SA-4 Press Kit

8/8/2019 SA-4 Press Kit

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C This is the first such experiment knownr in rocketry.1 The burning time of the other seven engines will be ex-

tended somewhat to compensate for the loss of thrust, and the* overall performance is expected to be about Whe same as that

of an ideal eight-engine flight.I 3 Several other changes inl the vehicle w~ill contribute toI. the development of the Block II (SA-5 and beyond) version of

Saturn: Some components of future Saturns will be attachedin "kits" to the inert second stage, accelerometers will be

'I used for the first time, a stabilization platform which willbe used acivel, b' nng wi.th the seventh Saturn sill be.'1loan, a KISTRPM System transponder will fly on a passengerbasis, a "Q-Ball" angle of attack device will be mounted on

{ .'the nose cone, and new heat shield insulation at the tail sea-I ;ion will be tested.

This will be the fourth in a series of ten research anddevelopment flights planned for Saturn I, the largest rocketpresently being tested in the United States. By late 1964,the vehicle is expected to be ready for its role in flighttesting the three-man Apollo spacecraft.

This is scheduled as the final booster-only test of therocket. The next Saturn (SA-5), to be launched later this year,will have a live second stage and will have the capability of

- placing 20,000 pounds in Earth orbit.

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The three Saturn vehicles launched to date have madeperfect flights, a rather unusual record, considering the.ize and coniplex!iy of the vehicle and the state-of-the-artadvancements made in its development. 'Bee separate piece,"Previous Saturn I Flighto.")

Saturn I and other Saturn vehicles are being developedunder the direction of the NASA IMarshall Space Flight Center,Huntsville,, Ala., headed by Wernher von Braun. The launch-ing will be conducted by an integrated team of the NASALaunch Operations Center, Cape Canaveral, and the MSFC Launch

- Vehicle Operations Division. Kurt H. Debus, LOC Director,k. ' will be in charge.0 The booster will be oowered by eight H-1 engines dev'%z-

oping 165,000 pounds thrust e-ach,, for a total of 1.3 millionpounds. (After the SA-4 test, the booster's engines will berated at 188,000 pounds thrust or 1.5 million for the stage,)I Again., second and third stages (S-IV and S-V) will be inert1 in this test, ballasted with water to simulate propellantweight. An inert Jupiter nose cone is the payload.

Unlike SA-2 and SA-3., the vwater-laden upper stages willA . lNOT be exploded in the ionosphere. That scienitific experi-

mient, dubbed "Project Hgh Water," has been succes.sully com-pleted as an extra benef'it of Saturn I testing.

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K SA-4 is 165 feet tall, 21-4 feet at mdximm diameter,with a liftof. weight of about 940,000 pounds. The boosterwill carry a propellant load of about 625,000 pounds,, matohingclosely that of SA-1 and SA-2 but some 125,000 poundsor propellant less than SA-3.

The vehicle will be launched on a path 100 degrees eastor north. A smooth tilt program will begin at about the 10%hsecond of flleht ana continue until about the 105th second whemthe rocket will be inclined at 43 desrees from the 2launch v eal. .Xt will pass through the region of imazi dynamic pressw ot .65 seconds after liftoff. Impact Wil1 oocur about seven zinu-t:after liftoff some 229 miles downwange. aximu vetocity wiltXJbe-3, 600 mph.

The trajeCtorzy ror this flight is somewhat shallower thanion previous launches because of different assumedwind and pro-Pulaion condition., At apex., the vehice wrill be 77 miles highaz compared to about 85 miles on earlier launches.

The tilt program for this launch isbased on ei~ht-ongineopzratioa in order to more closely simlate Blocc II operatinGconditions. Thc vehicle will A'ollow a trajectory somewthat :moroshnallow thzui on previous i1lGhto because thetilt program Is"bi.ased" to roellove wind efects which are prominent durinG themointh of NIarch.

