SA-6 Press Kit

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NATIONAL AERONAUTICS AND SPACE ADMINISTRATIO14 S WO 2-4155-*NA-IONA WASHINGTON DC 20546 TEL WO 3-6925FOR RELEASE: WEDNESDAY AM ' sMay 20, 1964

RELEASE NO: 64-113

NASA TO LAUNCH SIXTH SATURN IThe National Aeronautics and Space Administration

will launch the sixth Saturn I flight vehicle (SA-6)from Cape Kennedy, Fla., no earlier than May 26.

Main purpose of the flight is to qualify the launchvehicle further and develop the technology necessary tobuild the more powrful Saturns needed for manned lunarlandings and other space exploration.

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SA-6 will carvy into Earth orbit the first unmanned"boilerplate" model of the Apollo spacecraft which is beingdeveloped to carry three American astronauts to the iloonbefore the end of this decade.

An active guidance svstem will be used on a SaturnCor the first time to steer the second stage of the Saturn Iand the attached Apollo spacecraft into an orbit ran-in6froo L0C) to 140 statute n,'les above the Earth. The SA-6satellite, consisting of tici second stage (S-IV), an instru-ment unit and the Apollo spacecraft will weigh 37,300pounds.

The weight-in-orbit record is held by tne fifthSaturn I (SA-5) launch which put 37,700 pounds in orbitJan. 29. This orbiting package consists of the S-IVstage, instrument unit and a sand-filled nose cone. An"open loop guidance"., or autopilot system, was used in theSA-5 flight.

Other primary missions of the SA-6 flight are totest propulsion additionally, structure and flight con-trcil systems and to prove the technique for separating thesecond stage from the 7irst stage.

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-3-Secondary missions include determining structural

characteristics of the launch escape system, operationalsuitability of Atlantic Missile 1lange ground tracking sta-tions, launch escape system jettison characteristics, anddemonstrating the compatibility of spacecraft researchand development instrumentation and communication systemswith launch vehicle systems.

Five Saturn I's, each generating 1.3 million poundsthrust or more and weighing a million pounds have beensuccessfully launched.

The first four (Block I) rockets had only the boos-ter stage live. Beginning with the Block II Saturn SAG-1all Saturn I's have powered second stages and are capableof placing about 20,000 pounds of useful payload intoEarth orbit.

SA-6 and later vehicles in the series carry early,unmanned models of the Apollo command and service Modules.The last three Saturn I flights (SA-9, SA-8, SA-10) willcarry meteoroid detection satellites.

SA-6 is 190 feet tall and will weigh about ',130,000pounds at liftoff, It consists of four elements: S-Istage, S-IV stage, instrument unit, and an Apollo space-craft ("boilerplate" Command Module, dummy Service Module


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The S-Iv and the ir n crument unit are being flownfor the second time. Thie S-I is undergoing its secondflight test in this (Block II) configuration.

Dr. George E. Mueller, Associate Administrator forManned Space Flight, at NASA Headquarters, is in charge ofall NASA manned space effort, including the development ofthe Saturn vehicle and Apollo spacecraft. The three cen-ters sharing responsibility in the Apollo moon programare the Marshall Space Flight Center, vehicle developer;Manned Spacecraft Center, spacecraft developer; and Ken-nedy Space Center, t1-. launching organization. The cen-ters, reporting directly to Mueller, are headed by Dr.Wernher von Braun, Dr. Robert Gilruth and Dr. Kurt Debus,respectively.

In the SA-6 launching, the centers will be assistedby three firms, Chrysler Corp., Douglas Aircraft Co., andNorth Americaun Aviation, principal contractors for theSaturn I first and second stages and the Apollo spacecraft,respectively.

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DETAILED BACKGROUND INFORMATION ON SA-6

Flight Sequence........... ........................... 6The SA-6 Sal 'llite . . .................... * 8Measuring Program. .......................... .. ... . 10Apollo Spacecraft .............. ............... 12Vehicle Background and Description.. 17Launch Complex. ................ .. . .. .. . .. .. . 31Launch Preparations ............................... 33Optical Systems . ........... ................... 36Tracking Networlc. .......................... . . 40Saturn/Apollo Industrial Participation ............... .42


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FLIGHT SEQUENCE

After ignition the SA-6 will be held to the launchpedestal until all engines are operating smoothly. Liftoffnormally occurs about three seconds after ignition.

SA-6 will be fired on an azimuth of 90 degrees, butafter the first few seconds it will "roll into" its flightazimuth of 105 degrees. The tilt program will begin after15 seconds of flight. The rocket will continue to tiltuntil the 134th second of flight when it will be inclinedat 67 degrees from the launch vertical.

About 70 seconds after liftoff the rocket will passthrough the region of maximum dynamic pressure (max Q)when the aerodynamic pressures exerted on the rocket'sstructure are Greatest. This will occur about 3.5 statutemiles In range and 7.5 statute miles in altitude.

Soon nifer the 100th second of flight there begins acritical series of actions concerning the separation of thetwo stages and the ignition of the S-IV. The steps are asfollows:

(1) At 107 seconds, S-IV (second stage) engine hydro-gen prestart flow begins, lasting 4l l seconds (until S-IVstart-up).

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(2) At 134 seconds the S-I (first stage) propellantlevel switches, which will sense a low level of propellantand initiate the liquid oxygen (LOX) prestart flow in theS-IV, are armed.

(3) At 138 S-IV LOX prestart flow begins.(4) The inboard engines will be cut off at 140 seconds

and the outboard engines will be cut off by an automatictimer (program device) six seconds later. At S-T outboardengine cutoff the vehicle will be traveling about 5,900statute miles per hour at an altitude of about 43 miles anda range of about 56 miles,

(5) Within two seconds, the following sequence takesplace: The S-IV's four solid propellant ullage motorsbegin their three-to-four-second firing; separation commandis given and the explosive bolts attaching the two stagesare fired; the instrument unit (IV) control rate gyro signalsare introduced into the S-IV control system; the S-I's foursolid propellant .etrorockets begin their two-second firingperiod; and the S-IV stage engines are ignited (1.7 secondsafter the separation signal) about 1118 seconds followinglif toff .

