SA-2 Press Kit

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9;.eoottIN EWS R E LEAS ENATIONAL AERONAUTICS AND SPACE ADMINISTRATION

gor A>400 MARYLAND AVENUE, SW, WASHINGTON 25, D.C.TE!EPHONES. WORTH 2-4155-WORTH 3- 1110

./ FOR RELEASE: A.M's SundayApril 22, 1962RELEASE NO. 62-102

NASA TO LAUNCH SECOND SATURN VEHICLEThe second Saturn C-1 heavy space vehicle (SA-2) will belaunched from Cape Canaveral, Florida, by the National Aeronauticsand Space Administration no earlier than April 25, 1962.This vehicle test will be almost identical to that of thefirst Saturn (SA-1) which was launched successfully Oct. 27,1961.The main purposes will be to further test the propulsionsystem of the booster or first stage (S-i) which was launchedsuccessfully October 27, 1961.The Saturn is being developed for the manned lunar landingeffort and other programs of the NASA under the direction of theNASA Office of Manned Space Flight. Technical direction andsupervision of the program is the responsibility of the NASAMarshall Space Flight Center. The NASA-. Launch OperationsCenter will conduct the launching.Only the first Atage of the Saturn will be powered intais flight. Two upper stages (S-IV and S-V) will be inert,ballasted with water to simulate the weight of live stages.The vehicle will be fired over a short ballistic trajectory,with the first stage engines operating for about 115 seconds.Maximum rocket velocity will be about 3,750 mph.The one significant difference between this test andSA-1 will be the addition of a "bonus" scientific experi-ment which will be conducted following the completion ofthe primary mission objectives--i.e., after the boosterengine operation has been completed.

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The Saturn vehicle will be deliberately destroyed some 45seconds after booster burnout. This will occur at about 65miles altitude. The explosion will release in the upperatmosphere most of the 95 tons of water ballast which isbeing carried in the upper stages.The purpose of the experiment, known as "Project High Water,"is to investigate the effects of the unprecedented release of alarge volume of water in this region. This is an experiment in

the physics of the ionosphere, an attempt to see what effectsmight take p5lace due to chemical or physical properties of waterat that altitude. Ice and vapor clouds are expected to form andto be visible for many'miles on a clear day.This is the second of ten Saturn C-1 research and develop-ment flights. After these tests are concluded in 1964, the C-1is expected to be ready for use in the first phase of the Apollomanned lunar landing program--that step being the placement of athree-man spacecraft in earth orbit for up to two weeks.D. Brainerd Holmes, director of the NASA Office of Manned

Space Flight, summed up the launch of the first Saturn as follows:"This firing was one of the most complete successes in thehistory of experimental rocket testing. Eight large engines,each delivering 165,000 pounds of thrust, operated for fullduration.... Every part of this most complex rocket stagethus far attempted by the United States performed well. Theentire 12-hour countdown that preceded the firing was conductedwithout a single technical interruption."An advanced version of the rocket, the Advanced Saturn,will enter R&D flight testing in 1965. With five times the

booster thrust of the C-1, the Advanced Saturn will be usedto send the Apollo spacecraft t:o the moon.The SA-2 vehicle is 1.62 feet in height. It will weighabout 927,000 pounds at liftoff. In these early flights theeight H-1 engines in the booster cluster develop about 165,000pounds thrust each, providing a stage thrust of 1.3 millionpounds. For the fifth flight and thereafter, the engines willhave 188,000 pounds of thrust, giving a stage thrust of 1.5million pounds. Saturn is the world's largest known rocket.SA-2'n boonter will be loaded with about 620,000 pounds

of propellant, short of the designed capacity of 750,000pouidi. This propellant will be burned at a rate of more1-2


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than 5,000 pounds a second. The upper stages will carry 190,000pounds of water, or about 23,000 gailons. The dummy payload isthe nose section of a Jupiter missile, weighing more than a ton.The launching will be conducted at Launch Complex 34, CapeCanaveral, which was completed in June, 1961, and is being usedfor the second time.The main vehicle objectives of the SA-2 flight are:*Determine the in-flight performance of the eight boosterengines, the controlling movements of the four gimballed engines,and engine cutoff and propellant utilization.*Verify structural integrity of the vehicle's airframe,evaluating stress at critical moments of flight and determiningvibration and bending modes.*Further prove the operation of launch facilities for

Saturn vehicles--propellant supply systems, ground supportequipment, automatic checkout equipment, instrumentation,and launch pedestal with hold-down arms.Other flight objectives include confirmation of aerodynamiccharacteristics, correlation of predicted stability and performancewith that encountered in flight, demonstration of the capabilityof the modified ST-90 stabilized platform in the guidance andcontrol system, and demonstration of the vehicle instrumentationsystem.

FLIGHT SEQUENCEThe SA-2 flight plan is essentially the same as SA-1's.The vehicle will, be launched on a path 100 degrees east ofnorth. The peEs. velocity will occur at cutoff---about 3,750 mph.Discounting t1s destruction of the vehicle as it nears the apex,the peak altitude would be about 88 miles and the impact rangewould be about 225 miles from the launch site.A smooth tilt program will begin about the 10th second offlight and continue until about the 100th second when the rocketwill be inclined at 43 degrees against the launch vertical.The vehicle will pass through the condition of maximumdynamic pressure about 60 seconds after liftoff. The fourinner engines will be cut off at about 109 seconds. At about115 seconds, the outer engines will be cut Oft. The range atcutoff will be about 19 railes; the altitude, 35 miles.

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The two sets of engines are cut off in a staggered arrange-ment to prevent unacceptable oscillations which might occur ifall were shut down at the same time. Also a more complete fuelconsumption is permitted.The figures given here assume that all eight engines operatein a normal manner. The Saturn, however, has an "engine-out"capability. This capability, although it will not be fullyrealized until fins are added at the booster tail section onthe fifth flight, allows the failure of one or sometimes twoengines without causing a failure of the mission.The engine-out capability derives from the fact that fueland liquid oxygen t.nks have separate propellant interchangesystems at the base of the booster. In case of an engine failurethese interchange systems make available to the remaining enginesnearly all the propellant which would have been consumed by thedead engine. The total booster burning time is increased tocompensate for the diminished level of thrust.The degree of the rocket's performance with an engine deaddepends on which engine is out and at what point in flight thefailure occurred.

