASE ATTITUE PZEfRETO MANEUVWSTADIlIZAnON 30 MNK BEFCOE LA'ING

0

PLUS I HE OECINAFE 0O 63 MRSCAMOPLIS SLW; AND CAMOKS RACause inNBRAMTTLY AFTf SIDCotw5AUDCOMS0 CORRCINWO~cr~ABOUT ULolC PUZ' Is HtS es

I24MRS

AT00PAT LAUNC~H


37/51

-29-

Atlas sustainer engine cutoff (SECO) occurs after 239seconds of flight at an altitude of about 90 miles. Twoseconds later Atlas and Centaur are separated by a flexibleshaped charge which severs the interstage adapter. Eightretrorockets on the Atlas are l'ired to increase the rate ofseparation.

Centaur PhaseAt T plus 250 seconds, Centaur's two hydrogen-oxygenRL-10 engines are ignited for a planned burn o1 435 seconds.Centaur ignition occurs at about 96 miles altitude when thevehicle is 236 miles down range traveling at a velocity of7,800 MPH.After 685 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 ol ' launch, but Is approximaitely 23,'700 mph.Shortly after Centaur engine Thutdown, the Centaur pro-grammer commando Ourveyor's, legs and two omnidirectional antennasto extend, and orders the spacecral't's transmitter to high power.At T plus 756 seconds and an altitude of' 107 miles, the pro-grammer commando separation of ' Surveyor from Centaur. Threespring-loaded cylinders force the spacecrai't and vehicle apart.Five seconds after spacecraft separation, Centaur isrotated 180 degrees by Its attitude control syst;em in orderto perform a retromaneuver. Unused propellanto are then blownthrough the rocket thrust chambers to increase separation of'

Centaur and Surveyor -- the rersult is that some f'ive hourslater they are at least 208 miles apart. This eliminates thepossibility that Surveyor's star tracker will mistakerly lockon Centaur. Centaur's trajectory is thereby altered toprevent it 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 Eart., orbit, extending more than 257,000miles into space and circling the Earth once each 11.3 days.

First Surveyor EventsShortly after Centaur engine shutdown, the programmercommands Surveyor's legs and two onmLdivc-1;ional antennacto extend and orders the spacecraft's truLLomitter to high power.After Surveyor separates Vrom the Centaur an automatic

-more- _


38/51

-30-

command is given by the spacecraft to fire explosive boltsto unlock the solar panel. A stepping motor then moves thepanel to a prescribed position. Solar panel deployment canalso be commanded from the ground if the automatic sequencefails.Surveyor will then perform an automatic Sun-seeking man-euver to stabilize the pitch and yaw axes and to align itssolar panel with the Sun for conversion of sunlight to elec-tricity to power the spacecraft. Prior to this event the

spacecraft main battery is providing power.The Sun acquisition sequence begins immediately afterseparation from Centaur and simultaneously with the solar paneldeployment. The nitrogen gas jet system, which is activatedat separation, will first eliminate random pitch, roll andyaw motions resulting from separation from Centaur. Then asequence of controlled roll and yaw turning maneuvers iscommanded for Sun acquisition.Sun sensors aboard Supveyor will provide signals to theattitude control gas jets to stop the spacecraft when it is

pointed at the Sun. Once looked on the Sun, the gas jetswill fire 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 no perform the Sunseeking maneuver automatically, this sequence can be cor-manded from the ground.The next critical step for Surveyor is acquisition ofits radio signal, by the Deep Space Net tracking stations atAscension Island and Johannesburg, South Africa, the first

DSN stations to see Surveyor after launch.It s critical at this point to establish the communi-cations link with the spacecraft to receive telemetry toquickly determine the condition of the spacecraft, for com-mand capability to assure control, and for Doppler measure-ments frotm which velocity and trajectory are computed.The tranimitter can only operate at high power forapproximately one hour wilhuout overheating. It is expected,however, that the ground station will lock on to the space-craft's radio signal within 40 minutes after launch and i.overheating is indicated, the transmitter can be commandedto low power.The next major spacecraft event; after the Sun has beenacquired is Canopus acquisition. Locking on the starCanopus provides a fixed inert~lal. reference for the roll orienta-tion.