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Some 12 seconds after' S-[/tS-Iv separlat.ion, the launchescape tower and the S-LV ullage motor cases are Jettisoned.Active guidance employing the ST-1211 platform, used for thefirst time on SA-6, will start about 16 seconds after S-IVengine ignition. The guidance system will determine contin-ually during flight the most efficient steering commandswhich will result in the requLred conditions for insertioninto orbit. The S-IV engines will operate about 4175 seconds,almost eight minutes. At that time, 10.5 minutes afterliftoff, the S-IV with the instrument unit and unmannedApollo will go into orbit.

At Insertion, the SA-6 satellite will be traveling atabout 16,500 statute miles per hour. Insertion will occurabout 1,300 statute miles downrange from the launcri site.

THE SATELLITE

The length of the portion to be orbited is 80 feet,slightly less than half the length of the entire vehicle.The payload will not be separated from the second stageand instrument unit and there will be no reccvery. Theorbiting body and weights of components include:

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-9-Spent S-IV stage -- 14,200 lbs.Instrument Unit -- 6,1co lbs.Payload (Insert/AdapterApollo Command Module andApollo Service Module)--17,000 lbs.Total 37,300 lbs.

(Initially the orbiting body will have an additional 1,700pounds of weight - propellant residual in the S-IV stagewhich will gradually evaporate).

It is expected that the orbit will have a perigee ofabout 110 statute miles and an apogee of about 140 statutemiles. The planned orbital lifetime of the payload is lessthan a week.

The satellite will have an orbital period of about 88minutes and may tumble slowly. When the satellite is insunlight and the viewer in shadow, it will be easily visiblefrom Earth. Its visibility will vary with altitude, but itwill usually appear about the magnitude of Venus, the even-ing star.

If the vehicle is launched about mid-morning, as planned,the satellite will not be visible to the North Americancontinent on the first evening. It may be visible the nextmorning in the southern Uniced States.

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A minitrack transmitter in the instrument unit willbe operating on a frequency of 136.650 m.c. The systemhas one battery which should assure operation for thevehicle's lifetime.

The telemetry system is expected to operate throughone orbit, providing signals which will be tracked byother ground stations.

The SA-6 flight will allow a test of the major groundtracking networks of the U.S. NASA, the Department ofDefense and the Smithsonian Astrophysical Observatory willtake part in a global ground tracking exercise. NASA'sGoddard Space Flight Center will coord4nate this operation.Early "quick look" tracking and data reduction to determineorbital characteristics will be conducted at the MarshallSpace Flight Center with assistance from several stations.

MEASURING PROGnAM

SA-6 will telemeter to the ground during flight some1310 measurements, as follows: S-I stage, 630; S-IV, 355;Instrument Unit, 210; and spacecraft, 116. Block I Saturns,with only one stage live and carrying no instrument unics,had about 600 flight measurements. SA-5 made about 1200measurements. In addition to the flight measurements, 220"blockhouse measurements" are scheduled to be received in


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The vehicle has 13 flight telemetry systems: sixon the S-I, three on the S-IV and four in the instrumentunit (excluding minitrack). The payload has three.

The telemetry systems transmit such measurements asengine turbine temperature; propellant pump rpm; poistionsof valves; temperature of engine bearings, heat exchangeroutlets, tall skirts, turbine exhaust and nitrogen pressur-ization tanks and payload, pressures in combustion chambers,propellant tanks and payload; strain and vibration through-out the vehicle; stabilized platform position; velocity;motion of control actuators; propellant level; batteryvoltages and currents; inverter frequency.

Optical systems which are being carried for the secondtime on Saturn. Eight motion picture cameras and two tele-vision cameras will record vital functions of rocket opera-tion. Similar optical systems were highly successful on theSA-5 flight.

NASA also will record acoustic, vibration, blasteffects and other measurements of the launching. About 400measurements will be made at Launch Comple;: 37, at otherlocations on Cape Kennedy,, on Merritt Island and on theFlorida Mainland up to a distance of about 15 miles fromtoe launch site. This program is being conducted by theJohn IF. ennedy Space Center, NASA.


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APOLLO SPACECRAFT

The SA-6 vehicle will carry an early, "boilerplate"model of the Apollo Con-and and Service Modules, plus theinsert/adapter which is located beneath the Service Module.The total Apollo weight in orbit will be about 17,000 pounds,more than 5:000 pounds of which will be lead ballast.

The launch escape system, to be Jettisoned during S-IVpowered flight, weighs about three tons and consists of aninert pitch control motor, an inert launch escape motor andnozzle skirt, a spacecraft escape tower with separationmechanism, and necessary instrumentation sensors and wiring.mounted within the nose will be a "Q-ball," a dynamic pres-sure sensor used to measure the angle of the vehicle inflight.

Pitch Control Motor, simulated for this mission, isnine inches in diameter, 22 inches long, and weighs 35 pounds.

Tower Jettison Motor is a solid propellant motor, 26inches in diameter, 47 inches long. it will have a boltflange at the aft end to attach it to the forward end of thelaunch escape motor. The motor has two thrust nozzies,canted at 30 degrees from the motor centerline. Its gr)aswtight is 55 pounds including interstage structures. T:tower Jettison motor develops 33,000 pounds of thrust fo.'one second and burn-out occurs at 1.3 seconds.


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Launch Escape Motor, simulated for this mission, weighsapproximately 4,900 pounds, is 26 inches in diameter andis 183 inches long.

Tower Structure is composed of welded tubular titaniumalloy with truncated rectangular cross-section. It is 120inches long with a base 46 by 50 inches. The tower formsthe intermediate structure between the Command Module andescape motor. A structural skirt is used to attach theescape mctor co the tower. The tower will be covered withan ablative material.

Tower Separation System Consists of explosive bolts ineach of four tower legs. In addition to the conventionalinternal explosive charge, an independent linear shapedcharge is provided at a flattened section on each bolt. Eachdhaige is triggered by a separate initiator. This system pro-vides a redundant means of tower separation.

Command Nodule on SA-6 is a boilerplate aluminum struc-ture simulating size, weight, shape and center of gravity ofthe manned operational spacecraft. It is covered with corkinsulation material to protect the structure from overheating.

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Crew Compartment in the boilerplate Command Moduleuses frame stiffeners of the exterior shell structure toattach mountings for instrumentation, electrical power sys-tem and ballast required to maintain proper weight and cen-ter of gravity. Also included are a main hatch (aluminumalloy structure) for access to the compartment and a forwardaccess way (tubular structure of aluminum) welked to the for-ward bulkhead. This access is provided with a bolted-on cover.

