sa-5 press kit

8/8/2019 SA-5 Press Kit

1/53

P65 - 10 I2lNEWS RELEASENATIONAL AERONAUTICS AND SPACE ADMINISTRATION400 MARYLAND AVENUE, SW , WASHINGTON, D. C. 20546TELEPHONES: WORTH 2-4155 -------- WORTH3-6925FOR RELEASE: THURSDAY PM'sJanuary 23, 1964

RELEASE NO: 63-268

NASA TO LAUNCH FIFTH SATURN

Five years ago the United States decided to experimentin ground tests with a very large rocket having a thruct ofone and cne-half million pounds. The program later expandedto flight "hardware" and the decision was made in late 1959to develop high-energy liquid hydrogen propulsion for upperstages.

That was the beginning of the Saturn program. In thenext few days, no earlier than Jan. 27., 1964, the NationalAeronautics and Space Administration will attempt to launch

-more-


2/53

-2-

the first complete Saturn vehicle. This will be the fifthSaturn to be fired (SA-5), the first of the Blockc II versionof the vehicle in which the second stage is live and an earth

orbital capability exists.SA-5 is the most powerful and most heavily instrumented

rocket ever launched by the U.S.

The main purposes of the flight are to further test thefirst stage (S-I), to demonstrate separation of the S-I stageand the second stage (S-IV), and to test the function of theS-IV propulsion system Which uses liquid hydrogen to providea performance more t'nan a third greater than conventionalfuels such as the one used in the S-I stage.

If all systems perform as expected, an inert payload of38,000 pounds will be placed in earth orbit. The satelliteassembly is 84 feet long including the empty S-IV rocket stage.It carries no scientific payload. The purpose of the flightis to prove the operation of a complex launch vehicle beingso tried for the first time. If all goes well the upperelement of the vehicle will cfit the earth as a natural resultof the flight course, but the fact that it will orbit is incon-

sequential to the development program.

-more-


3/53

-3-The Saturn project is under the direction of the Asso-

ciate Administrator for Manned Space Flight, Dr. George E.Mueller. The development operation is directed by the NASA-Marshall Space Flight Center, Huntsville, Ala., and launchingsare conducted by an integrated team of the NASA Launch Opera-tions Center, Cape Kennedy, Fla. and the Marshall Center.Dr. Wernher von Braun and Dr. Kurt Debus head I'iarshall andLOC, respectively. Chrysler Corporation and Douglas AircraftCompany, S-I and S-IV prime contractor, respectively, willassist in the launch of SA-5 and subsequent vehicles.

The Saturn I testing program has met with unequalledsuccess. Four large rockets, each generating 1.3 millionpounds thrust and weighing about a million pounds, have beenlaunched without notable delay and have performed perfectly.But; the upcoming test is far more difficult than any performedto date.

The first four missions were principally to test thepropulsion and control systems of the first stage, and theoverall structural integrity and aerodynamic design of thecomplete rocket. (See "Block I Testing. )

SA-5 will be fired following a 10-hour countdown fromLaunch Complex 37B at John F. Kennedy Space Center. Thishuge facility, under construction two years at a cost of $65million, is being employed for the first time. Thus this will

-more-


4/53

-4-be a test of both the vehicle and the ground facility.

(See "Launch Complex 37.")

SA-5 is the fifth in a series of ten Saturn I rocketsplanned. The ten are split into two groups, known as BlockI and Block II. The four Block I rockets, now concluded,hadonly the boostersstage "live." Beginning with SA-5, the firstof Block II vehicles, all Saturns will have powered secondstages with the capability of placing 20,000 or more poundsinto earth orbit. Later vehicles in the series will launchearly; unmanned models of the Apollo command and servicemodules. Manned Apcllos, however, will be launched only onSaturn I's successors, the Saturn IB and the Saturn V. Othersecondary missions have been assigned to two Saturn I's.SA-8 and SA-9 will carry large meteoroid detection satelliteswith 100-foot wingspan into low earth orbit to investigatethe frequency and size of the small space-particles.

The SA-5 vehicle is 164 feet tall. It will weightabout1,124,000 pounds at liftoff, somewhat heavier than previousvehicles which carried water-ballasted inert upper stages.The vehicle consists of four elements: S-I stage, S-IVstage, instrument unit and payload assembly (Including adaptor).