-more-


39/51

-31-

Canopus AcquisitionCanupus acquisition will be commanded from the groundabout six hours after launch. The gas jets will fire to rollthe spacecraft at 0.5 degree per second. When the sensorsees the predicted brightness of Canopus (the brightest starin the Southern Hemisphere) it will order the roll to stopand lock on the star. The brightness of the light sourceit is seeing will be telemetered to Earth to verify thatit is locked on Canopus.Verification can also be provided by a ground commandordering a 360 degree roll and the plotting of each light sourcethr sensor sees that is in the sensitivity range of the sensor.(,he sensor will ignore light levels above and below givenintensities.) This star map can be compared with a map pre-pared before launch to verify that the spacecraft is locked onCanopus.Now properly oriented on the Sun and on Canopus, Sur-veyor is in the coast phase of the transit to the Moon.Surveyor is transmitting engineering data to Earth andreceiving commands via one of its omnidirectional antennae.Tracking data is obtained from the pointing direction ofground antenna and observed frequency change (Doppler).The solar panel is providing electrical power andadditional power for peak demands is being provided by one oftwo batteries aboard. The gas jets are firing intermittentlyto keep the craft aligned on the Sun and Canopus.The engineering and tracking inxormation is receivedfrom Surveyor at one of the stations of the Deep Space Net.The data is communicated to the Space Flight Operations

Facility (SFOF) at the Jet Propulsion Laboratory in Pasa-dena where the flight path of the spacecraft is carefullycalculated and the condition of the spacecraft continuouslymonitored.Midcourse Maneuver

Tracking data will be used to determine how large atrajectory correction must be made to land Surveyor In thegiven target area. This trajectory correction, called themidcourse maneuver, is required because of many uncertain-ties in the launch operation that prevent absolute accuracyin placing a spacecraft on a trajectory that will interceptthe Moon precisely at the desired landing point.

The midcourse maneuver is timed to occur over the Goldstonestation of the USN in the Mojave Denert, the tracking stationnearest the S10Ol1 at JPL.-more-


40/51

SURVEYOR MIDCOURSE CORRECTION

CRUISE ATTITUDE

SUN IS - 9 /YAWOR PITCH) TURN

STAR 5--V(ANOPUSSUN AN D CANOPUSREACQXXSMTONERoi TURN --

VERNIER ENGINES BURN

__-


41/51

-32-.

The thrust for the midcourse maneuver will be provided bythe spacecraft's three liquid fuel vernier engines. Total thrustlevel is controlled by an accelerometer at a constant accel-eration equal to 0.1 Earth g (3.2 ft/sec/sec). Pointingerrors are sensed by gyros which can cause the individualengines to change thrust level to correct pitch and yawerrors and swivel one 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 the trajectory, or flight path, Surveyor willbe commanded to roll, then pitch or yaw to achieve thisalignment. Normally, two maneuvers are required, a roll-pitchor a roll-yaw.The duration of the first maneuver is radioed Lo thespacecraft, stored aboard and re-transmitted back to Earthfor verification. Assurei that Surveyor has received theproper information, it Is then commanded to perform thefirst maneuver, When completed, the second maneuver ishandled in the same fashion. With the spacecraft now aligned

properly in space, the number of seconds of required thrust istransmitted to tihe spacecraft, stored, verified and thenexecuted,In the event of a failure of the automatic timer aboardthe spacecraft which checks out the duration of each maneuverturn and firing period, each step in the seqmenco can beperformed by carefully timed ground commands.After completion of the midcourse maneuver, Surveyorreacquires the Sun and Canopus. Again Surieyor is in thecruise mole and the next critical event will be the terminal

maneuver.Terminal Sequence

The first step starts at about 1,000 miles above theMoon's surface. The exact descent maneuvers will depend onthe flight path and orientation of the Surveyor with respectto the Moon and the target area. Normally they will be aroll followed by a yaw or a pitch turn. As in the midcoursemaneuver, the duration times of the maneuvers are radioedto the spacecraft and the gas jets fire to execute the re-qiired -oll and pitch and yaw. The object of the maneuveris to align the main retro solid rocket with the descentpath. To perform the maneuvers, the spaCecratt will breakits lock on the Sun and Canopus. Attitude control will bemaintained by inertial sensors. ayros will sense changes inthe attit de and order the gas jets to fire to maintain thecorrect attitude until the retrorocket is ignited.