Aft Heat Shield on the boilerplate is similar in shapeto the operational heat shield. It is composed of an innerand outer layer of laminated glass over an aluminum honey-comb core and attached to the Commane Module by four struts.

Forward Compartment Cover on the SA-6 mission, is asheet metal fabricated cover and fiberglass honeycomb radomeassembled together and bolted to the Command Module.

Communications and Instrumentation Systems will handle116 measurements to be telemetered to ground stations.

Environmental Control System provides cool air in acontinuous flow to maintain Command Module ambient temperatureat 80 degrees F., plus or minus 10 degrees. The system con-sists of a storage tank, pump, cold plates, heat exchanger,fan thermal control valves, and quick disconnect valves.Power for this unit is supplied by the electrical power system.


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Electrical Power System consists of two instrumentationbatteries, two pyro-batteries, two logic batteries, a powercontrol box, and a Junction box. The instrumentation bat-teries are 120 ampere/hour units and the pyro batteries arefive ampere/hour units.

Launch Escape System Sequencer serves primarily as thearm/de-arm mechanism for the pyro system. It does notinitiate any sequence in the SA-6 flight. The tower sepa-ration and Jettison motor firing signal is provided by theSaturn instrument unit flight sequencer to the launch escapesystem sequencer. The launch escape system sequencer for-wards this signal to the tower sequencer firing circuits.The sequencer includes two independent and identical sectionsthat perform the same functions. Each section containsseparate pyro and logic batteries and busses, and individualpyro and logic arm/de-arm motor switches.

Service Module and Insert are aluminum structures 154inches in diameter. The Service Module, 124 inches long andthe insert, 52 inches long, are bolted together. The Ser-vice Module is attached to the Command Module by an insert,or non-functioning separation system, bolted to the adapter.The active umbilical system, instrumentation sensors, associ-ated cabling and ballast are contained in the Service Module.


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Also included are reaction control system quadrant packageshaving the same weight, shape, location and aerodynamiccharacteristics as live service module reaction controlsystem packages.

Spacecraft Adapter is an aluminum structure bolted tothe S-IV stage. It is 154 inches in diameter, 92 incheslong, and contains an air conditioning barrier, instrumen-tation sensors and associated cabling.


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VEHICLE BACKGROUND AND DESCRIPTION

Saturn SA-6 is a two-stage 190 feet high vehicle.Liftoff weight is approximately 1,130,000 pounds.

Elements of the SA-6 are the S-I first stage, theS-IV second stage, an instrument unit and a boilerplateApollo payload.

This two-stage vehicle -- second of the Saturn IBlock II configuration -- is capable of placing into alow Earth orbit about 20,000 pounds of useful payload.

(In the case of SA-6, the total weight is greater, but thisincludes the spent S-IV stage, the instrument unit and thepayload adapter, which in a normal mission, would not or-bit with the payload.)

Some 1310 measurements throughout the vehicle willbe monitored during prelaunch and flight.

THE SATURN I

The Saturn I program -- of which SA-6 is the sixthflight vehicle -- grew out of studies made by a groupheaded by Dr. Wernher von Braun in 1957. Initial objectiveof the study was to demonstrate with ground tests thefeasibility of building a large rocket using a cluster of


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small, available engines. In slightly more than a year,a flight program, including the development of high-energyupper stages, was started.

Saturn I has had a remarkably successful test pro-gram and has led to the development of two larger spacevehicles, the Saturn IB and Saturn V. The Saturn I, willnot be used for manned Apollo flights, NASA, in October,1963, cancelled the four manned flights which had beenplanned for Saturn I.

Saturn IB uses virtually the same first stage as theSaturn I,but for its second stage, it uses the 200,000-pound-thrust S-IVB. Originally the S-IVB was designedonly as the third stage of the Saturh V moon rocket. Usingit in the Saturn IB permits an increase over the Saturn Ipayload capability by 50 per cent without the expense ofstarting a new development program.

The Saturn I program will end with the 10th flight.issions of the remaining four vehicles will be to contrib-

ute to the development of the Saturn IB and Saturn V; tolaunch unmanned Apollo boilerplate command and servicemodules (SA-7); and to place into Earth orbit large satel-lites (having wingspan of 100 feet) to detect the presenceand determine the size of meteoroids (SA-9, SA-8, and SA-l1.)


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-19-S-I STAGE DESCRIPTION -- SA-6ts first stage -- the

S-1 -- is a 1.5-million pound thrust booster which is21-1/2 feet in diameter and 80 feet long.

Weight at liftoff of the S-I is some 960,000 pounds.About 850,000 pounds of this weight is propellant.

Major areas of the big stage are the "boattail" (orengine) area, propellant containers and the spider beamarea.

Eight liquid oxygen-kerosene (RP-1) Rocketdyne H-1engines, each developing 188,000 pounds thrust, are moun-ted in the "boattail" area to power the S-I stage. Totalnominal thrust is 1,504,000 pounds.

In the first four Saturn I launchings, the H-1 engineswere operated at 165,000 pounds thrust, giving the stagea total oi 1.3 million pounds thrust. SA-5 was the firstflight test of the propulsion system at its designed rat-ing. The few internal engine changes necessary to increaseperformance primarily increased the flow rate of propellantsinto the combustion chamber. Rocketdyne is uprating theH-1 engine to operate at 200,000 pounds thrust.

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Four inboard engines of S-I are rigidly mounted tothe thrust structure in a square pattern around the cen-terline of the vehicle and are canted outward at a three-degree angle. The outboard engines (six degree cant angle)are gimbal-mounted to permit turning for control. purposesduring the first stage powered flight,

A television camera mounted in the number two enginecompartment will provide for the first time real-timecoverage and a permanent record of the operation of com-ponents on a flight engine. The camera begins operatingjust before liftoff and continues until the stage fallsinto the ocean. It will monitor the operation of propel-lant wrap-around lines, the gas generator, the heat ex-changer, hydraulic actuator arms and flexible flame cur-tains.

Nine tanks feed the eight H-1 engines. Clusteredin a circle about a large center tank 105 inches in diame-ter (Jupiter size) are eight 70-inch diameter (Redstonesize) tanks.

The center tank and four outer ones contain liquidoxygen, the alternate outer tanks hold kerosene fuel.Kerosene tanks are pressurized by gaseous nitrogen carriedin spheres atop the tanks and the liquid oxygen tanks are


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liquid oxygen through heat exchangers that are part ofeach engine package.