-more-


5/53

Both the S-IV and the instrument unit are being flownfor the first time. Additionally, the S-I has been modifiedand is undergoing its first flight test in this configuration.S-I changes include:

-- The eight H-1 engines are flying at their rated thrust,188,000 pounds, for the first time, giving the stage itsdesigned thrust of 1.5 million pounds.

-- The nine propellant tanks have been extended by sixfeet, adding about 100,000 pounds to the usable propellantcapacity (850,000 pounds presently) and 30 seconds to burningtime.

-- Tail fins have been added for increased stability.(For more details on the launch vehicle, see separate

piece, "SA-5 PFckground and Description,".)

Flight SequenceThe booster ignition and liftoff sequence is the same as

on previous flights. The vehicle will be held to the launchpedestal until assurance is received that all engines are oper-ating smoothly. Normally liftoff occurs about three secondsfollowing ignitioe.

SA-5 will be fired on an azimuth of 90 degrees, but duringthe first few seconds will "roll into" its flight azimuth of105 degrees. The tilt program will begin following 15 secondsof flight. The rocket will continue to tilt until the 135thsecond of flight, when it will be inclined at 6: degrees fromthe launch vertical. -more-


6/53

Seventy seconds following liftoff the rocket will passthrough the region of maximum dynamic pressure, when tireforces exerted on the rockcet's structure are at their greatest.This critical time in flight will occur about three st.atutemiles in range and eight statute miles in altitude.

Soon after 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 primary stepsare as follows:

1. At T+107 seconds, S-IV engine hydrogen prestart flowbegins, lasting 42 seconds.

2. The S-I propellant level switches which will sense alow level of propellant and initiate the LOX prestart sequencein the S-IV are armed at T+133.

3. S-IV LOX prestart flow starts at T+139.4. According to propellant utilization estimates, the

S-I inboard engines will be cutoff at T+141. The outboardengines will be cut off by an automatic timer (program device)six seconds later, at T+147. At S-I cutoff the vehicle will betraveling at 6,000 statute miles per hour; the altitude willbe about 48 miles and the range about 65 miles.

-more-V


7/53

-7-5. Within less than two seconds, these actions occur

(in the order listed): The S-IV's four solid propellantullage motors be in' heir 3 to 4 second firing period;separation command is given and the explosive bolts attachingthe two stages are activated; the S-I's four solid propellantretrorockets begin their two-second firing period; the S-IVstage engines are then ignited, at about T+149.

Some 20 seconds following S-IV ignition, the stage'sullage rockets are jettisoned and the tilt program is resumedand lasts until cutoff when the rocket's angle will be 107degrees from the launch vertical. The S-IV burns to T+630seconds, or almost eight minutes. At that time, 10-1 minutesfollowing liftoff, the S-IV stage and attached payload of thevehicle ko into orbit.

At insertion into orbit, the body will be traveling atabout 16,650 statute miles per hour. Injection will occurabout 1,300 statute miles downrange from the launch site,375 miles north of Antigua tracking station of the AtlanticMissile Range.

The PayloadThe length of the orbiting portion is 84 feet, or slightly

more than half the length of the entire vehicle. It is madeit, of the following items, approximate w*ights of which aregiven: -more-


8/53

Spent S-IV stage -- 14,300Instrument Unit -- 5,200Payload Adapter -- 4,000Jupiter nose-cone -- 2,500Ballast (Sand) -- 11,600Miscellaneous -a 100Total -- 37,700

There are several reasons why it is not possible toforecast with accuracy the characteristics of the orbit.. orits duration. SA-5 has no active guidance system, only acontrol system. Thus the vehicle is not being guided :.ntoan exact orbit of -re-determined values. The rocket's dragcharacteristics are not known. Because of these unknowns,it is only possible to estimate that the payload may orbitwith a perigee of about 160 statute miles and an apogee ofabout 400 statute miles. It should be in orbit at leastseveral days.

The Satellite will have an orbital period of about 93minutes. It will probably be tumbling slowly, requiringabout eight minutes to complete one revolution end-over-end.Under certain atmospheric conditions it may be visible to thenaked eye from earth. Its visibility will vary with altitude,but in general terms iit will appear about the size of Venus,the Evening Star.

-more-


9/53

-9-If the vehicle is launched about mid-morning, as is

presently planned, the satellite will not be visible to theNorth American continent on the first evening. It shouldbe visible the next morning, however, to at least the southerntier of states. Two passes would occur with possible sightingopportunities -- at about 5 a.m. and 6:35 a.m., CST.. (Otherinformation on this subject will be released as soon as itis available).