-mcrc-


42/51

-32a-

SURVEYOR'TERMINAL DESCENT'1'O LUNAR SURFACECRUISE ATTITUDE lAppromimate Allitudos and Velocilles Given)

PRIEETRO MANEUVER 30 MINBEFORE TOUCHDOWN ALIGNSMAIN RETRO WITH FLIGHT PATH

MAIN RETRO START BY ALTITUDEMARKING RADAR WHICH EJECTSFROM NOZZLE, CRAFT STABILIZEDBlYVERNIER ENGINES AT5? Ml ALTITUDE, 5,900 MPH

A k( MAIN RETRO BURNOUT AND EJECTION,VERNIER RETRO SYSTEM TAKEOVER AT37,000 Ft, 400 MPH

VERNIER ENGINES SHUTOFrAT 14 FT, 3:/, MPH

TOUCHDOWN Al 8 MPH

'


43/51

-33-

With the spacecraft properly aligned, tha altitude mark-ing radar will be activated, by ground command, at approximately200 miles above the Moon's surface. All subsequent terminalevents will be automatically controlled by radars and the flightcontrol programmer. The auxiliary battery will be connectedto help the main battery supply the heavy loads required duringdeneent.At approximately 60 miles' slant range from the Moon'ssurface, the marking radar starts the flight control program-mer clock which then counts down a previously stored delaytime and then commands ignition of the solid propellant mainretro and the three liquid fueled, throttleable vernier engines.The vernier engines maintain a constant spacecraft attitude dur-ing main retro firing in the same manner as during midcoursethrusting.The spacecraft will be traveling at approximabely 6,000miles-per-hour. The main retro will burn out in 40 secondsat about 25,000 feet above the surface after reducing thevelocity to about 250 miles-per-hour. The casing of the mainretro is separated from the spacecraft, on command from theprogrammer 12 seconds after burnout, by explosive bolts andfalls free.After burnout the flight control programmer will controlthe thrust level of the vernier engines until the Radar Alti-meter and Doppler Velocity Senvor (RADVS) locks up on its returnsignals from the Moon's surface.Dascent will then be controlled by the RADVS and the vernierengines. Signale from RADVS will be processed by the flightcontrol electronics to throttle the three vernier engines re-ducing velocity as the altitude decreases. At 13 feet above thesurface, Surveyor will have been slowed to three miles per hour.At this point the engines are shut off and the spacecraft freefalls to the surface.Immediately after landing, flight control power isturned off to conserve battery powcr.

-more-


44/51

-34-

Post-landing Events

of prime interest to the en!tneers who designed Surveyorwill be the engineering telemetry received during the descentand touchdown. Touchdown will be followed by periods of engin-eering telemetry to determine the condition of the spaoecraft.Then a series of wide angle, 200-line television pictures willbe taken.The solar panel and high gain planar array antenna willthen be aligned with the Sun and Earth, respectively. If thehigh-gain antenna is successfully operated to look on Earth,transmission of 600-line television pictures will begin. Ifit is necessary to operate through one of the low-gain, omni-directional antennas, additional 200-line pictures will betransmitted.The lifetime of Surveyor on the surface will be determinedby a number of iactors such as the power remaining in thebatteries in the event that the Sun is not acquired by the solarpanel and spacecraft reaction to the intense heat of the lunarday and the deep cold of the lunar night.