SA-6 propellant containers, as have all Block IIvehicle propellant containers, have been lengthened toprovide some 100,000 pounds of additional propellants,At liftoff the LOX in the stage is approximately 600,000pounds and the fuel load is about 250,000 pounds,

Each engine uses 737 pounds of propellant per sec-ond and the total propellant consumption per second is5,900 pounds. There are 320 valves and control devicesgoverning the propellant flow in the stage.

S-I's spider beam area, while structurally support-ing the forward end of the stage, adapts the stage to theS-IV and transmits thrust to the S-IV stage. This assem-bly also provides mounting for retro rockets, film andtelevision cameras, a LOX/SOX (liquid oxygen/solid oxygen)disposal system, which includes five sets of high pressurepneumatic triplex spheres, and various measuring and con-trol components.

The LOX-SOX disposal system prevents unintentionalignition of cool-down LOX, SOX or both, which falls fromthe thrust chambers of the S-IV stage engines during the


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chiildown period prior to the S-IV stage ignition. Gase-ous nitrogen is channeled from storage tanks through sixdispersal manifold rings into the RL-10 thrust chamberareas. This gaseous nitrogen keeps the liquid oxygenfrom freezing during chilldown and allows the gaseousoxygen to escape into the atmosphere.

Eight tail fins (four large and four stubs) on theS-I provide support and hold-down points for launch andincrease aerodynamic stability during flight. Span of thelarger fins -- which measure some nine feet across -- isabout 40 feet.

Eight of the 10 S-I flight stages are being assembledand tested by the Marshall Center. The two other firststages, S-I-8 and S-I-10, and all first stagesfor theSaturn IB are being produced by the Chrysler Corp. atMSFC's Michoud Operations, New Orleans, La,

SA-6's first stage structural fabrication tookapproximately 27 weeks. Final assembly was completed insome 17 weeks.

Fifty-three miles of wiring and 73,000 connectionswere used to join the S-I's 1,708 electrical and elec-tronic components.


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SA-6's first stage was static fired twice duringMay and June, 1963, at the Marshall Center: a short dura-tion firing of 30 seconds and a full duration firing ofnearly 2.5 minutes.

S-IV SECOND STAGE -- The S-IV sta'e is a 90,000-pound-thrust stage powered by six Pratt and Whitney RL-10A3engines, each developing 15,000 pounds thrust. The enginesburn liquid hydrogen and liquid oxygen, a high-energy com-bination which produces more than a third more thrust perpound of propellants than conventional fuels. The use ofsuper-cold hydrogen (it boils at -423 degrees F) presentedseveral problems, the solutions to which represent a con-siderable advancement in the art of rocketry.

S-IV is 18 1/2 feet in diameter, 41 1/2 feet long andweighs about 13,500 pounds empty. It carries about 100,000pounds of propellant -- enough for about eight minutes ofpropelled flight.

Douglas Aircraft Co.'s Missiles and Space Divisionwas awarded the S-IV Development contract in July, 1960.Manu:acturing is done at Santa Monica, Calif., and statictesting at Sacramento, Calif.

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The RL-10 engine is the country's pioneering hydro-gen power3d rocket. Its design was begun by Pratt andWhitney Division of United Aircraft in 1958. It under-went its first in-space operation in a Centaur rocketlate in 1963. It has been ground tested to an unusualdegree and has been shown to be a very reliable engine inthese tests. The engines functioned perfectly in flightsof Centaur AC2 and SA-5.

S-IV is a self-supporting structure designed to per-mit ground handling without pressurization. Basicallythe S-IV is a two-section tank structure which has an in-sulated coamrLn-n bulkhead dividing the tank structure into aforward liquid hydrogen tank and an aft LOX tank.

Unusual techniques used in S-IV include a commonbulkhead to separate propellant tanks, internal insula-tion in the liquid hydrogen tank, a helium heater, stor-ing helium gas in titanium bottles immersed in the liquidh arogen fuel and use of a new system to corntrol pro-pellant use.

The common bulkhead separating the large liquid hy-drogen tank from a smaller liquid oxygen tank is made upof two aluminum domes with fiberglass honeycomb bondedto each to form a rigid "sandwich". The bulkhead mini-mizes heat losses from the liquid oxygen, at -297 degrees F.to the liquid hydrogen, at -423 degrees F.


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-25-The extremely low boiling point of the liquid

hydrogen requires that the fuel tank be insulated tominimize loss through boil-off. Inside surfaces of theliquid hydrogen container have 3/4-inch polyurethanefoam bonded to the walls. Glass cloth, 1/10-inch thick,coated with a polyurethane sealant, covers the foam.The interior of the tank is machine-milled in a waffle-like pattern to reduce weight.

Helium gas which pressurizes the liquid oxygen tankduring flight is stored at liquid hydrogen temperatureto take advantage of the resultant large weight savings.The titanium bottles, in addition, have improved materialproperties at this super low temperature. The helium ispassed through the helium heater to raise its temperatureand expand it prior to entering the liquid oxygen tank.

The RL-10 engine resembles other engines externallybut internally it contains many advances, Most rocketengines use propellant-burning gas generators to drive thepumps which feed propellants to the thrust chamber.

In the RL-10, liquid hydrogen from the pump entersthe cooling jacket surrounding the thrust chamber to coolthe engine, Combustion temperature inside the chamber is6,ooo degrees F. In the cooling jacket the hydrogen


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-26-becomes gaseous and then, still very cold, it passes througha venturi. It expands and drives a turbine which pro-vides power to pump more of the liquid hydrogen into thecooling jacket. The turbine also provides power to pumpliquid oxygen.

S-IV's six engines are mounted on the thrust struc-ture canted six degrees outward from the vehicle's centerline and can be gimballed through about four degrees. TheS-1V stage is controlled by gimballing the six engines inresponse to signzls from the vehicle instrument unit.

The SA-6 second stage was static tested once, for459 seconds, at Douglas Aircraft's test facility nearSacramento, Calif., on Nov. 22, 1963.

INSTRUMENT UNIT -- The SA-6 vehicle maintains sta-bility and alters its flight path by changing the directionof the thrust vectors of the S-I's four outboard enginesor the six engines of the S-TV. Commands for engine gim-balling as well as inflight sequencing of vehicle systemsoriginate in the Instrument Unit (IU).

The IU is located between the S-IV stage and the pay-load. It has five temperature and pressure-controlled areasfor environmental control of the electrical/electronicequipment.