In the nose cone is a minitrack transmitter which willbe operating on a frequency of 136.995 m.c. Four temperaturemeasurements will be broadcast to ground stations, from thefollowing locations on the satellite: minitrack beacon;stabilized platform (ST-124) mounting ring in instrument unit;and two places on the minitrack beacon battery pack. Thesystem includes twelve 50-pound batteries, which should assureoperation for about six weeks.

In addition, the vehicle's entire telemetry system isexpected to operate through one orbit, providing signals whichwill be tracked by other gound stations.

Aside from vehicle missions, the SA-5 flight will affordan opportunity for a significant test of all the majorgroundtracking networks of the United States, NASA, the Departmentof Defense and the Smithsonian Astrophysical Observatory will

-more-


10/53

-10-

take part in a unique global ground tracking exerfise, oneof the most extensive yet conducted. (See separate piece,"SA-5 Global Tracking.") The Goddard Space Flight Center willbe responsible for coordinating this operation; early "quicklook" tracking and data reduction to determine orbital charac-teristics will be conducted at the Marshall Center withassistance from several stations.

Measuring ProgramSA-5 will telemeter to the ground during flight, 1,183

measurements, as follows: S-I, 616; S-IV, 362; instrumentunit, lo9; and payload, 16. This is by far the largestnumber of such measurements taken from a U.S. space vehicle.Earlier Saturns, with only one stage live and carrying noinstruemnt units, had about 600 flight measurements.

In addition to these flight measurements, there are 201so-called "blockhouse measurements" which are received in theblockhouse only during countdown and are terminated at liftoff.Generally the blockhouse measurements are a duplication on aselective basis of the in-flight measurements, for the useof the launch crew during countdown.

The vehicle has 13 flight telemetry systems: six onthe S-I, three on the S-IV and four on the instrument unit.

-more-


11/53

The telemetry systems transmit such measurements asengine turbine temperature and propellant pump rpm; positionsof valves, temperature of engine bearings, heat exchangeroutlets, tail skirts, turbine exhaust and nitrogen pressuri-zation tanks; pressures in combustion chambers, propellanttanks and payload; strain and vibration throughout the vehicle;stabilized platform position; velocity; motion of controlactuators; propellant level; battery voltages and currents;inverter frequency, etc.

Other significant portions of the vehicle instrumentationare the optical systems which are being carried for the firsttime. Eight motion picture cameras and one television camerawill record vital functions of rocket operation. Such instru-mentation has not previously been attempted on this scale.(See separate piece, "Optical Systems.")

Aside from vehicle measurements, as in the past Saturnlaunchings NASA will measure acoustic, vibra tion and blasteffects of the launching. A total of about 50 measurementswill be made at Launch Complex 37, elsewhere on Cape Kennedy,on Merritt Island and on the Florida mainland up to a distanceof about 15 miles from the launch site. This program is beingconducted by the NASA-launch Operations Center.

-more-


12/53

-12-

SA-5 BACKGROUND AND DESCRIPTIONThe Saturn I rocket (Block II) consists of two stages,

an instrument unit and a payload. SA-5 is the first ofthese vehicles. This configuration is capable of placinginto earth orbit about 20,000 pounds of useful payload--in the case of SA-5, the total weight is nearly 38,000,but this includes the spent S-IV stage, the Instrumentunit and the payload adapter, whicN .4n normal mission,would not orbit with the payload.

In August, 1958, the Advanced Research Projects Agencyof the Department of Defense initiated the Saturn programwith the von Braun development group at Huntsville, Ala.That group was then a part of the Army Ordance MissileCommand; by mid-1960 both the group and the Saturnproject had been transferred to the NASA.

The program grew out of studies made by the von Braungroup in 1957. Initially the objective was to demonstratewith ground tests the feasibility of building a largerocket using a cluster of available engines. Withinlittle more than a year, a flight program, includingthe development of high-energy upper stages, was started.

-more-


13/53

-13-The Saturn I, as it is now known, has had a remarokably

successful test program to date and has led to the develop-ment of two larger space vehicles, the Saturn IB and theSaturn V. Now that the lunar landing program is firmedup, it has become obvious that because of timing, schedulingand funding considerations, the Saturn I, with its limitedcapabilities insofar as the moon program is concerned,will not be used for manned Apollo flights. NASA announcedin October that it had cancelled the four manned earthorbital flights previously assigned to the Saturn I.