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~ jThe overall objectives of the flight are to provide,further c9nfirmation. f the in-f ight performance of thebooster engines, the controlling movements of the fourjoutboard gimballed enginesa, and propellant utilizati on; tofurther verity struactural integrity of the vehicle' s air-

svI frame evaluating stress at critical muoments of flight andj determining vibration and, banding modes; to demonstratesystms;and- to test,nunei'ous launch and flight technqUe.

*and hardware Item *Uhot are to be Incozrpo'at~ed in the,prog=ax.in.the tuture,

Engie~Ot ge imentThe Saturn l booster was designed to. permit the loss

of an engine during flight. When one engin-e is ou~t off.. thefu,~ and oxygen mnanifoldsat the base of the booster allowthe re-routing of propellants that would have been consumedby the dead eng.ne The, other seven engines burn longerthan in an elght-engiVe case, with relatIvely little losain vehicle performance. Although the reliable performanceof the boooster system to date ind~icates th~is feature may

~jnot be a necessity, the purpose of this experiment is toConfirm that an engine-out capability does exist and canbe relied upon in some emergency situations.

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Engine-out tests have been made successfully by MarshallCenter enrgineers, using both small, cold-flo* ,model engines andactual Saturn,I hardware on the static test stand. ThroughI ~laboratory tests and anal.ytical means., it %)Pears that the booster'can lose one and sometimes two engines Without'necessarily [j meaning a loss of the Mission$ depending upon what engine osout at what time, and the degree of demand the mission is Plaginon the launh vehicle,

The SA4ensine-out experiment was placed in the pr'op'aoJ ~~following the second su~ccessful flight test of the Qt'A secondamy purpose is to help designers gain an n1,ghtr1 1 into crYogenic fluid flow prob:lems with a view tow=r asigtingin later' vehicle development pr'ograms.~In this flight, one of the fixed inboard engines (5 i.

be cut Off 100 seconds arter liftoff by a pre-set timer. WhdyI not earlier In flight? As in all such first experiments, thereis smeemnt o 'rsk.Most f the parx'am&-ers desired can beobserved following the 100-second muark in flight, when the powered

f'ight le nearly completed, whereas cutting off the engine earliermight Jeopardize an otherwise successful test mission. -So this isa conservative, first-time-out approach,

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I5 all eight engines operated throughout on.the mission,the four inboard engines would cutoff at 112 seconds. The' loso. one engine at 100 seconds will extend the burning time of theother engines about two seconds. So the othsr three inboardengines will cut off at about 114 secondsp, and the outboardengines at about 121 seconds.

Here are major areas of performance which will be watbxed, closely:

.-uncooled for the remainder of the flight, Initially thsome concern that heat from the other -enines would. disin

9 taerate this engine, alow1in itp or parts of t# to :buCuokc3 andswing over, puncturing the xuel-cooled nozzle 'of nearby engne.This, of oirse, would disable another engine ad cause a irxewhich would likely brn about mission failure. Engine #5 tam-perature will be measured at the edke oC the nozzle, where heatingwill be greatest.

The loss of an engine also somewhat upsets the flow of hotzases on the heat shield which protects the engine compartment.This imbalance-the concentration oC heat in certain areas-wa3of potential concern, but allowances have been made for this IndesiSn, and this should not ofPCr a problem in this flight.

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J, I2. Propellant transexr and utilization. Fuel tank #1

feeds engines 'land W'5.1en #5 goes out, this means that one-half of the flow from that tank will cease; the fuel that wouldhave been consumed by 45 then flows into an interchange connected'with the other engines. It will take zeveral seoonds-possibly10-for the fuel systems to stabilize and maintain an apProximatelyequal level in all tanks. The same is true for the liquid oxygensystem. B3ecause of a natural resistance in the interchage System,the fuel level in tank -,A will be ollahtly higher than in tieother tanks, but the difAerence is no-l1Gible.

The propellant ut~liza~tion in the seven-engino case shouldbe virtually as efficient as if all enGinea were operating.A relatively few potuids of propollant will be added to the normalpropellant reciduals, Which 4n a typical eight-engine case wouldaverage about 8,000 pounds.