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The unitfs overall height is approximately 91 inchesand the outside fairing height is 58 inches. The 154-inch diameter unit weighs some 6,100 pounds.

The SA-6 IU houses the vehicle guidance and controlsystem, seven tracking sub-systems and four telemetrysub-systems. Other systems include the power supply anddistribution system, the cooling system arid the gaseousnitrogen air bearing supply system,

Four 40-inch diameter tubes arranged at 90 degreesaround a vertical 70-inch diameter center hub make upthe environmentally-controlled portions of the IU. Mostof the unit's instrumentation is housed within the fivetemperature and pressure controJbd tubes. Antennas,horizon sensors, and the umbilical panel for use in groundcheckout and servicing are located on the outside skin.The liquid nitrogen cooling system is attached to the in-side of the structure.

SA-6's guidance and control system is adaptive. Itwill not try to adhere to a predetermined trajectory butwill adapt itself to any foreseeable situation. It con-sists of the ST-124 stabilized Dlatform, the platformelectronic box, guidance signal processor, and digital com-puter,

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On SA-6 the "closed-loop" guidance function is pro-vided by the combination of the stabilized platform (ST-124) system, the guidance signal processor (GSP-24) andthe digital computer (ASC-15). The ST-90 stabilized plat-form active on previous Saturn I flights will provide thetimed tilt program and roll maneuver during S-I flight,The program device sequences the switch over between thetwo stabilized platforms, and shortly thereafter the com-puter introduces signals to guide the S-IV/Apollo intoorbit.

The instrument unit also has two control accelerome-ters which are used to measure the vehicle's lateral ac-celeration in the pitch and yaw planes during the portionof S-I flight where significant aerodynamic forces exist.The purpose is to bias the vehicle into the wind directionand thus reduce engine swivel angle and angle-of-attack.This reduces structural loading. The control accelerometerswere first flown active on SA-4., replacing the local angle-of-attack meters used previously.

Several other systems that were flown on SA-4 and SA-5are being tested again, These include a radar altimeterand a Q-ball transducer.

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-29-Seven separate on-board tracking systems will in-

clude subsystems, that, together with subsystems beingflown on other SA-6 stages will be used in determiningtrajectory for range safety purposes and for vehicle per-formance evaluation. Four of the tracking systems areoperational and used for flight evaluation. The otherthree systems are in the developmental stage.

A tape recorder will record transmitted data ofone of the IU telemetry systems at critical time periods(S-I/S-Iv Separation and around S-IV cutoff) for latertransmission to ground stations.

Some 210 measurements will be transmitted through thefour IU telemetry links to ground stations during theflight.

SA-6 TRANSPORTATION -- All major sect-ions of the 190foot tall SA-6 arrived at Cape Kennedy late in Februray.

The Saturn I booster and instrument unit made the2,000-mile 11-day trip to the Cape aboard the MarshallSpace Flight Center barge "Promise".

The S-IV stage was flown from the Douglas AircraftCo. test facility at Sacramento, Calif., aboard a modifiedStratocruiser known as the "Pregnant Guppy!".


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The Apollo spacecraft boilerplate, complete withlaunch escape system, Command Module, Service Module andrelated ground service equipment and insert/adapter, wasflown to Florida aboard the "Pregnant Guppy" and Air Forceplanes from North American Aviation, Inc., Downey, Calif.,the prime contractor.

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LAUNCH COMPLEX 37

SA-6, will be launched from the 120-acre Launch Complex37 at Cape Kennedy. Complex 37 is just north of Complex 34where the first four Saturns (Block I) were launched. Con-struction of the $65-million facility was begun in 1961 andcompleted in 1963. Its first use was for the launch of SA-5in Jan. 29, 1964.

Complex 37 has dual launch pads and associated facili-ties. The two pads, 1,200 feet apart, are designated "A"and "B". Pad B was completed in time for the launch of SA-5and is being used again for SA-6. Work is still underway onPad A.

Each pad has its own umbilical tower, launch pedestaland automatic ground control station. A single launch con-trol center and mobile service structure serve both pads.The pads also share a central propellant storage and trans-fer system.

The umbilical towers are 268 feet high with a 32 foot-square base. The towers can be heightened to 320 feet ifnecessary for future programs.

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The pads of Complex 37 are served by the LaunchControl Center 1,000 feet away. It is a half-sphere 110feet in diameter and 37 feet high. It's dome is morethan 12 feet thick. More than 3,000 cubic yards of con-crete and 400 tons of steel were used in its construction.

Complex 37 has a 328 foot-tall 7,000,000-pound servicestructure which rolls between Pads A and B to provide accessfor technicians and scientists who check out the Saturnrocket. Atoo is a derrick with a mast 60 feet high. It canlift as much as 60 tonse.

The service stbrcturets 120 foot-square base rides on72 wheels along its tracks at 40 feet per minute. In work-:tng position at either pad, the service structure's weightis removed from the wheels by hydraulic arms lowered ontofoundation assemblies and locked into place.

The SA-6 will be launched from a pedestal 47 feetsquare. In the center of the pedestal a 12-sided, 32 foot-diameter ring allows engine exhaust to escape during launch.Triangular platforms on top of the pedestals provide awork area around the base of the rocket.

Complex 37 has a complete fuel storage and transfersystem for both liquid oxygen/RP-l and liquid oxygen/liquid hydrogen engines. (Complex 34 had no liquid hydrogen


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facilities but is being modified to include them.) Amongthe facilities on Complex 37: a 125,000 gallon storageunit; a 28,000 gallon replenishing tank for storing RP-1(kerosene) fuel; and a 125,000 gallon storage tank{ forliquid hydrogen.

A high-pressure gas facility provides nitrogen andhelium for purging fuel lines, actuating hydraulic systems,etc. for both Complex 37 and nearby Complex 34.

LAUNCH PREPARATIONS

Preparations for the launch phase of SA-6 began withthe arrival by barge of the S-I first stage at the John F.Kennedy Space Center, NASA, Feb. 18. The booster was movedFeb. 19 to Launch Complex 37B and was erected in the ser-vice structure. The Apollo spacecraft arrived at CapeKennedy Feb. 19 and was taken to Hangar AF for checkout.The SA-6 S-IV second stage arrived Bef. 22 and also wastaken to Hangar AF for inspection and weighing.

The S-IV was mechanically mated to the S-I boosterMarch 19. The instrument unit which was brought to theCape with the booster, was erected March 23.