The Saturn IB vehicle used virtually the same firststage as the Saturn I. For its second stage, it uses theS-IVB, which develops 200,000 pounds thrust instead of the90,000 for the S-IV. Originally the only ;use for theS-IVB was as the third stage of the Saturn V moon rocket.Employing it in the Saturn IB allows NASA to increase theSaturn I payload capability by 50 per cent without theexpense of starting a new development program.

With the reshaping of the Apollo manned fights, theSaturn I program will end with the 10th flight, accordingto present plans. There will, then, be five firings afterthis one. The missions of those vehicles will be tocontribute to the development of Saturn IB and Saturn V,bp launch early, unmanned versions of the Apollo command

-more-


14/53

-14-and service modules (beginning with SA-6) and to placein earth orbit large satellites (Having wingspread of 100feet) to detect the presence and size of meteoroids innear space (SA-8 and SA-9).

The Saturn I, with dummy Jupiter nosecone such asis carried on SA-5, stands 164 feet tall. With Apollospacecraft, including launch escape system, it will be190 feet tall. The vehicle weighs more than 1,1 mi.lionpounds--SA-5 liftoff weight is 1,121,680 pounds.

DescriptionFollowing are the descriptions of the Saturn I stages

and instrument unit:S-I: The first stage (S-I)ia powered by a cluster

of eight Rocketdyne H-1 engines, eachof which produces188,000 pounds to give the stage a nominal thrust of1,504,000 pounds. In all four previous launchingsthe engines have been operated at an interim level of165,000 pounds thrust, giving the stage only 1.3 millionpounds thrust. SA-5 is therefore the first testof the propulsion system at its designed rating. Fewinternal changes in the engines were necessary in orderto increase the performance. It was primarily a matterof increasing the rate of flow of propellants into thecombustion chamber.

-more-


15/53

-15-The H-1 engine is an outgrowth of an engine which has

propelled several hundred missiles and space vehicles.The same basic engine is used on Jupiter, Thor and Atlas(in pairs in the latter). The H-1 burns RP-1 (kerosene)and liquid oxygen. For its Saturn use, major changesincorporated in the H-I include a simplified start sequenceusing a solid propellant gas generator, and location ofthe turbopump on the thrust chamber below the gimbalblock so that the flexible propellant lines to theengine need carry only low level pressure propellant.

The eight H-1 engines are atta4hed to an eight-leggedthrust frame on the aft end of the vehicle, arranged intwo square patterns. The four inboard engines arerigidly attahced and canted at a three-degree angle tothe center line of the booster. The outboard enginesare canted at an angle of six degrees and mounted ongimbals which permit them to be turned through anglesof up to eight degrees to provide control of the vehicleduring first stage powered flight.

Nine tanks feed the eight H-1 engine. Clusteredin a circle about allarge center tank of 105 inches indiameter (Jupiter size) are eight smaller tanks, each70 inches in diameter (Redstone size). The center tankand four outer ones contain liqud oxygen, while the

-more-


16/53

-16-remaining (alternating) four outer tanks carry the kerosenefuel. The fuel tanks are pressurized by gaseous nitrogencarried atop the tanks and the liquid oxygen throughheat exchanges that are part of each engine package.

The fuel tanks as well as those containing liquidoxygen are interconnected at the base to allow the mainten-ance of equal levels in all tanks during burning. Incase one engine malfunctions and is cut off duringflight, this arrangement permits the remaining sevenengines to consume the fuel and oxygen intended for thedead engine. Thus, the burning time of the seven remain-ing engines is increased and there is little loss in overallbooster performance.

The nine propellant tanks are attached at the topby a structural member called a "spider beam." Thisstructure supports the S-IV stage.

The booster is 80 feet long and 21-1/2 feet in diameter.Empty, it weighs about 107,000 pounds.

Eight of the ten S-I flight stages are being assembledand tested by the Marshall Center, The other two S-LBtsfor the Saturn IB, are being produced by the ChryslerCorporation at MSFC's Michoud Operations, New Orleans.