OtherF M ision Aspects

Other aspects of the SA-4 mission are sutmarized as follows:

1. Several "Icits" are attacbed to the inert S-IV staGeand inter-stai,, - ullae rockets, chilldown hyjdrogen ducts Z'or thc0-XV o#Lne (I'.^.Chw ,ll '- flovin be.nnlnS ,lith SA-5), andc cabletrut1c tunnlel, Theze adlditiLonz, wfhile thcy resve no u1.cttional pur-- r)e _' tChiz m-szion, hC2p to zinulate the Block II conj1urationaeiodynar.nqcally.


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2. The rour solid propellant retrorockets at thetop of the boosteq willl be fired about 12 seconds folowlniCutotQ of the inboard enines, as on SA-3. There wil.beo noseparation of staaes.A, ,t 3. In the control system, two control aocel5e--I aee being used Lor the firat time. Thea aceleomeo>used to measure tha lteral acceleration In the phplanes. The purpose it to bi-a the vehioleio h -4r!tion and thereby reduce enine swivel angle, and 'thu) structural loading. These accelerometersJ, mounted Oh trhe "idrbeam" assembly at the top of the booster, are being lOwn SO-tive in the v~hicle attitude control system for the tirst time,replacing angle-of-attack meters used previously.

i4. Although the vehicle is controlled by the ST-90(Jupiter) stabilized platform, a prototype of the ST-124 plat-form is being flown as a passenger. As on SA-3, the ST-124Pwill be instrumented and Its performance monitored throughOUtthe flight. It is located in an instrument cannister betweenthe S-I and S-IV stages. This platform will enter the guidanceana control system on an active basis beginning with the seventhSaturn fflight.

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5.A radar altimeter is eing fl1own for the ftirZ, rtine on an experimental basis. When fully developed,, 'thlz{altimeter will allow a precise determnination of a vehicle'strajectory with1 reupeet to altitude up to about 250 miles.It will be flown on Saturn I's while under development and is

A ~expected to be used operationally-on Saturn V.V1 6.Inooperation with. the Atlantic Missile R~ange, this-~ and subsequent Satur'n I'swill cuVy MISA1MK (Missile Tra-'I -Jectory Measurement) System transponder. M1S=RAD, under devel;p9 f

-ment for the Range, is an ele toi ui ytmthatdetermines the position and velocity of a vehicle b' j we of

KYInterferomnater radar mea-surements and trianulation tecbmiqucso'The purpose is to develop a tracking system more accurate thanthose now used. Saturn and certain other vehicles launched atCanaveral are carrying the transponders as passengers to aidin the development of~ he systemn.

7. A small tape recorder is associated with one of the10 telemetry link6s on the Saturn vehicle. Telemetry will berecorded aboard the vehicle as It is transmitted simultaneouslyto Ground stations. Nearly a minute following cutoff of the,booster, a one-minute playback in thre tapo will begin. Thepurpose of this experiment is o find a means of protecting data~inch is lost or partially lost duriar, the vital period' of booster

\~- t1of~re and upper ztaize i-nl tion. Ion-izad conbusrtion -azeft' In


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-S X a- 4r- ---10~i- EN --vehicle antenna areas disturb or kaock. out the signal nor-amally transmitted. By this means, the signal will be 'saved"

and transmitted when the ionization problem is passed..S. As a part of the control system development, aIpassener" ' , -Bai l" trans1ucer which senses the fangle of attao)C

will be. lown in the tip Qo he nqdfied nose cone. This is Ysimilar to a device used for stimilar-puge on the X-15 ar-craft, The cone-shapedr 4Q-ti; 's a abotXt i.e inh lpngA new 18-inch adapter conneabsa it to the,stndArd Jxpiter'nose cone. Thus nosV is t teet loner nnWthe height of the vehicla to 145 feet, three feet tallor thanthe 'first hree Saturns.

9. At the tail section, a new type heat ashe14 insulationhas been applied to some of the panels, to cheek it out in 'light.