-more-


45/51

-35-ATLAS-C0NTAUR AND SURVEYOR TI-:AMS

NASA HMADQrJARTERS, WASHINGTON, D.C.Dr. Homer E. Newell Associate Administrator forSpace Science andApplicationsOran W. Nicks Director, Lunar and Planetary

ProgramsBenjamin Milwitsky Surveyor Program ManagerV. L. Johnson Director, Launch Vehicle andPropulsion ProgramsT. B. Norris Centaur Program ManagerJET PROPULSION LABORATORY, PASADENA, CALIF.Dr. William H. Pickering DirectorGen. A. R. Luedecke Deputy DirectorHoward H. Haglund Surveyor Project ManagerKermit S. Watkins Assistant Project Manager for

Surveyor OperationsRobert 0. Forney Surveyor Spacecraft System

ManagerDr. Leonard Jaffe Project ScientistDEEP SPACE NETWORKDr. Eberhardt Rechtin Assistant Laboratory Directorfor Tracking and Data Ac-quisition, JPLDr. Nicholas A. Renzetti Surveyor Tracking and Data

Systems Manager, JPLW. E. Larkin JPL Engineer in Charge,

Goldstone

-more -


46/51

1 I

-36-

J, Buckley Pioneer Station Manager,GoldstoneR. J. Fahnestook JPL DSN Resident in AustraliaRe As Leslie Tidbinbilla Station ManagerPhil Tardani JPL DSN Essident in SpainDonald Meyer Robledo Station ManagerAvron Bryan Ascension Station ManagerLEWIS RESEARCH CENTER, CLEVELAND 0.Dz Abe Silverstein DirectorDr,. S C. Himel Assistant Direcoor for LaunchVehiolesEdmund R, Jonash Centaur Project ManagerUINNEDY SPACE CENTER, FLA.Dr. Kurt R. Debus lareotorRobert H. Gray Director of Unmanned LaunchoperationsJohn D. Gossett Cklet, Centaur OperationsPRINCIPAL SCIENTIFIC INVESTIGATORSDr. Eugene Shoemaker TelevisionU.S, Geologioal SurveyDr. Ronald F. Scott Surface SamplerCalirornia Institute ofTechnologyHUGHES AIRCRAFT COMPANY. CULVER CITY. CALIF.Dr. Robert L. Roderick Surveyor Program ant petAssistant Manager -- Lunar

ProgramsRobert 3. Sears Associate Program ManagerRichard R. Ounter Assistant Program Manager

-more-


47/51

-37-

GENERAL DYNAMICS/CONVAIR, SAN DIEGO, CALIF.Grant L. Hanson Vice Presidents Launch VehiclePrograms

KATAND WHITNEY AIRCRAFT DIVISION OF UNITED AIRCRAFT CO.$WZTPAMl MEACH. FL ARichard Anchutze RL-10 Engine Project ManagerHONEYWELL. INC., ST. PETERSBUR2, FLA,R. B. Foster Centaur Guidance ProgramManager

SURVEYOR/ATLAS-CENTAUR SUBCONTRACTORSSurveyor

AlRosearch Division Ground Support EquipmentGarrott CorporationTorrance, Calif.Airite Nitrogen TankE1 Segundo, Calif.Airtek Propellant TanksFansteel Metallurgical Corp.Compton, Calir.Ampex Tape RecorderRedwood City, Calif,Astrodata Deoomutetors and SubaArrierAnaheim, Calif, Discriminator SystemsBll & Howell Company Camera LensChicago, Ill.Bendix Corporation Landing Dynamios stabilityProducts Aerospaoe Division StudySouth Bend, IndianaBorg-Warner Tape RecorderSanta Anas Cali.TErunson Optical Allnent quipm ntKansas City, KansasCarleton Controls Helu RgulatorBuffalo, New York

eorem


48/51

-38-Eagle-Picher Company Auxiliary BatteriesJoplin, Mo.Electric Storage Battery Main BatteriesRaleigh, N.C.Electro-Development Corp,, Strain Gage ElectronicsSeattle, Wash,Electrolechanioal Research DocmutatorsSarasotao Fla.Endevyo Corporation AccelerometersPasadena, CalitfGeneral Bleotro Dynmaias Vidicon TubesCarland, Tex,General Precision, Inc. Spaceorart TV Ground DataAdvanced Products Division Handling SystemLink OroupSunnyvale, Calif,Hellotek Solar ModulesSylzar, Calif.Hi-Shear Corp, Separation DeviceTorrancoo Calif,C Go. Hokarson Mob, Taperature ControlSanta Monica* Calif. UnitHolex SqulbsHollister, Calif.Hon gele Cl Tape Reoorder/ReproducerGeneral Precision, Inc. Floated Rate IntegratedKearfott System. Division GyrosWayne, N. J.KXnetic Main Power SwitchSolana Beach, Calif.Lear Siegler T.Vo Photo RecorderSanta Monica, CalifeMenas o Cas TanksLos Angeles, Calif.