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-34-The Apollo spacecraft was mated April 2 and electrical

mating of the S-I, S-IV and IU was accomplished April 3.

On April 24, radio frequency (RF) checks were madeof the integrated launch vehicle and on May 7 cryogenictanking tests were conducted on both the S-I and S-IVstages.

A simulated flight test was conducted on T-6 days.The S-I stage will be loaded with RP-1 (fuel) on T-2 days.

The 18-hour launch countdown begins on T-l day. Thefirst part of the count, about seven hours long, includesbattery installation, propulsion system checks, ordnanceinstallation and connections.

Part two of the countdown requires 11 hours. Major steps are:

T-10 hours -- radio frequency (RF) checksT- 9 hours -- internal power testT- 8 hours -- final propulsion preparation, S-I and S-IV stagesT- 7 hours -- begin liquid oxygen loading, S-IT- 6 hours -- destruct system connectionsT- 4 hours, 30 minutes -- begin liquid oxygen loading, S-IVT- 3 hours -- remove service structureT- 2 hours, 30 minutes -- begin final phase liquid oxygenloading, S-I


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-35-T-ll0 minutes -- seal launch control center doorsT-105 minutes -- begin liquid hydrogen tanking, S-IVT- 60 minutes -- terminal count begins, pneumatic systemto flight pressure, complete liquidhydrogen tankingT- 24 minutes -- telemeters onT- 20 minutes -- C-band, MISTRAM and UDOP onT- 15 minutes -- range safety command transmitter onT- 13 minutes -- final phase internal power test beginsT- 10 minutes -- telemetry calibrationT- 5 minutes -- ignition arming onT- 4 minutes -- range clearanceT- 3 minutes -- arm destruct systemT- 2 minutes, 33 seconds -- firing command, automaticsequence beginsT- 3 seconds -- ignitionT- 0 -- LIFTOFF


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-36OPTICAL SYSTEMS

SA-6 will carry eight motion picture cameras and twotelevision cameras to view the interiors of two oxygen tanks,S-IV stage separation, retrorocket firing and S-IV stageullage rocket and propulsion system operation. All motionpicture cameras, mounted on the perimeter of tY- spider bean,are slanted outward for ejection. All will cary color filmexcept those monitoring the interior of the oxygen tanks.

This is the second time such an elaborate optical in-strumentation has been carried on a launch vehicle -- thefirst being SA-5. The cameras will record events in severalcritical areas of the rocket, especially the activities in-volved in the separation of the S-I and S-IV stages and inthe ignition of the six RL-10 engines of the S-IV stage.Similar camera systems will be carried on SA-7.

Advantages of photography include high picture resolution,in color if desired, and filming at a high frame rate for laterviewing in "slow motion.' A chief advantage of in-flighttelevision is that the information is acquired in real-timeand might eventually be used as a basis to make decisions.

Motion Picture System

Two film cameras will view the interiors of two LOXtanks, the center and one outer, through optical-fiber bundles.


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Four cameras will view forward along the outside of thevehicle to monitor retrorocket and ullage rocket firing,coasting, aerodynamic flutter of one blowout panel and firingof the S-YV stage. A third interior camera will view sepa-ration of the stages and engine number four of the S-IV, andthe last camera uses an optica:-fiber bundle to monitor theoperation of the solid oxygen-gaseous oxygen disposal system.

The two ameras viewing LOX tank interiors will startat ignition. Five others will start about 40 seconds beforestage separation and will run for about one minute. Thecamera recording panel flutter will operate for 90 secondsbeginning 30 seconds after liftoff

Each camera is enclosed in a capsule whicn has an op-ticany clear quartz window at the forward end. Images arerecorded on 16mm film. The cameras are powered by 28 voltsd.c. supplied by the booster's electrical system.

One camera, equipped with a battery pack, will continuetaking pictures for some 25 seconds after separation of stageseven though the camera will have been ejected at 20 Secondsafter separation. The capsule will have no special stabili-zation system to keep it trained on the booster. However,tests have shown that the camera's move off target is so slowthat the booster will be photographed for several secondsafter capsule ejection.


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All film cameras will be ejected at about 300,000 feetaltitude from individual ejection tubes 20 seconds afterstage separation about 87 miles downrange. Capsules willre-enter the atmosphere at more than 7,000 mph and impactin the Atlantic Ocean about 500 miles from the launch site.

At 1,000 feet altitude a paraballoon will be inflatedto serve as a stabilizer and to decelerate the capsule'sfalll.ng speed to about 90 feet per second before impact. Panelsof the balloons are alternately international orange andcoated with white glass beads. Upon contact with water, ayellow-green flourescent dye will be released. Packed witha radio transmitter atop the balloon is a high-intensityflashing light which produces a flash every two seconds.

Ships and airplanes will be stationed in the impact areato watch for the falling capsules and make speedy recovery.Para-divery of the USAF Air Rescue Service will attach ad-ditional floatation devices to the capsules when they arereached. The primary recovery aid is a SARAH beacon.

Of the ei.ght camera capsules ejected from SA-5, sevenwere recovered.

Telavision SystemThe television system will provide real-time visual in-

formation on the functioning of selected items and a permanent


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-39-visual record for future study and analysis. The cameraswill operate at 30 frames per second from liftoff until S-Iimpact. The television cameras will not be ejected. Imageswill be recorded on video tape at the ground monitoringstationand a kinescope record will be kept as a backup tothe tape.

One camera is mounted forward on the spider beam tomonitor staging and ejection of two motion picture cameracapsules. The other is mounted in the number two engine com-partment of the S-I to view the wrap-around lines, gav gener-ator, heat exchanger, engine curtain and actuator arms.

Video signals are preamplified in the camera and passedon for amplification in the control unit. The control unitprovides aperture correction and focusing control of thecamera, generates the sweep signals for the camera vidiconand introduces the blanking signals to the video output. Asynchronizing generator in the control unit keeps the opera-tiLon of components in sequence.

The transmitter's carrier signal is 860 me. Input powerrequired is 50 watts, and nominal output is five watts. Aseparate power supply will provide voltage for transmitteroperation. The ground receiving, monitoring and recordingstation consists of an antenna system, a parametric amplifier,tape recorder, kinescope recorder, viewing unit and a monitor


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TRACKING NETWORK

The Saturn SA-6 orbital vehicle will be tracked by acombination of tracking and data acquisition facilities in-cluding portions of the manned space flight network and theSTADAN (Satellite Tracking and Data Acquisition Network),supported by the Smithsonian Astrophysical Observatory Net-work and elements of the Department of Defense nationalranges.