10. The booster QutoX'^ sequence is the samne as SA-3 used.Propellant level swtches will cut off the inboard engines whenthe propellant reaches a Given level. The outboard engines willcontiiue until the liquid o:ygen is depleted, about 7 to 8 sec-oad. later. (On SA-1 and SA-2, the outboard enginies were cu-< offautomatically by a timer six secorids a;Zter inboavd engine shut-down. This new syztem allows more complete prop-llant utilization.) '

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-12- raturn, Lauch ComRlex .SA-4 will be the fourth vehicle to be ;ir-d from

Launch Coraple; 34. This $45 million dollar facility is [located on the north end of Cape Canaveral. It was con-structed under the supervision of the Army Corps off 13n-gineers, using criteria established by the NASA LaunchOperations Center.

Here Is a thui >- sketch of Complex 34:* A 45-acre installation, dominated by a movable

structure 310 feet.high and weighing 2,800 tons.* A Launch Control Center -with walls 12 feet thick(), having a steel door two feet thick which weighs 23 tons.wh * icient fuel and liquid oxygen storage facilities

which are capable of pumping.750,000 pounds of liquid propellantinto the big booster in approximately an hour.

* A launching pedestal foundation reinforced by 4,400cubic yards of concrete and 580 tons of steel.

* A total off 100 million pounds of concrete used in con-struction.

* A unique Automratic Growud Control Station, a room 38:4cat wide by 215 feet long, located beneath the concrete anda zteel launching pad.

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Vehi:cle: A total o' 719 measurements will be receivedf'or the rocket, three more than on SA-3. Of these, 102 willbe blockhouse measurements and 617 wtill be in-flight measure-ments.

The telemetry system transmits measurements such as en-Sine turbine temperature and propellant pump revolutions per1 minute; positions o f valves ; temperature of en-gine bearigs,,heat eXchanger outlets, tail skirt, turbine exhaust, high pres-sure spheres used for pressurizing fuel tanks; pressures I

.1 I combustion chambers, propellant tanks, inert upper stages;i C strain and vibration measurements at critical locatiohs on the

rocket; stabilized platform position, velocity measurements;Motion of control actuators, propellant level, battery voltageand current, inverter frequency, etc.

These data will be recorded at telemetry recording stationsat Complex 34 and elsewhere at Canaveral. In addition, 102"blockhouse" measurements will be taken during the countdown.Thesse measurements generally duplicate the most critical launchmeacluremeents listed above; however, the data flow directly tothe Launch Cor.trol Center for irmaediate observation and use bytest conductors.

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Hi) Environmental: As on previous Saturn Plights, NASAand the Air Force will cooperate in measuring the acoustic,vibration and blast effects of the launching. A total ofabout 70 measurements will be made at Launch Complex 34, else-where on Cape Canaveral, on Merritt Island and the mainland upto a distance of about 15 miles from the launch site.

Engineers want to gain more experience in such a measuringprogram, which will become vital in larger rocket projects, andto develop confidence in methods of predicting these phenomena.These studies are made so that the nature, intensity and trans-rission of low-frequency rocket sound will be niown in order toassist in the location of facilities, and, in marginal cases,the selection of firing times with respect to atmosphezic con-ditions.

These measurements will be made by the NASA Launch OperationsCentdr, NASA Marshall Space Flight Center and the Air ForceMissile Test Center.

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.P.ROJ',Cr-: BAC1,:ROUI ADMIIL FAC SHE zThe National Aeronautics and Space Admirnistration and

associated industries are developing three large rockets un-der the project name Saturn.

The first version, Saturn 1, which is now in the testfl.ight phase, will be followed by the Saturn IB and Saturn V.The primary use of Saturn I will be for Slights leading tothe manned exploration of the moon--Projict Apollo, under theoveral l direction of the NASA Office of Manned Space Flight,headed by D. Brainerd Holmes.

The Saturn development program is under th e technicaljJ~\ direction of NASA's George C. Marshall Space Flight Center,

Huntsville, Alabama, headed by Dr. Wernher von Braun, withlaunching conducted by the NASA Launch Operations Center,,directed by Dr. Kurt H. Debus. Hundreds of industrial contrac-tors and suppliers are participating. The booster or first stageresearch and development program is centered at the MarshallCenter; upper stages are being developed by industry under Mar-shallts direction.