The S-I has had several modificatimea, beginningwith this vehicle, the first of the Block II design.Following isa summary of the more important changes:

-more-


17/53

-17-1. Full Thrust--As previously mentioned, the H-i

engines are flying at their rated full thrust for the firsttime, giving the booster 1.5 million pounds,

2. Longer Tanks--The maximum burning time of thestage has been extended by about 30 seconds as the resultof elongating the nine propellant tanks. They now hold850,000 pounds of usable propellant instead of 750,000,having been extended by about six feet. The overalllength of the booster was changed from 81.6 feet to 80,2feet--the area above the S-1 tanks where instrumentationwas formerly carried has been eliminated. The S-IVstage now pits directly upon the spider beam, and theinstruments once carried in this area have either beenmoved to the instrument unit or relocated to the twosmall instrument compartments above two fuel tanks.'

3. Fins--Fins have been added to the tail section toincrease stability. Four large fins--each having approx-imately 120 square feet of area and extending out aboutnine feet--are attached to the S-I stage thrust structureat 90 degree intervals around The circumference of thetail section. Four stub fins--each having some 50 squarefeet of area--are attached to the thrust structure at90 degree intervals midway between the larger fins.

-more-


18/53

-18-The fins provide aerodynamic stability to the vehicle

and eight attachment points to arms which hold the vehicleto the launch pad until it is assured that all enginesare operating properly. Three of the stub fins alsoprovide enclosures and attachments for exhaust ductassemblies which allow chilldown hydrogen from the S-IVstage to be dumped overboard.

4. LOX-SOX Disposal System--The liquid oxygen-solid oxygen disposal system prevents unintentionaldetonation of cool-down LOX, SOX, or both, which fallsfrom the thrust chambers of the S-IV stage engines duringthe chilldown period prior to S-I/S-IV stage separation.Gaseous nitrogen (GN2) is channeled from storage tanksthrough six dispersal manifold rings into the RL-10thrust chamber areas. This GN2 .keeps the liquid oxygenfrom freezing during chilldown and allows the gaseousoxygen to escape into the atmosphere.

5, Hydrogen Vent System--The purpose of the hydrogenvent systemis to remove the chilldown hydrogen which beginsto flow through the S-IV stage plumbing approximately40 seconds prior to S-I/S-IV stage separation. Thehydrogen exits the S-IV stage through three 12-inch-diameter ducts which lead down the sides of the S-I/S-IVinterstate at 90 de-rees around the S-I stage in line


19/53

-19-with stub fine II, III, and IV. The ducts exit throughthese three stub fins, thus leading the hydrogen completelyaway frDm any explosive environment and duraping it intothe edge of the jetstream.

6. S-I Fuel Pressurization--This system, originallyhaving as storage vessels 48 small fiberglass spheres,now has two steel tanks. The 20 cubic foot tanks providegaseous nitrogen for maintaining tank pressure duringthe flight.

7, Feed Lines Modified--Propellant feed lines havebeen modified in the boattail area. In earlier versionsof the S-I stage, LOX was piped from the center tank throughthe outside tanks and in turn to the engines. A sumpassembly has been welded to the bottom oL each tank withflanges nor interconnect lines welded to the sump. AY-arrangement now carries propellants from both the centertank and the other tanks to the engines. This arrange-ment gives better utilization of the propellant and betterperformance.

8. Structural Changes--Ihe outriggers of the thruststructure have been modified. The Block I boosters hadbeam outriggers while SA-5 has beam and panel outriggerassemblies. These improved structures accommodate the finsupports.

-mores,


20/53

-20-A second stage adapter assembly has been changed.

The adapter is siow covered Wy a seal plate. The sealplate keeps hydrogen and oxygen used in S-IV chilldownfrom accumulating in areas between the S-I tanks. Thisplate eliminates explosive lizards in the S-I stagewhich could be caused by the escaping propellants.

the Second SazeS-IV--The second stage of the Saturn I is the S-IV,

which is powered by six Pratt and Whitney RL-10A3 engines,each developing 15,000 pounds thrust for a stage thrustof 90,000 pounds. The stage burns liquid hydrogen andliquid oxygen, a high-energy combination which gJves aperformance more than a third greater than conventionalfuels. The use of the super-cold hydrogen (it boils at--423 degrees F) presented several unique problems, thesolutions to which represent a considerable advancementin the art of rocketry.

The S-IV, being flown for the first time, is 18-1/2feet in diameter and 41 1/2 feet long. Its dry weightis about 130500 pounds and it is designed to carry100,000 pounds of propellant--enough for a normal operationtime of about eight minutes,

-more-


21/53

-21-Douglas Aircraft Company's Mifiiles and Space Division

was awarded to S-IV development contract in July, 1960.Major design and manufacturing is done at Santa Monica,while static testing is done at Sacramento.