nocremr'C,


49/51

-39-

metoam Magnetron AssemblySale, asMotorola, Ina. Subearrier OscillatorsMilitary Ileabronios DivisionScottsdale# AriseNational Water Uft Co, Landing Shook AbsorberAtlanasoo, Nich.Northrop/Norair landing torHSathorna, Calif.Ryan ATronuteical Co. Rar AltitudiopplerelooityScn Diveoo oalnf Asneor8cnborn Le Fe O8011.graphWaltham Mass*olontilchmAtlnta Systom Test ItpAAlanta, N. .

SLng r-Retrive Pt No CallbretwBr^&4goport,, Maso.Tilemetrioatiml actorSantr Anl,Calif.Uniteol Chemical Corps vtan ritro sNordon Divisionolktanmo Pd$hiokol heDival Corpirnir Propulsion AysteReaotion otors DAviaionDenvlllo, No JoTlnoloy laboratories# Inae Spacecraft irrcrsaerkloya, Calif.Unittof Alroraft Corps Bubcam.ler Ovoillator,Nordon DivisionSouthh4_pton_asV otor Ruboarrier OoolllatorSouthhamptonp Pao

Atl"x"aentaurRooketdyne Diviloon of NA-.5 Propulsion JrstemNorth American Aviation,, Ina.Canoga Parks Calif,

-Noref


50/51

-40-

Thiokol Chemical Corp, LOX and Fuel 8taging ValvesReaction Motors DivisionDenville, N. J,Hadley Co., Inc, Valves, Regulators ndDi connect CouplingFluidgeniao, Inc. RegulatorsOeneral Precision, Inc. Displacement GyrosKearfott DivisionWayne, N.J.Honeywell, Inc. Rate 0yrosAeronautical DivisionFifth Dimension, Inc. CommutatorsBendIx Corp Telepalks and OscillatorsBendix Pacific DivisionFairchild-Hiller LOX Fuel VA Drain ValvesStratos Western DivisionBourns, Inc. Transducers and PotentiometorsWashington Steel Co. Stainless SteelWashington, ft.aoneral nnmmics Insulation Panels and NosePort Worth DivIsion FairingFort Worth, %ox.Pasco Products Division of Soout Pwpos for RL-lO Engineszarg'-tw z Corp.Be~ord, 0,Bell Aerosystm Co. of Attitude Control SystemBell Asrospac Corp.uffalor, . Y.Liquidometer Aeropao lvision Propellant Utillsation Systemimnd Pre IioM roducts, nc.ng tIsland, N.Y.general Prelision, Inc, Cpater fori inertial auiaeKsarfott Division tKSu Nros# Calif.

aore-


51/51

-41-

Goodyear Aerospace DWiv1on Nmlindln Triler |Goodyear ire and Rubber Co.Mo'ono 0.0Isyitems and Instrwents Dmv DstructorsBulova Watoh Co.Plushin.. No Y.Consolidatd Contros Corp Sate an4 Am Initiatorxi Segundo, Calif.Dorg- r Control Division Invorterrkav# Calif3IP1oan Caorp Modules tor elant Utl'tI-oon s . tion aysteGeneral 3eotwio Coo TurbieIqm# NatsSVilckes ivision of Hrdraulio Pp8pe', 1and Corp.

4Trr "LohZdalitt Instintn Ino.oTransduoers an 54dcthe,Nonrovia, Ca0li.RN wt i rits Co. ndurI0s# 0M5sientitfi Data systems amputersSanta Nonioas calif.WV. 0.ledn* drogn MAOVet Va lve*..-.- andtb en

Documents

Surveyor D Press Kit