CHANGES IN BOOSTER TANKAGEIn the flight of SA-1, relatively minor instability of thevehicle was noted after 90 seconds of flight. It did not approachthe point of endangering vehicle control or structural integrity.This instability was due to the sloshing of propellants in thebooster's tankage.To remedy this situation, additional anti-slosh baffles(weighing 300 pounds) have been placed in the lower end ofthe eight outer tanks. The 105-inch center liquid oxygen tankhas baffles throughout its length. There has been no change init.

VEHICLE MEASURING PROGRAMSix hundred and 22 channels of information will be radioedfrom the SA-2 vehicle prior to and during flight. Of the total,527 are so-called flight measurements, i. e., data radioed to

ground stations on the many aspects of rocket performancefollowing liftoff.Flight telemetry transmits measurements such as: engineturbine temperature and rpm; positions of valves; temperatures

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of engine bearings, heat exchanger outlets, tail skirt, turbineexhaust, high pressure spheres used for pressuring fuel tanks;pressures in combustion chambers, propellant tanks, inert.upperstages; strain and vibration measurements at critical locationson the rocket; stabilized platform position, velocity measure-ments; motion of engines, propellant level with respect to enginecutoff; and battery voltage and current, and inverter frequency.These data will be recorded at telemetry recording stationsat Complex 34 and elsewhere at Canaveral. In addition, 95 "block-house" measurements will be taken during the countdown and flight.These measurements generally duplicate the most critical nieasure-ments listed above; however, the data flow directly to the LaunchControl Center for immediate observation and use by test conductors.

ENVIRONMENTAL MEASURING PROGRAMSound is of considerable concern to the developers of largeiiunch ve'hicles. The Marshall Space Plight Center conducted athree-year sound investigation effort in connection with the

Saturn development program. The purpose was to study the nature,intensity and transmission of this type of sotmd to aid in thelocation of test and launch facilities in order to assure anadequate degree of protection for personnel and property.The primary program effort to date has monitored staticfirings at Huntsville. The first three or four live firingsat Canaveral will also provide critical data.The sound pressure levels measured during the SA-1 launchgenerally agreed with predicted values. On the day of thelaunch, however, ideal meteorological conditions existed, and,as a consequence, the sound of Saturn as heard in nearby CocoaBeach was no greater than that of certain other rockets launchedat Canaveral. This, however, was a rare condition, and residentsare advised that sound pressure levels on SA-2 and other Saturnsmay be greater, although there will be no danger whatsoever topersons or property.A total of about 50 measurements of acoustic, vibrationand blast will be made on the SA-2 launch. Sensors will belocated at and surrounding Launch Complex 341, lsewhere onCanaveral, on Merritt Island and the mainland up to a distanceof about 10 miles from the launch site.The majority of the measurements are being made by MSFC.Other organizations participating include the Air Force MissileTest Center, the USAF Aeronautical Systems Division's environ-mental survey team, and the U. S. Coast and Geodetic Service,the latter of which will conduct ground vibration measurements.

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SATURN PROJECT BACKGROUND AND VEHICLE FACT SHEETSaturn is a project of the National Aeronautics and SpaceAdministration to develop large rockets for the manned and un-manned exploration of space.The initial version of Saturn, now in the flight test phase,is known as C-1. The primary early use of the vehicle will be inconnection with the nation's manned lunar exploration program,which is directed by the NASA Office of Manned Space Flight,headed by D. Brainerd Holmes.The Saturn development program is under the technicaldirection of NASA George C. Marshall Space Flight Center,Huntsville, Alabama, headed by Dr. Wernher von Braun. Hundredsof industrial contractors and suppliers are participating. Thebooster or first stage program is centered at the Marshall Center;upper stages are being developed by industry.Several versions of the rocket are planned, each morepowerful than its predecessor. Saturns use conventionalchemical rocket propellants in the first stage and high-energychemical propellants in upper stages. Later Saturns may usenuclear propulsion in. some upper stages, for which initialdesign studies are now underway.Saturn is expected to be the major heavy vehicle for U. S.space exploration for a number of years. It is the first largerocket developed specifically for scientific space programs andmanned spaceflight.

BACKGROUNDAs early as the spring of 1957, studies were being made byDr. von Braun's rocket development group at Huntsville on large,cluster-engine rockets.In the late summer of 1958, the group, then working forthe U. S. Army, received authorization from DOD's AdvanceResearch Projects Agency to proceed with design and develop-ment of a 1.5 million-pound thrust booster rocket based onthe clustered engine concept. The program was specificallyset up to demonstrate with captive test firings the feasibilityof the clustered engine concept.By November, 1958, the go-ahead was given to build fourflight-test vehicles and to study development Problems associatedwith reliable multistage Saturn vehicles. Preliminary planningfor upper stages was begun.

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In 1959 technical direction of the program was transferredfrom the Department of Defense to the National Aeronautics andSpace Administration and on July 1, 1960, the Huntsville develop-ment group was transferred to NASA's newly-established MarshallSpace Flight Center.THE SATURN VEHICLE

The current Saturn configuration, C-1, will consist of twostages, S-I and S-IV. The 10-vehicle research and developmentflight test program will end in 1964. In the first four flighttests, only the booster (S-I) will be live. In the others, thebooster and the second stage (S-IV) will be live. While theprimary purpose of the first 10 fli6,ics is to prove the vehicle.The last flights in this series will have secondary missions oftesting early models of the Apollo spacecraft.Initially it was planned to use three live stages in severalof the 10 C-1 flights. Two changes in the program, however, willpermit the accomplishment of the Apollo missions using a two-stagerocket: (1) the thrust of the S-IV stage was increased from 70,000pounds to 90,000 pounds by the addition of two engines and(2) thepropellant capacity of the S-I is to be increased, beginning withthe fifth flight.On the first four flights, with inert upper stages, thevehicle will be about 162 feet high. Beginning with the fifthflight, the vehicle, with Apollo spacecraft mock-up, will beabout 170 feet in height. Also beginning with the fifth flight,aerodynamic fins will be added at the booster's tail section togive the Saturn a capability for broadly-varied missions in thefuture.In the first flights using inert upper stages ballastedwith water, the C-1 configuration will weigh about 927,000pounds at liftoff. In later flights using Apollo hardware

as payload, the C-1 will weigh 1,100,000 pounds.Following are descriptions of the Saturn C-1 stages:S-I: The Saturn C-1 first stage (S-I) is powered by acluster of eight Rocketdyne H-1 engines, each of which willultimately produce 188,000 pounds of thrust to give a totalof 1,500,000 pounds. The H-l's in the SA-2 launch are ratedat 165,000 pounds thrust each.The H-1 engine, an advanced and compact offspring of theJupiter and Thor engine, was selected because of its relative

simplicity, early availability, and proven reliability. Itburns RP-1 (kerosene) fuel and liquid oxygen. Major changesincorporated in the H-1 include a simplified start sequenceusing a solid propellant gas generator and location of theturbopump on the thrust chamber below the gimbal block sothat the flexible propellant feed lines to the engine needonly carry low pressure propellant.2-2