BackgroundIn the spring off 1957, detailea studies were started by

Dr. von Braun's roolcot development group at Huntsville on largC,cluster-engine rockets.

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- 6In the late summer of 1958, the group, then working for

the U.S. Army, received authorization from the Department ofDefense's Advanced Research Projects Agency to proceed withdesign and development of a 1.5 million-pound thrust boosterrocket based on the clustered engine concept.

In 1959, technical direcsion of the programwas transfer-

red from the Department of Defense to the National.Aeronauticsand Spaue Administration and on July 1, 1960, the Huntsvilledevelopmeni group was transferred to NASA's newly-establishedMarshall Space Flight Center.

In early 1962, NASA decided to develop a much larger Sa-

turn, the Saturn V, as the Apollo moon rocket,since the Saturn

I will not be capable of placing men on the moon. The SaturnV first stage has five times the first stage thrust of the Sa-turn 1--7.5 million pounds thrust. It Is in early stages ofdevelopment by the'Marzhall Center and associated stage contrac-tors, Boeing Co., North American Aviation, Inc., and DouglasAircraft Co.

In mid-1962, it was decided to pi.n a rocket witha capability between that of Saturn I and. -;urnV, using com-ponents from both programs. This will be the Saturn IB, oor-posed of the first stage of the Saturn I and the third stage ofthe Saturn V. It will be able to orbit some 16 tons--five tonsmore than the Saturn I--and will permit orbital testing of the

* >N entire three-module Apollo spacecraft.before the Saturn V is*s- f .y qualified. Saturn V will be able to place 240,000 pounds

In low Earth or' T send 90,000 pounds to the moon.-more-

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The complete Saturnt I configuration will consist of twostages, S-I and S-IV. The Saturn I vehicles are broken downinto two groups, Block I and Block U1. There are four vehiclesin Block Is the fourth of which will be fired in the next test.

The first 'our rockets in the 10-vehicle research anddevelopment flight program simulate three-stage rockets, althoughonly the first stage is powered. Beginning with SA-5, the firstvehicle in Block II, the Saturn I will consist of two live stages.By malting certain design changes in the original system, it willbe possible to accomplish all assigned missions with two stagesinstead of three.

While the primary purpose of the first 10 flights is toprove the vehicle, flights SA-6 and beyond will have secondarymissions of testing early versions of the Apollo spacecraft.

By 1965, the Saturn I should be ready to place th e mannedApollo into earth orbit for extended flights of up to two weeks.

On th e first five flights, the vehicle is some 1'. .high (SA- 4 is 165). Beginning with th e sixth flight, th e vehicle,with Apollo spacecraft mock-up, will be about 190 feet in height.Beffinning with the fifth flight, aerodynamic fins will be addedat the booster's tail section to Give the Saturn increased eta-

''- biliwy desired for varied missions.-more-

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VolhiciC woigt will varywith missions. SA-4 at liftoff

will weih9)40,000p

Owing are descriptions Of the SaturnI stages:

SKI: The Saturn I first stage (S-I) ispowered by a clus-

ter of eight aoccldtdyne ji-I engineS,each of which Will ulti-

mately produce 188,000 pounds of thrustto give a total of

l,500>0Q0j.he H-I's in the SA-4 launch are ratedat 165,000

pounds thrust each.

The --1 engine, an advanced and compact offspringof the

Jupiter and Thor engine, was selectedbecause of its relative

simplicity, early availability, and provenrelias Itit

r > burns RP-1 (kerosene)fuel and liquid oxygen. Iajor changes

incorporated in the X'-1 include a simplifiedstart sequence using

a solid propellant gas generator and locationof the turbOPumP

on the thrust chamber below the gimbalblock so that the flexible

propellant feed lines to the engine needonly carry low pressure

propellant.