The Smithsonian network will supply orbital tracking in-formation through the use of Baker-Nunn cameras.

DOD participating stations are -- Hawaii, Point Arguello,Calif.; White Sands, N.M.; Cape Kennedy, Fla., and others ofthe Atlantic Missile Range such as Patrick Air Force Base,Ascension Island and Antigua.

Manned space flight network stations involved includethose at Bermuda; Woomera, Australia; and NASA's new dual-purpose tracking station at Carnarvon, Australia. Thesestdions will record telemetry for one orbit and "skin-track"with C-band and S-band radar for an indefinite period. Theprecount, countdown and first two orbits will be treated ina manner similar to the Mercur--Atlas missions, with the net-work under the control of a network director at the space


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-41-Although the air-to-ground voice links and command

subsystems will not be used, standard operations procedureswill be employed. Radar data will be transmitted to Goddardin real time and the standard station-to-station voice com-munication network will be used.

The S-IV second stage, the instrument unit and theboilerplate Apollo spacecraft in an orbit of about 110statute miles perigee and 140 statute miles apogee will givethe radars a good target. The telemetry beacons of the launchvehicle may operate for one complete orbit. Beyond this,radar look angle data will be computed at GSFC and determina-tion of daily individual station tracking assignments willbe made.

A minitrack beacon on board the payload will permitthe STADAN stations to continue tracking for the lifetime ofthe vehicle, and computers will periodically update the lookangles.

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-42-SATUJRI /APOLLO INDUSTRIAL PARTICIPATION

SaturnThirty-nine industrial firms hold 130 active research,

development and production contracts totaling more than$500,000 per firm in the Saturn program. In addition, otherfirms hold 44 contracts valued at between $100,000 and$500,000. Of this 174 total, 29 contracts concern Saturn Ionly, seven combine work on Saturns I and IB, three concernIB and V, 47 are for I and V, 13 cover all three configura-tions, two are for IB only and 73 are fo r Saturn V only.

Contracts were awarded directly to the firms by theNASA-Marshall Space Flight Center, technical manager ofSaturn development. Hundreds of other companies are parti-cipating to a lesser degree, most being subcontractors.

Five major firms hold a total of 20 contracts valuedat $1,770,875,523 for work in the Saturn I, IB and V programs.Each firm has contracts totaling more than $100 million.

North American Aviation's Rocketdyne Division. CanogaPark, Calif. and Space and Information Systems DivisionDowney, Calif. head the list with eight contracts totaling$484,807,766. The contracts are for H-1 engines for SaturnI and IB and for F-2 and J-2 engines for the Saturn V (all


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-43-The Boeing Co. of Seattle, holds two contracts listed

at $469,394,362. Boeing is manufacturing S-IC stages forthe mammoth Saturn V Moon rocket at the NASA Michoud Opera-tions plant in New Orleans.

Douglas Aircraft Co., Santa Monica, Calif. holds fourcontracts totaling $400,723,917 for S-IV stages for Saturn Iand S-IVB stages for Saturn IB and V.

Chrysler Corp., Detroit, has three contracts with atotal value of $303,407,591 for manufacturing first stagesfor Saturn I and IB at the Michoud plant.

United Aircraft Corp.'s Pratt and Whitney Aircraft DJ-vision. West Palm Beach, Fla. and East Hartford, Conn. hasthree contracts in support of the Saturn I program. P & Wsupplies RL-10 engines for the S-IV stage. These contractstotal $112,541,525.

Mason-Rust Co., New Orleans, is sixth largest with threecontracts totaling $29,826,624 for facility maintenance andsupport services at the Michoud plant.

Bendix Corp., Teterboro, N.J. has five contracts totaling$25,516,097 in support of Saturn I, IB and V. Bendix is pro-ducing stabilized platform systems for the three rockets.


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International Business Machines Corp., Rockville, Md.has six contracts adding up to $23,431,186 fo r flight com-puters, data adapters and other electronic equipment forSaturns I, IB and V.

Brown Engineering Co., Huntsville, Ala. is next largestwith 10 contracts totaling $23,367,674. Brown is furnishingresearch and development engineering services and fabricationmanpower in the Saturn I and V programs.

Hayes International Corp 0 , Birmingham and Huntsville,Ala. has seven contracts totaling $14;642,734 to provideR & D engineering services and for fabrication and relatedservices.

Federal Mogul Bower Bearings, Inc.'s Arrowhead ProductsDivision, Long Beach, Calif. is designing and testing itemsof S-IC ducting in the Saturn V program under a contract for$13,217,899.

Radio Corp. of America, Van Nuys, Calif. as four con-tracts totaling $10,349,689 providing for ground computerstations, display and console systems and data channels forSaturn I.

Spaco, Inc., Huntsville, has five contracts totaling$4,307,357 for R & D engineering and fabrication services.


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Lockheed-Georgia Co., Marietta, Ga. and Lockheed Mis-siles & Space Co., Sunnyvale, Calif. and Huntsville, Ala.hold six contracts valued at $3,474,835 covering design ofan advanced telemetry system, R&D support on structural com-ponents, and gaidance and control systems, and for missionsupport services.

Other contractors, contract amounts and the services orproducts being provided are:

Republic Aviation Cor , Farmingdale, N.Y., $3,283,234,fabrication of S-I components, ground support and testequipment.

AVCO Corp., Cincinnati, 0. and Nashville, Tenn..,$2,953,730, provide digital decoders and other electronicequipment and components.

Calumet and Hecla, Inc., Flexonics Division, Bartlett,Ill., $2,909,827, manufacture of propellant feed lines andconnectors.

Ryan Aeronautical Co. and Ryan Electronics, San Diego,Calif., $2,616,843, design and fabrication of radar alti-meters and fabrication of bulkhead segments for S-IC fueltanks.

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Whittaker Controls, Iran Nuys, $2,519,950, provide fueland LOX prevalves for Saturn V booster stage.

Cornell Aeronautical Laboratory, Inc., Buffalo, N.Y.$2,45C,312, base heating studies on Saturn stsages.

Wyle Laboratories, Huntsville, $2,378,085, vibrationtesting.

Progressive Welder and Machine Co., Pontiac, Mich.$2,124,116, tooling and fabrication of major fixtures forS-IC construction.