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The eight H-1 engines are attached to an eight-legged thrustframe on the aft end of the vehicle, arranged in two square pat-terns.' The four inboard engines are rigidly attached and cantedat a three-degree angle to the center line of the booster. Theoutboard engines are canted at an angle of 6 degrees and mountedon gimbals which permit them to be turned through angles of upto 7-1/2 degrees to provide control of the vehicle during firststage powered flight.Nine separate tanks feed the eight H-1 engines. Clusteredin a circle about a large center tank of 105 inches in diameterare eight smaller tanks, each 70 inches in diameter. The centertank and four outer ones contain liquid oxygen, while the remain-ing four outer tanks carry the kerosene fuel. The fuel tanks arepressurized by gaseous nitrogen carried in 48 fiberglass spheresatop the tanks and the liquid oxygen tanks are pressurized bygaseous oxygen obtained by passing liquid oxygen through heatexchangers that are part of each engine package.The fuel tanks as well as those containing liquid oxygenare interconnected at the base to allow the maintenance ofequal levels in all tanks during burning. In case one enginemalfunctions and is cut off during flight, this arrangementpermits the remaining seven engines to consume the fuel andoxygen intended for the dead engine. Thus, the burning timeof the seven remaining engines is increased and there is littleloss in overall booster performance.The nine propellant tanks are attached at the top by aneight-legged spider beam.One test model and the flight SA-1 and SA-2 boostershave been successfully static fired a total of more than 25times, including several full duration runs of about 120seconds.The first several Saturn flight boosters are being producedat MSFC. Later ones will be produced by the Chrysler Corp. at.NASA's Michoud Operations plant, New Orleans, Louisiana.S-IV: The S-IV second stage of the C-? vehicle will bepoweredTy six 15,000-pound thrust Pratt and Whitney RL-10liquid hydrogen-liquid oxygen engines.The S-IV is 18 feet in diameter and about 40 feet in length.Its development was begun almost two years ago by the DouglasAircraft Co. in Santa Monica, California.The s-r1f 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 etage beneath.This structure will remain with the lower stage upon separation -

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The mid-portion of the S-IV is primarily an aluminumcylindrical container componed of the liquid-oxygen tanklocated behind the larger liquid hydrogen tank.Attached to the cylindrical section are smal l rocketsto be used in separation of the S-IV from the S-I stage. Atthe forward end of the cylindrical containers is the structural

assembly or forward adapter which will provide support for a-spacecraft or S-V stage. Retrorockets for separation of theS-IV and S-V are mounted on this adapter.S-V: The S-V was required in an earlier Saturn configura-tion iand could be the third stage for some later C-1 operationalflights. It will be a Centaur modified for use on Saturn, usingtwo RL-10 engines of the type employed in the S-IV.

GUIDANCE AND CONTROLThe initial Saturn guidance and control system is primarily

an adaption of Jupiter system components to meet Saturn require-ments. One significant departure is the addition of rate gyrosas sensing elements. Structural bending of the large and rela-tively flexible Saturn required rate gyros for stabilization.Saturn uses all-inertial guidance. More advanced hardwarewill he introduced into the system as the guidance missionsbecome more demanding. Object of the guidance scheme'is toprovide a universal system that is capable of performing avariety of mission requirements placed on the vehicle to meetpayload objectives. This universal guidance concept will allowa variety of requirements with a minimum of changes.Heart of the final guidance scheme is a high-speed digitalcomputer incorporating advanced techniques of design and packag-ing and capable of meeting Saturn's high reliability standardsand difficult missions in terms of programming.For S-I, for example, the guidance system will automaticallygive corrective signals necessary to compensate for deviationsresulting from loss of thrust should one of the eight H-1 enginesfail to perform properly.

SATURN MISSIONSThe two-stage Saturn C-1 vehicle will be capable of placinga payload of about 20,000 pounds in low orbit.The Advanced Saturn, by comparison, will be Able to placemore than 200,000 pounds in low earth orbit or send 80,000 poundsto escape velocity.

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Major early uses of Saturn vehicles will be in connectionwith manned space exploration. The two-stage C-1 will be usedto place Apollo Spacecraft, carrying three men, into earth orbitof up to two weeks duration. The advanced version will send alater model of the same three-man spacecraft to a moon orbitand return. These two steps are in preparation for a mannedlunar landing which could be accomplished using a still largervehicle (Nova5 in a direct flight or with Advanced Saturn employedin orbital rendezvous.

Other possible uses of Saturn include launching of soft-landing stationary or roving payloads of instruments on themoon, probes to Venus and Mars, and 24-hour communicationsatellites. The Saturn may also be used for other mannedearth orbital experiments and as a carrier vehicle fornuclear propulsion tests.TRANSPORTATION

Because of its size, transportation of the S-I fromHuntsville to Cape Canaveral poses a unique problem. It '-stoo large to be moved by conventional rail, highway or airtransport. As a result a barge is used to transport theS-1. The route includes the Tennessee, Ohio and MississippiRivers, the Gulf of Mexico, and intercoastal waterways toCape Canaveral on the east coast of Florida. The distanceis more than 2,000 miles.The S-IV stage is planned to be shipped by water from its

point of manufacture on the West Coast to Cape Canaveral, viathe Panama Canal.