The eight H-1 engines are attached toan eight-legged thrust

fraCe on the aft end of the vehicle,arranged in two square pat-

terr.. The four inboard engines are rigidlyattached and canted

at a three-degree angle to the center line ofthe booster. The

outboard engines are canted at anangle of 6 degrees and mounted

on Gimbals which permit them to beturned through angles of up to

j .~' 7-- degrees to provide control of the vehicleduring first stage

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Nine tanks feed the eirht 11-1 enoinec. Clustered in acircle about a large center tank of 105 inches in diameter areeight smaller tanks, each 70 inches in diameter. The centertank and four outer ones contain liquid oxywJ.-n, while the re-malinne (alternating) four outer tankcs carry the kerosene fuel.The fuel tanks are pressurized by gaseous nitrogen carried in48 fiberglass spheres atop the tanks and the liquid oxygen tanksare pressurized by gaseous oxygen obtained by jssing liquidoxygen through heat exchangers.that are part of each enginepackage.

The fuel tanks as well as those Containing liquid oxygenare interconnected at the base to allow the maintenance of equal( levels in all tanks during buning,. In case one Angina mal-functions and is cut off during flight, this arrargement permitsthe remaining seven engines to consume the fuel and oxygen in-tended for the deaa engina. Thus, the burninS time of the sevenremaining enginez; is increased and there is Little loss in over-all booster performance.

The nine propellant tanks are attached at the top by anei-ht-legged spider beam. This structure supports the upperflight stases.

The first several Saturn flight boosters are being pro-duce4 at MSFC. Later ones will be produced by the Chrysler Corp.at' NASA's Michoud Operations plant, New Orleans, Louisiana.

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S-IV: Tile S-I second stage of the Saturn I vehiclewill be powered by six 15,000 pound thrust Pratt and W.1hitneyRL-10A3 liqxvid hydroger.liquid oxygen engines.

S-IV is 18 feet in diameter and about ILO feet in length.its development was begun in 1960 by the Douglas AircraftMissiles and Space Systems Division in Santa IMonica, California.

The S-IV stage uses an interstage structure which providesspace for the six engines and transmits the load from the upperpart of the rocket to the support points on the stage beneath.This structure will remain with the lower stage upon separationin flight.

The mid-portion of the S-IV is primarily an aluminumcylindrical container composed of the liquid-oxygen tank locatedbelow the larger liquid hydrogen tank.

Attached to the cylindrical section are four small vlllagerockets tro be used to position the propellants during separationand start-up. At the forward end of the cyLlndrical containeris th e structural assembly or forward adapter which will providesupport for the instrument unit and spacecraft. The S-IV is inadvanced development by Douglas. One test model has been firedmar*, times, including a full duration run of seven minutes. Thefirst "live" S-IV will be flown in the last half of 1963.

Guidance and ControlThe initial Saturn guidance and control system (for Block

I) is pr-...arily an adaption of Jupiter system components to meetSaturn reauires ents. -more-


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Saturn will use an all-inertial guidance system.O d Advanced hardware (the ST-124 platform plus digital guidance

system) will be introduced into the system as the programprogresses. Object of the guidance scheme is to provide auniversal system. that is capable of performing a variety ofmission requirements placed on the vehicle to meet payloadobjectives. This adaptive guidance concept will a1low avariety of requirements with a minimum of change..I

Heart of the adaptive guidance scheme is a high-speeddigital computer capable of meeting Saturnis high reliabilitystandards and mission flexibility.

Transportation.

The size of the Saturn stages posed a unique transporta-tion problem. They are too large for conventional rail, high-way or air shipment. Thus water transportation is a necessityand has been a Wajor factor in the selection of manufacture,testing and launch sites.

The first stage of the Saturn I in moved by barge from theMarshall Space Flight Center in Alabama to Canaveral,. via theTennessee, Ohio and Mississippi Rivers and coastal waters. Theroute is more than 2,000 miles long.

The Saturn I second stage (S-iV) will be moved from theWest Coast by s}p, through the Panama Canal.

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SATU1RN INDUSTRIAL PARTICIPATIONActive research, development and production contracts in

the Saturn I and IB program include 27 contracts that are halfmillion dollars or more in size. The contracts are held by 16firms. Addit.lonally, 11 contracts of this amount are supportingboth the Saturn I and Saturn V programs.