Martin-Marietta Corp., Baltimore, Md. $2,115,884,manufacture of horizon sensors and associated power suppliesand for designing, manufacturing, and testing high pressurehelium storage bottles.

Electronic Communications of St. Petersburg, Fla.$1,876,826, development and fabrication of prototype flightcontrol computers.

AiResearch Division of the Garrett Corp., Phoenix,Ariz. $1,796,299, development of S-IC fuel and LOX pre-valves.

Noithrop Corp. Hawthorne, Calif. and Huntsville,$1,714,066, R&D engineering and mission support services.Nortronics Division Hawthorne, and Norwood, Mass. $1,056,061,fabrication of hermatically sealed gyros and rate gyro pack-


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-47-Telecomputing Corp., yl,013,118, operation of com-

puter facility at Slidell, La.

ARINC Research Corp., Huntsville, $966,368, R & Dengineering services.

Edwards Air Froce Base, Calif. $800,000, study ofblast hazards of rocket propellant.

General Dynamics/Fort Worth, Fort Worth, Tex.,$673,930, fabrication of honeycomb sections.

Redstone Machine and Tool Co., Huntsville, $659,691,engineering and fabrication services.

Auburn Research Foundation, Auburn, Ala., $636,670,research on radio frequency systems and analytical study ofthrust vector control on large space vehicles.

Moog Servo Controls, Aurora, N.Y. $627,610, fabricationof prototype mechanical feedback servo-actuators.

Parker Aircraft Co., Los Angeles, $589,537, R & Dvalves and pre-valves.

Greer Hydraulics, Los Angeles, $588,136, fabricationof a hydraulic system and fabrication and installation ofa fluid power system, Saturn V.

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-48-Goodyear Aercspace Corp., Akron, 0. $514,804, R & D

of materials for Saturn heat shield curtains and honey-comb bonded sandwich structure.

Aerojei eneral, Downey, Calif. $511,959, study of deto-nation of solid propellants and exploding bridgewire ignitionsystem.

Minneapolis-Honeywell, $501,540S, fabrication of rategyros (Boston), fire detection system. or Saturn (LOB Angeles).


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-49-Apollo Command and Service Modules

Thirty-one industrial firms hold active research,development and production contracts totaling more than$500,000 in the Apollo program. An additional 11 firmshold contracts valued at between $100,000 arid $500,000.Some of these contracts were awarded directly to thefirms by the NASA Manned Spacecraft Center, which hasmanagement responsibility for the Apollo program, whileothers were awarded through the principal contractor,North American Aviation, Inc.'s Space and Information Sys-tems Division.

Major contractors for the Apollo Command and ServiceModules are:

North American Aviation Space and Information SystemsDivision, Downey, Calif., principal contractor, $934I,000,000

Aero jet-General Corp2, Space Propulsion Division,Sacramento, Calif., Service Module propulsion motor,+22,200,000.

,Aronca Manufacturing Corp., Middlatown, Ohio, honey-comb panels, `4,000,000.

AVCO Corp., Research and Advanced Development Division,Wilmington, Mass., ablative heat shield, $18,000,000.

Avien Inc., Woodside, N.Y., main communications an-tenna systems, $2,800,o000Beech Aircraft Corp., Wichita, Kan., super critical


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Bell Aerosystems Co., Buffalo, N.Y., positive expul-sion tanks for reaction control system, ;5,700,000.

Beckman Instruments Inc., Fullerton, Calif., dataacquisition equipment, $1,000,000.

Collins Radio Co., Cedar Rapids, Iowa, communicationsand data, '45,000,000.

Elgin National Watch Co., Elgin, Ill., central timingsystem, $1,,000,000.

Electro-Optical Systems, Inc., Micro Systems, Inc.(subsidiary), temperature and pressure transducer instru-mentation, $1,000,000.

Garrett Corp., Air Research Manufacturing Division,Los Angeles, Cal:f., environmental control system,$25,000,000.

General Motors Corp., Allison Division, Indianapolis,Ind., fuel and oxidizer tanks, $3,000,000.

General Precision, Inc., Link Division, Binghamton,N.Y., mission simulator trainer, $12,000,000.

Giannini Controls, Duarte, Calif., reaction controlgaging system, $4,700,000.

Honeywell, Minneapolis, Minn. stabilization and con-trol, $53,000,000.

ITT-Kellogg, Chicago, Ill., in-flight test, $1,600,000.Lockheed Propulsion Co., Redlands, Calif., launch es-

cape and pitch control mctors, $6,400,000.


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1'iotorola Inc., Scottslale, Ariz., up-data link digital,$2,000,000.

Marquardt Corp., Van Huys, Calif., reaction controlmotors (service module), qll,3O0,000.

Northrop Corp., Ventura Division. Newbury Park, Calif.earth landing system, $131,000,000.

Radiation Inc., Melbourne, Fla., automated tele-metry data processing system (during vehicle testing),.p2,000,000.

RCA Electronics, Astron Division, Princeton, N.J.,television cameras, 2,000,000.

Simmonds Precision Products, Tarrytown, N.Y., pL7o-pellant gaging mixture ratio control, 'La,100,000.

Thiokol Chemical Corp. , Elkton Division, Elkton, Md.,escape system jettisoi motor, :,2,200,00C.

'ransco Products_, nc, Venice, Calif., telemetry an-tenna system (research and development), 4i1,000,000.

United Aircraft Corp. , Pratt and Whitney Aircraft DivisicnEast Hartford, Conn., uel cell, 4J9,(7'C,

.Ie2tinghou32 El-c tric Corp., Aer.space ElectricalDlvi:;isLn, Lima, Ohio, s. tic invertcr conversion unit,yu,OOC,OOo.

Douglas Aircraft Co., Inc., Long Beach, Calif., aircraftmcdiication of the C-133, .563o,oo0.

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-52-Daystromr, Inc., Weston Instr'lments and Electronics

Division, Newark, N.J., in-flight instrumentation forEarth orbital phase, G600,000.

Lear Siegler, Inc., Power Equipment Division, Elyria,Ohio, test point disconnect couplings, $500,OOO.

-end-


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SAT RN SA-6 VEHICLE

LAUNCH ESCAPE SYSTEM

COMMAND MODULE

SERVICE MODULE

INSTRUMENT UNIT

190

---- 1LIFTOFF WEMT:.Y S-I STAGE

- I,530,000 LOS.

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SA-6 Press Kit

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