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SATURN LAUNCH Cu'-MT- P,-( 34The second Saturn C-1 vehicle will be fired at Cape03.naveral from a massive site designated "Launch Complex 34,."The niultirmillion dollar facility was completed last year andwas used in the launching of the first Saturn October 27, 1961.It is located on 45 acres at the north end of the Cape.Construction of the complex was done for the NationalAeronautics and Space Administration under the direction ofthe U. S. Army Corps of Engineers, Jacksonville (Fla.) District.Major industrial contractors were Diversified Builders, Inc.,of Montebello, California, for the launch control center; KaiserSteel Corp., Montebello, California, for design and constructionof the service structure; and Henry C. Beck Co. of Palm Beach,Florida, for the launch stand and appurtenant facilities.The general criteria from which the complex was constructedwa3 prepared by the NASA Launch Operations Center, which launchesSaturna from th e complex. LOC is headed by Dr. Kurt H. Debus.Here is a thumbnail sketch of Complex 34:*A 45-acre installation, dominated by a movable structure310 feet high and weighing 2,800 tons.*A Launch Control Center with walls 12 feet thick havinga steel door two feet thick which weighs 23 tons.*Ef'ficien, fuel and liquid oxygen stonage facilitieswhich are capable of pumping 750,000 pounds of liquidpropellant into the big booster in approximately an hour.*A launching pedestal foundation reinforced by 414o00cubic yards of concrete and 580 tons of steel.*A total of 100 million pounds of concrete used inconstruction.*A unique Automatic Ground Control Station, a room 38feet wS&e by 215 feet long, lveated beneath-the concreteand steel launching pad.

FUTURE LAUNCH FACILITIESAbout a mile north of Complex 34 is the site where NASA'snew complex, designated 37, is being constructed. Scheduled

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for first-phase completion late in 1962, this new complex wileventually have two launch pads, served by a common, rail-mounted tower.Farther north of 34 is the site of projected NASA expansionwhich will permit the construction and operation of six ox , morelarge Advanced Saturn and Nova-class launch vehicle complexes.NASA has announced plans for the acquisition of some 80,000acres for this expansion which covers lands north and west ofpresent Cape facilities.The planned complexes will be a base for manned lunar flightsand other missions requiring Advanced Saturn and Nova-class boosters.

YfAJOR EMIEM1ATS OP COMPLEX 34Service Structure: The service structure is 310 feet tall.It has t7in legs measuring 70 feet by 37 feet at the base. Thecenter opening, in which the rocket is situated during checkout,is 56 feet wide.Each of the legs contains a two-floor building which houssWsthe structure's operating equipment and rocket checkout apparatus.

A huge bridge crane of 60-ton capacity is on the structure toerect the rocket on the launching pedestal.Said to be the world's largest movable irhe&eLdi t;tructure,the tower can be controlled by a single operator, situated ina cab at the 27-foot level. The tower is capable of movingfrom 1-1/2 to 40 feet per minute. During-launch it is parkedsome 600 feet from the launch pedestal.Launch Center: The Saturn control building is verysimilair tothEe blockhouses built at Canaveral for Titanand Atlas missiles. It has 10,000 feet of protected floor

space on two levels and an additional 2,150 square feet ofunprotected space in an equipment room which will not beoccupied during launchings.The first floor of the building is to be used by boosterand upper stages contractor personnel involved in tracking andtelemetry operations.The main firing operation is located on the second floor.Equipment includes firing console, test supervision and conductorconsoles and various monitoring and recording panels.Launch Pad: The launch pad, constructed of reinforcedconcrete, is 438 feet in diameter and eight inches thick.Special foundations have been provided for the servicestructure and the launch pedestal.

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Pedestal: The pedestal is looat3ed in the center of thelaunch pad. It is 42 feet square and 27 feet high. The pedestalfoundation contains 4,400 cubic yards of concrete and 580 tons ofsteel. Its depth varies from eight feet at the center to fourfeet at the edges.Bolted to a ring at the top of the pedestal are eight-arms.Four are support arms and the other four both support the rocketand restrain it from liftoff until the proper combustion has been

achieved by all eight H-l engines.Deflector: Beneath the launch pedestal is a rail-mountedflame deflector. This steel structure diverts the 5,000 degreeF. jetstream in two opposite, horizontal directions. A sparedeflector is parked on a spur track on the same side of thepedestal.Umbilical Tower: Adjacent to the launch pedestal is theumbilical tower, the main function of which is to provide elec-trical, hydraulic and pneumatic lines to the rocket.Automatic Ground Control Station: A room known as theautomatic ground control station is located immediately beneatha major portion of the pad. It serves as a distribition pointfor all measuring and checkout equipment, power and high'pressuregas. It is not occupied during launching.Fuel System: RP-1 fuel (kerosene) is provided to the boosterfrom two above-ground tanks located about 950 feet from the launchpedestal. The tanks have a capacity of 30,000 gallons each. Un-like many fueling operations, this one is completely automated,being operated from the control building. Normally the boosterwill be fueled in about 40 minutes.Liquid Oxygen S stem: There are two liquid oxygen (LOX)storage tanks 650afeet from the launch pedestal, well removedfrom the fuel facility. A six-inch line feeds the rockets ata flow rate of up to 2,500 gallons per minute. It takes about40 minutes to fill the Saturn booster's five LOX tanks, whichhold an estimated seven tank car loads.High Pressure Gas acility: There are several uses ofgaseous nitrogen and helium in the preparation and firing ofthe Saturn. A high-pressure gas facility is located about1,100 feet from the launch pad. There are 36 storage vesselsdivided into two groups. Four contain helium used for bubblingthe LOX tanks of the booster. Thirty-two contain nitrogen whichis used for purging fuel and LQX lines, englpe and in..rumeptcompartments, for air bearings and for certain pressure-operatedcomponents such as valves.

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Skimming Basin: A skimming basin is located about 300feet from the edge of the pad on the beach side. This vatis used to collect fuel which might be spilled on the pad,thus preventing it from enteringnormal Cape drainage canals.Water Systems: A water system has been installed on thepad and throughout the service structure, primarily as a safetymeasure. Water is avialable at all work levels on the tower forfire protection. There is a quenching system for use in casefire occurs accidentally ih the "boattail" or engine compartment;

this system is also used to extinguish flame in the engine com-partment in case the engines are cut off immediately after ignitionand before liftoff.Opertion Suort Building: On the opposite side of thecontrol building from the launcih area is an operations supportbuilding which will be used fo r general shop and engineeringactivities in direct support of launch operations.Communication Sstem: A voice communications system hasbeen Insta ll by the Mu-nch Operations Center. The systemconsists of about 200 stations scattered throughout the 45-acreinstallation.