These contracts were awarded directly to the firms by theNASA-Marshall Space Flight Center, technical rampager of the Saturndevelopment. In addition, hundreds of companies are participatingto a lesser degree. And most of the holders of prime contractsfrom the government have numerous subcontractors.

Saturn I ContractsThe largest Saturn I contract is held by the Chrysler Corp.

Space Division, Detroit. Chrysler will build S-I stages at theNASA Michoud Operations plant in New Orleans, at an estimated costof $219,451,499.

The next largest contract in the program is held by DouglasMissile and Space Division, Santa Monica, Calif., which has the$125,710,992 prime contract to develop and produce the S-IV stageof the vehicle.

Pratt and Whitney Aircraft of West Palm Beach, Fla., has twocontracts totaling $45,464,511 for the production of RL-10A3 en-gines for the S-IV stage.

H-1 engines for the booster are being furnished by RocketdyneO ivision of North American Aviation, Inc., Canoga Parkc, Calif.,and Neosho, tro., under two contracts totaling $40,683,178.

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0 Bendix Corp. of Teterboro, N. J,, holds three contractstotaling $'3,515,121, for the fabrication of s Abilzed pa ;-form systems for the guidance and control system.

Booster fuel and oxygen tanks, both 70-inch and 105-inchsizes, are being produced by the Ling-Temco-Vought Corp. inDallas, Texas, under two contracts totaling $9,428,736.

Packard-Bell Electl'ronics Corp., tLos Angeles, is providingautomatic checkout systems for $6,548,008.

Republic Aviation Corp. of Farmingdale, N. Y., has twocontracts totaling $6,190,400, providing for the fabricationof S-I components, ground support and test equipment.

Flexonics Division of Calumet and Hecla, Inc., Bartlett,Ill., has two contracts involving $4,978,648 for the manufactureof propellant feed lines and connectors.

International Business Machines Corp. of Rockville, Md.,is providing flight computers and other equipment under twocontracts totaling $5,610,471.

Radio Corp. of America, Van Nuys, Calif., is fabricatingground computer stations and display and console systems undertwo contracts valued at $3,267,904.

Solar Aircraft Co. of San Diego has a $1,155,987 contract for0 development of propellant feed lines.-more-

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--0 -26-Redstone Machine and Tool Co., Huntsville, Ala., has a

$1,049,235 contract for engineering and fabrication cervices.

Arrowhead Products Division of Federal Mogul Bower Bearings,Inc., Long Beach, Calif., is providing vent and pressurizatiCclines under a contract for $824,095.

Design and fabrication of radar altimeters are being doneby Ryan Electronic Co., San Diego, for $6721Q00.

A. 0. Smith Corp., Milwaukee, Wis., 2as a contract for$519,707 to build pressurization spheres.

.0 Saturn I and Saturn V ContractsThe following active contracts are of half million dollars

or greater are supporting both the Saturn I and t4he Saturn Vprograms:

Mason-Rust, New Orleans, $16,052,910, two contracts fo rsupport services for prime production contractors and the NASAstaff at the Michoud Operations plant, New Orleans.

Brown Engineering Co., Huntsville, Ala., $16,005,869, engi-neerIng services for Marshall Center.

Hayes International Corp., Birmingham, Ala.,, $14,186,703a for engineering, design and fabrication services.

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Spaco, Inc., Huntsville, Ala., $3,332,222, engineeringand fabrication services relatng to special tooling.

Progressive Welder and Machine Co., Pontiac, Mich.,$2,408,430, two contracts for tooling and fabrication of majorproduction fixtures.

Cornell Aeronautical LaboratoW. Inc., Buffalo, N. Y.$1J006,437, base heating studies on Saturn stages.

Reynolds Electrical and Engineering Co., Freeport, Texas,Y734;,257, electrical checkout facilities.

9 Vitro Services, Ft. Walton Beach, Fla., $660v000J instru-mentation and control support services, MSFC Test Division.

Lockheed-Georgia Co., Marietta, Ga., $619,'742., fabricationof heat shields, fire walls and other components.

-END-

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