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PROJECT "HIGH WATER"A scientific experiment--known as Project "High Water"--

will be conducted in conjunction with the research and develop-ment flight of the second Saturn space vehicle.The 95 tons of ballast rater carried in the inert upperstages of the Saturn will be released--by explosion--at analtitude of 65 miles. The explosion should occur at about

160 seconds after liftoff and -Z large cloud of ice particlesis expected to be formed from L.vater released in this nearvacuum.The ice and vapor cloud i., xpected to be visible toviewers in the Cape Canaveral ticinlty.This scientific experiment is sponsored by the NASA Officeof Space Sciences, with mar.- organizations making independentobservations. It is being ) ,.'ned and coordinated by the MarshallSpace Flight Center's Research ?rojects Division.Pro4ect High Water will not interfere in any way with theflight of SA-2. The objectives of the flight test will havebeen met at the time the vehicle is exploded. The water in theA inert upper stages has to be carried by the vehicle for ballast,s'mulating the weight of fuel later "live" stages will carry.Very little special vehicle preparation is required in thevehicle to carry the explosive charges The explosives (prima-cord and shaped charges) are installed in the upper stages andwill be activated by ground command, using the normal destructsystem of the booster.

Scientific ObjectivesBroadly, she objective of the experiment is to observethe effect of this large mass of water on the upper region ofthe atmosphere or lower ionosphere. Data obtained should beof much value in defining the normal state of this area,scientists say. High Water project technicians are particularlyinterested in the .chemical and physical effects the releasedwater vapor may have on the "high atmosphere."This Is thought to be the largest such release of waterin this altitude region.As a preliminary to the experiment, a small scale waterrelease was conducted March 2 by NASA's Goddard Center in

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Greenbelt, Maryland. About 40 pounds of water was released atan altitude of 65 miles from a Nike Cajun rocket launched fromthe NASA Wallops Station, Virginia, shortly before sunrise. Theice cloud formed by this experiment was visible from as far awayas Washington, D. C.Sequence of Experiment

The explosive charges attaihed to the Saturn vehicle willbe initiated by a radio signal from the ground when the rocketreaches the altitude of prime interesU-t-about 65 miles. If alleight booster engines operate properly, this will occur about160 seconds after liftoff. The vehicle will be about 50 milesdowri the Atlantic Missile Range on its trajectory. The vehiclewill be broken into several pieces and its components willgenerally follow the normal trajectory down range.The water will immediately boil at the time of the explo-sion. In boiling, an estimated 15 per cent of the water willevaporate alway immediately--the remaining 80-85 tons will form

into a cloud of very small ice particles along the remainderof-the vehicle trajectory.Persons watching from Cape Canaveral should see (on a clearday a large cloud immediately after the explosion. The cloudof The particles will continue on down the intended Saturn tra-jectory, gradually thinning out and perhaps forming a vaporcloud underneath the trajectory.Although the cloud will quickly fade as far as naked eyeobservation is concerned, it will remain enough intact forobservations to be made by instruments for several minutes to

several hours after the water is released.The cloud will be observed by a large number of camerasand radar devices operating at Cape Canaveral and nearby onthe Florida mainland, on aircraft flying patterns all alongthe trajectory at various altItudes, and by tracking cameraslocated on Grand Bahama Island.Many of the observations will be made from the time ofthe release until after dark on the day of the launch, dependingupon the persistence of the cloud.Twenty-two ground-based cameras will take part in theexperiment at various locations along the trajectory, accord-ing to tentative indications from the many participants.

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Ten or more aircraft will provide camera coverage.Thi.rteen radars of the search, track and weather type willbe used, as well as ionosondes in three locations.Instruments will be devoted to various types of measure-ments according to the major interests of the snonsors. Someexamples are: track brightest object or ice for* rajectoryinformation, track In release area xor cloud growth and turbu-

lence, make triangulation measurements for cloud position,oblique view angle of cloud by radiometers with selectablefilters, radar scan from various angles, and measure air glow.To fully observe and study the formation, growth and dis-position of the cloud, NASA haE invited several agencies toparticipate In this experiment.Several American organization3--including the three armedservices--and British and Canadian agencies will carry out.important tracking and observation roles independently.The following are participating in the experiment:The U. S. Army, Navty and Air Force, Advanced ResearchProjects Agency of the Department of Defense, U. S. WeatherBureau, National Bureau of Standards, British Air Ministry,Canadian Armament Research and Development Establishment,Aerojet General Corp., Stanford Research Institute, DeviceDevelopment Corp., University of Michigan, Georgia Instituteof Technology, University of Pittsburgh, Geophysics Corp. ofAmerica, and the University of Colorado.

Project ManagementThe project is being sponsored by the Office of SpaceSciences, NASA Headquarters, under the direction of Dr. HomerNewell. Ray Miller is project officer. The Marshall Center'sResearch Projects Division, directed by Dr. Ernst Stuhlinger,is coordinating the scientific obuervations. The Physics andAstrophysics Branch of Marshall's RPD, headed by Dr. C. A.Lundquist, is in charge of the project. Working closely withLundquist on High Water are Dr. W. G. Johnson and Ray Hembree.

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THE SATURN C-1 TEAM

The Saturn C-1 space vehicle system is being developedjointly by government agencies and private industry under thedirection of she National Aeronautics and Space Administration.D. Brainerd Holmes, as director of NASA's Office of MannedSpace Flight, is in charge of the Saturn development program

through his Launch Vehicle and Propulsion Office, Milton Rosen,director. The program is managed for NASA by Richard B. Canright,assistant director for vehicles, rho has been associated withSaturn since its inception. Saturn program chief is W. M. Shempp.Development of the Saturn system is under the technicaldirection of the George C. Marshall Space Flight Centel-,Huntsville, Alabama. Dr. Wernher von Braun is director.Deputy director for research and development is Dr. EberhardF. M. Rees, and Harry H. Gorman is deputy director foradministration.Dr. Oswald It. ange is director of MSFC's Saturn SystemsOffice, K. K, Dannenberg is his deputy, and Robert Lindstromis C-1 project manager.Other Marshall technical offices and research and develop-ment divisions and their directors are:Aeroballistics, Dr. Ernst E. Geissler; Computation,Helmut Hoelzer; Manufacturing Engineering, Werner Kuers;Future Projects, Heinz H. Koelle; Astrionics, Dr. WalterHaeussermann; Light and Medium Vehicles, Hans Hueter; CentralPlanning, Hans H. Maus; Research Projects, Dr. Ernst Stuhlinger;

Propulsion and Vehicle Engineering, William A. Mrazek; QualityAssurance, Dieter Grau; Test, Karl L. Heimburg; Launch VehicleOperations, Dr. Hans F. Gruene.Dr. Kurt H. Debus, director of NASA's Launch OperationsCenter, Cape Canaveral, Florida, has charge of Saturn launchactivities. Albert Zeiler is chief of LOC's mechanical office,and Carl Sendler is chief of measurements and tracking. Testsupervisor is Robert Moser. Rocco Petrone is chief of theSaturn project office.The Marshall Center, whose personnel developed theJupiter C, Juno II and Mercury-Redstone rockets, Is fab-ricating and assembling the first Saturn flight boosters,the four inert second (S-IV) stages and conducting relatedresearch throughout the program.

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More than 80 per cent of Marshall's Saturn budget, how-ever, is going directly to private industry and other governmentagencies. And much of the remaining money is awarded outside ofNASA to federal agencies for various technical and administrativesupport.The following is a cumulative list of Saturn developmentand manufacturing contracts in the amount of $25,000 and aboveawarded from July 1, 1960 (the date the program was officiallytransferred to NASA from the Army) through February, 1962. Thesecontracts, which include the name of the organization, the dollaramount received and a brief description of the services or goodspurchased, are listed alphabetically by state, city and name ofthe recipient.

ALABAMA:Auburn -- Auburn Research Foundation, Inc.., $273,752,research and study of telemetering and radar systems, andrelated engineering and fabrication services.Birmingham -- General Electric Co., $58,397, electricalcomponents; H. L. Eakew & Sons, $78,922, test equipment; Leedsand Northrup Co., $25,666, strip chart recorders; Linde Co.,$92,996, liquid cOxygen and liquid nitrogen; Lynn-DickersonMachine Co., Inc., $63,170, mechanical parts and assemblies;Mg Electronics & Equipment Co., $25,434, electrical measuringinstruments; Mill & Textile Supply Co., $30,104, manufacturingtooling; The Hayes International Corp., $17,500,214, engineeringman-hours, and manufacturing, assembling and testing of Saturntooling, components and launch complex equipment.Decatur -- Pearce & Gresham Co., $56,355, modification

of test facilities at the Marshall Center.Huntsville -- Arde Engineering Division of Arde Associates,$75,616, services related to wind tunnel testing of space vehiclemodels and components; Brown Engineering Company, Inc., *12,260,736,engineering man-hours, research on vehicle components, and manufac-ture of Saturn booster flight assemblies and related tooling;Electro Mechanical Research, $33,336, electronic equipment;International Business MachinesCorp., $30,520, electronic equip-ment; Minneapolis Honeywell Regulator Co., $76,200, Saturnguidance components; Redstone Machine and Tool Co., $',179,512,fabrication of booster assemblies and related tooling; Space

Craft, Inc., $171,295, design, development and manufacture ofelectronic components and systems; Spaco Manufacturing Co.,$1,873,102, fabrication and assembly of SA-2 assemblies and5-2


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associated equipment; Southerland Blue Print Co., $33,764,drafting equipment; Westinghouse Electric Corp., $25,000,electrical components; Redstone Arsenal -- U. S. ArmyOrdnance Missile Command, $8941,738, technical and adminis-trative support of Saturn development program.ARKANSAS:

Little Rock -- A.R. & T. Electronics, Inc., $25,289,design, fabrication and test of electronic equipment.ARIZONA:

Scottsdale -- Motorola, Inc., $146,833, radar equipmentand electronic components.CALIFORNIA:

Anaheim - Beckman Instruments, Inc., $172,965, design,development and fabrication or6 radio frequency instrumentation;Ling Temco Electronics, Inc., $76,635, electrically drivenvibration system for structural testing of flight vehicles.Arcadia -- D. B. Milliken Co., $98X755, photographicequipment.Canoga Park -- Rocketdyne Divi-ion, North ;Americ^a Aviation,Inc., $21,832,030, development and manufacture of Saturn H-1engines.Culver City -- American Electron.ics Inc. $35,270, elec-trical components; Hughes Aircrrft Co., W9,776, materialsresearch and development; Micro flee Produxcts, Inc., $102,000,fabrication and assembly suppo.-.t equipment for Saturn booster.Dowmey -- Space and InformalIon Systems Division, NorthAmerican Aviation, Inc., $1,210,L497, study of Saturn boosterrecoverx system, study of space vehicles in the two-to-threemillion pound thiu"-t class, fabrication of interstage fairingsbetween Saturn ts first and second stages, and manufacture ofelectronic c^onponents.Glendale -- Frebank Co., $77,621, design and manufactureof thrust, hydraulic, fuel tank and liquid oxygen tank pressureswitches; General Precision, Inc., $509,660, design and develop-ment of electronic equipment for vehicle systems.Hawthorne -- Nortronics, $311.,317, engineering and fauri-cation of Saturn electronic components and systems; Servomech-anisms, Inc., $67.554L, electronic equipment.

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Long Btach -- Arrol;h,:ad Products Division, Federal MogulBow;er Bearings, Inc., $1,427,894, development and testing ofmechanical components for vent, prczsurization and propellantfeed lines in booster.Los Alamitos -- Arrowhead Proxducts Division, Federal MogulBowter Bearings, Inc., $160,110, engineering and fabricationservices in support of Saturn development program.Los Angeles -- Acoustics Associates, Inc., $74,200, pro-duction of liquid oxygen and fuel -ensing instrunents; AiResearchManufacturing Co., 130,345, fabr.ication of air conditioning pack-age; Arnowu Corp., $1,573,292, telemetry and related electronicsystem components; Master Specialties Co., $46,930, lamp assemblies.Packard Bell Electronics Corp., $2,084,992, automatic check-out system for flight boosters; Parker Aircraft Co., $472,610,design, development and fabrication of valve systems fcr flightboosters and related studios of fabrication techniques; SpaceTec.hnology Laboratories, Inc., $49,910, study of -methodsforassembling Saturn-class vehicles in both horizontal and verticalpositions.Manhattan Beach -- U. S. Chemical Milling Corp., $55,957,manufacture of 70-inch-diaxiuter spherical bulkheads and relatedstructural components for booster development program.Monrovia -- Consolidated Systems Corp., $141,290, highspeed data processing system; Spectralab Instrument Co.,$26,550, ultra-high frequency transmitter.North Hollyvtood -- Bendix Corp., $115,265, electroniccomponents and development of a separation indicating device

for use in later live multistage launching of Saturn vehicles.Oakland -- Noble Co., $95,475, services and modificationon Saturn service structure.Oxnard -- American Brake Shoe Co., $30,810, pumps forSaturn hydraulic system.?alo Alto -- Hewlett Packard Co., $30,135, electroniccomponents.Pasadena -- California Institute of Technology, $40,847,

research on failure of equipment when subject to vibration;Resdel Engineering Corp., $138,99S6, design, development andfabrication of radio equipment; Wallace 0. Leonard, Inc.,$30 442, liquid oxygen valves; Wiancko Engineering Co.,$104,785, electrical equipment.5-4


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Redwood City -- Ampex Corp., $252,302, tape recordingequipment and the maintenance and repair of Marshall Center7owned magnetic tape recorders.Riverside -- Bourns, Inc., $70,280, pressure relay systems.Sacramento -- Aerojet General Corp., $80,174, manufactureand delivery of small solid propellant rocket motors for futureSaturn vehicles.San Carlos -- Lenkurt Electric Co., $27,660, feasibilityand development study of telemetry system for flight application.San Diego -- General Dynamics/Astronautics Division, $848,753,fabrication of four inert third .(S-V) stages for early Saturn C-1research and development flights, research and development ofmethods for preventing corrosion of metals used in the Saturnvehicle system; Ryan Aeronautical Corp., $220,828, developmentof technique for explosive forming metal structures, and study

of recovery system for Saturn booster; Ryan Electronics Division,Ryan Aeronautical Corp., $200,000, design, development, test andfabrication of radar altimeter for Saturn vehicles; P. M. Elec-tronics, Inc., $35,700, electrical components and measuringinstruments; Solar Aircraft Co., $268,065, Saturn assemblycomponents.San Jose -- Jennings Radio Manufacturing Co., $34,150,electrical components.Santa Ana -- Borg Warner Corp., $66,998, electroniccomponents.Santa Monica -- Douglas Aircraft Co., $81,622,822,development and fabrication of S-IV and S-IVB Saturn stages.Van Nuys -- Networks Electronics Corp., $35,215, electricalcomponents; Radio Corporation of America, $2,487,795, developmentand fabrication of three Siturn ground computer systems, andengineering studies and system modification of Saturn launchcomputer complex; Waugh Engineering Co., $68,708, turbineflowmeters.COLORADO:Denver -- Cryogenic Engineering Co., $49,950, high pressureliquid oxygen Ed. iquid hydrogen test systems.

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CONNECTICUT:New Haven -- Textron Electronics, Inc., $62,347, electronicequipment.Norwalk - Perkin-Elmer Corp., $187,295, design, developmentand fabrication of optical alignment of instruments.Wallingford -- Revere Corp. of America, $32,760, weightmeasuring systems.

DISTRICT OF COLUMBIA:U. S. Air Force Air Research and Development Command,$28,030,520, acquisition of Saturn rocket fuel, procurementof test equipment and related Saturn development items, andadministration of funds to develop and/or procure H-1 engines,RL-10 upper stage engirns, S-V stage and transportation facilities;U. S. Naval Weapons P3ant, $113,950, design and manufacture ofSaturn components and test equipment.

FLORIDA:Jacknsonville -- U. S. Arnrj Corps of Engineers, $28,000,design and construction of mooring facilities for Saturn bargeat Cape Canaveral, Florida.Melbourne -- Radiation, Inc., $32,000, development, designand fabrication of analog to digital coimputer.Orlando -- Dynatronics, Inc., $488,503, design, developmentand fabrication of telemetry playback station, and delivery ofrelated electronic components; Mechtron Corp., $38,154, designand fabrication of electronic checkout equipment for Saturnvehicle; Ortronix, Inc., airborne telemetry systems.Patrick Air Force Base -- U. S. Air Force Missile TestCenter, $566,000, provision of propellants for rocket andground support equipment, and a vehicle test system.Sarasota -- Electro-Mechanical Research, Inc., $58,150,electronic equipment.St. Petersburg -- Electronic Communications, Inc.,$556,992, development and fabrication of flight computersand related components; Minneapolis Honeywell RegulatorCo., $764LI,0o0, modification of Centaur guidance packageto meet the requirements of Saturn missions, and provisionof gyros, accelerometers and related guidance instrumentation.

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Tampa -- Color Corp. of America, $25,225, photographicreproduction services.West Palm Beach -- Air Products, Inc., $116,025, liquidhydrogen rocket fuel; Pratt & Whitney Division, United Aircraft,$15,380,470, research, development and manufacture of RL-10liquid oxygen-liquid hydrogen engine for use in Saturn upperstages.

GEORGIA:Atlanta -- Ampex Corp., $154,715, magnetic tape recordingsystems and supplies; General Services Administration, $29,005,office supplies and furnishings; Scientific-Atlanta, Inc.,$79,000, design, development and.fabrication of automatictracking antenna system.Marietta -- Lockheed Aircraft Corp., $2,231,572, develop-ment of booster pressure and functional checkout equipment, andfurnishing of additional engineering and fabrication servicesin support of booster development effort.

ILLINOIS:Bartlett -- Flexonics Division, Calumet & Hecla, Inc.,$4,896,278, engineering, design, fabrication and testing ofvent pressurizing and propellant feed line assemblies, andrelated items necessary in manufacture of Saturn boosters.Chicago -- SciakX Brothers, Inc., $45,000, weldingsystem; Vapor Corp., $20,500, air supply temperaturecontroller for air bearing systems.Joliet -- A. L. Mechling Barge Lines; Inc., $335,859,towing of Saturn barges from Huntsville to Cape Canaveral.Lebanon -- Herrington Co., Inc., $29,887, compressorsystem.Morton Grove -- Cook Electric Co., $79,030, design,development and fabrication of cjectable, recoverable moviecamera packages for Saturn vehicle.

INDIANA:Fort Wayne -- I. T. T. Industrial Laboratories, $68,297,

design and construction of controlled storage televisionequipnrint.5-7


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Indianapolis -- Hugh J. Baker Co., $118,537, fabrication,delivery, installation and checkout of Saturn booster assemblygantries at Huntsville, Alabama.Muncie -- Lift-A-Loft Co., $79,445, mobile personnel lifter.

IOWA:Davenport -- Bendix Corp., $626,576, design, developmentand fabrication of l.quid level gaging systems and sensors.

KENTUCKY:Lexington -- Mason-Rust, $1, 215,128, support services forNASA Michoud Operations where Saturn C1 and C-5 boosters willbe manufactured.

LOUISIANA:Harvey -- Avondale Shipyard, Inc., $44,373, modificationof Saturn barge.

MARYIATD:Aberdeen Proving Crounds, $70,800, wind tunnel tests ofSaturn configuration models.Baltimore -- Martin Co., $455,849, heat exchanger assembliesfor boosters.Rockville -- Defense Electronics, Inc., $149,000, design,development and fabrication of telemetry pre-detection record-ing system; International Business MachinesCorp., $1,670,037,study for application of automatic data processing and digital

computing systems, and furnishing of test equipment for IBMmachine"..MASSt.AHUSE71.S:

Ashland -- Fenwal, Inc., $264,571, heat measuring instru-ments, and general engineering and fabrication services.Boston -- Minneapolis Honeywell Regulator Co., $107,338,gyro packages.Burlington -- Dynametrics Corp., $96,411, automatic

calibration system for pressure relay systems; Radio Corp.of America, $400,000, conceptual study of Saturn operationflight control scheme; Trans-Sonics, Inc., $26,589, leakdetector system.5-8


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Cambridge -- American Science & Engineering, Inc., $57,809,study of venting and disposal of hydrogen from Saturn C-1 vehicle;Arthur D. Little, Inc., $220,070, study of blast effect of Saturnrocket; Bolc, Beranek & Newman, Inc., $99,742, investigation ofacoustic environment of large booster systems; Dunn EngineeringCorp., $113,725, fabrication and assembly tooling.Lexington -- Trans-Sonics, Inc., $181,500, design, develop-,ment and fabrication of digital liquid level system, and furnish-

ing heat measuring instruments.Lowell -- Standard Steel Corp., $261,059, large scale liquidhydrogen spill test package, hydrogen fuel semi-trailer, and fab-rication of liquid hydrogen storage tanks.Newton -- G. P. S. Instrument Co., Inc., $168,618, analogcompressed time system computer.Pittsfield -- General Electric Co., $58,446, investigationof gyro gas lubricated gimbal bearing.Stoneham -- Dynamics Research Corp., $33,000, fabricationof data coding equipment.

MINNESOTA:Minneapolis -- Electric Machinery Manufacturing Co.,$31,313, motor generator set; Minneapolis Honeywell RegulatorCo., $19,919, study of the control and dynamic stability pro-blems of Saturn space vehicle; Rosemount Engineering Co.,$27,200, resistance thermometers.

MISSOURI:Joplin -- The Eagle Picher Co., $27,400, batteries.Kansas Cites -- Midwest Research Institute, $80,015,research on loading of space vehicles due to atmosphericturbulence and wind shear.

MICHIGAN:Detroit -- Chrysler Corp., $2t9,872,376, qualificationand reliability testing of Saturn booster and ground supportequipment and components, fabrication of vehicle structuralassemblies, investigation of corrosion prevention in various

components and materials used in Saturn vehicle, studies ofsteering in space flight operations, investigation of the5-9


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age deterioration of lubricants subsequent to storage on launchvehicle valves, research and investigation of redundant struc-tures, engineering man-hours at the Marshall Center and preparatorywork on the manufacture of the booster stage.Pontiac -- Progressive Welder & Machine Co., $2,0477,175,engineering, design and manufacture of fabrication and assemblytooling.Warren -- Cadillac Gage Co., $491,194, hydraulic equipmentand components.

NORTH CAROLINA:Ashville -- National Weather Records Center, $70,000,provide meteorological data on IBM punch cards for selectedstations.

NEW JERSEY:Boonton -- Marotta Valve Corp, $37,300, valve units andcomponents.Denville -- Thiokol Chemical Corp., $32,000, vibrationcutoff devices.Eatontovm -- Red Bank Division, Bendix Corp., $455,521,electrical components.Little Falls -- General. Precision, Inc., $125,131, design,development and fabrication of components for guidance system.Long Branch -- Electronic Associates, Inc., $174,460,analog computing system.Metuchen -- Gulton Industries, Inc., $83,769, accelerometersfor flight vehicle.Teterboro -- Bendix Corp., $3,0060,757, design and manufactureof major components for Saturn guidance package.Trenton -- Gulton Industries, Inc., $196,558, electronicproducts and recording tape for flight boosters.Union -- Potter Aeronautical Corp., $33,500, turbineflowmeter; Tenney Engineering, Inc., $200, 700, environmentalspace simulation test chamber.

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NEW YORK:East Aurora -- Moog Servocontrols, Inc., $460,180,hydraulic valves and actuators.Buffalo -- Cornell Aeronautical Laboratory, Inc.,$294,120, study of configuration effects on rocket vehiclebase heating.Farmingdale, Long Island -- Republic Aviation Corp.,$3,740,997, fabrication of components for flight vehicles.Flushing -- Filtron Co., Inc., $10i,448, research anddevelopment of advanced radio frequency interference controlsystems and techniques.Garden City -- American Bosch ARMA Corp. $37,000,accelerometers; Poviertron Ultrasonics Corp., i35,0000,development, fabrication and installation of ultrasoniccleaning equipment for vehicle components.New York -- Linde Co., $78,712, hydrogen recharger.Rome -- Rome Cable Corp., $25,169, control cable.Sidney -- Bendix Corp., $161,636, electrical connectors.Utica -- General Electric Co., $32,743, developmemt ofpower amxplifier for spaceborne p6orer supply system; BendixCorp., $65, 477, electronic components.Westbury -- Consolidated Avionics Corp., $26,430,plotting sub-systems.

OHIO:Brecksville -- Smith Electronics, Inc., $96,666, studyof radio phase stability.Cincinnati -- Aveo Corp., $192,234, electronic components,and engineering and fabrication services.Dayton -- U. S. Air Force Air Material Command, $55,000,acquisition of gear tester.Cleveland -- Lewis Research Center, NASA, $110,000, purchaseof propellants for static firing liquid oxygen-liquid hydrogenengine; White Sewing Machine Co,, $46,611, fabrication of highpressure spheres.

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PENNSYLVANIA:IDarrs1bur' -- Amp., Inc., $52,018, electrical supplies;Haraco Corp., $,12,176, hydrogf-n gad tr,.nsport trailers.Phila.delphia -- Franklin Inz"titutc, $79,940, study ofSaturn hydraulic System reliability.Pittsburgh -- Anerican Optical Co., $146,650, design anddevclopmi.'nt of optical aligrnuwrt equipment; Combustion & Mcplo-sives Re,;,


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Freeport -- Reynolds Electrical & Engineering Co., $95,563,modification, maintenance and checkout of electrical equipment.VIRGINIA:

Hampton -- Langley Research Center, NASA $116,000, modifi-cation of wind tunnel facilities to permit testing of Saturnconfiguration models and components.WISCONSIN:

Milwaukee -- A. 0. Smith Corp., $300,551, high pressure,spherical gas containers for Saturn vehicle system.

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