The RL-10 engine is the country's pioneering hydrogenpower plant. Its design was begun by Pratt and WhitneyDivision of United Aircraft in 19588 Although it underwentits first in-space operation late in November, 1963, ithas been ground tested to an musual degree and has beenshown to be . very reliable engine in these tests. Theengines functioned perfectly in their one (Centaur) flight.

STRUCTURE--The stage is a self-supporting structurethat is designed to permit ground handling withoutpressurization. Liquid o;ygen-liquid hydrogen (LOX-LH2)propellantE. are stored in two tanks containing a combinedusable propellant capacity of 100,000 pounds.

The oxidizer tank aft dome forms an integral part ofthe engine thrust structure. The engine thrust structureprovides a mounting surface fo r electrical and mechanicalcomponents. To protect these components from the heat ofthe engine combustion gases, a base heat shield is installedbetween them and the engine exit planes. An aft interstageassembly provides a means of attachment to the S-I stage.

-more-


22/53

-22-An inflight, S-I/S-IV, separation plane is lo-cated betweenthe aft skirt asserbly and the aft interstage assembly.

In general the S-IV stage is composed of the following:airframe, electrical power system, flight control system,propulsion system, hydraulic system, instrumentationsystem and flight termination system.'

DESIGN HIGHLIGHTS--Unusual techniques used in S-IVinclude a common bulkhead separating the hydrogen-oxygentanks, internal insulation in the liquid hydrogen taak,a helium heater, storing helium gas in titanium bottlesimmersed in the liquid jydrogen fuel and use of a uniquesystem to control propellant depletion.

One of the advanced techniques employed in the S-IVis the design of 'he common bulkhead separating the largeliquid hydrogen tank from the smaller liquid oxygen tank.Two aluminum domes, with fiberglass honeycomb bonded toeach dome to form a rigid "sandwich," provide highstructural strength and an insulation barrier betwieen thepropellants. The common bulkhead insulation minimizes heatlosses from the UIX--at 297 degrees F--to the LH2--at -423degrees F.

-more-


23/53

- 23 -

The extremely low boiling point of the liquid hydrogenrequires that the fuel tank be insulated to minimize lossthrough boil-off. A decision was made early in the S-IVprogram to use interaallinsulation - a new concept in tankdesign. Materials, particularly adhesives, were developedthat could withstand the temperature. The interior of thetank is machine-milled in a waffle-like pattern, similar tothat of the Thor rocket, for weight relief.

Helium gas which pressurizes the liquid oxygen tankduring flight is stored at liquid hydrogen temperature totake advantage of the resultant large wtight savings. Thetitanium bottles, in addition, have improved material pro-perties at this super low temperature.

The helium is passed through the helium heater to raiseits temperature and expand it prior to introducing it intbthe liquid oxygen tank.

A capacitance probe system was developed to help insurethat the liquid hydrogen and liquid oxygen would be burnedat the same relative rates. This new system, which also willbe used on the S-IVB stage, continuously senses the amount ofeach propellant remaining i-. he tanks andaccordingly regulatesthe engine mixttee ratio.

-more-


24/53

- 24-RL-10 ENGINE OPEhATION:The liquid hydrogen enters the cooling Jacket surrounding

the thrust chamber at -423 degrees F. The hydrogen burningwith oxygen inside the chamber is at 6000 degrees F. Thehydrogen in the Jacket cools the engine while it itselfbecomes sufficiently heated to convert to a gas, the tempera-ture of which is still more than 100 degrees below zero.This hydrogen is then expanded in a turbine which furnishedpower to pump more liquid hydrogen into the combustionchamber. The turbine also furnished power to pump the liquidOxygen. Thus the cold hydrogen plays two roles before it isburned. It cools the thrust chamber and drives the pumps ina so-called "boot strap" system. It is burned only in thethrust chamber where it produces useful thrust.

The engine was designed to provide a capability of restartsin space, with long coast periods between firings. Theproblems associated with maintaining a conventional lubri-cation system under conditions of coasting made it desirableto eliminate oil lubrication in the gear box. The gears andbearings in the turbopumps of the RL-10 were developed tooperate dry with hydrogen cooling.

The RL-10 has a nozzle expansion ratio of 40 to one--meaning the area at the exhaust end of the thrust chamber is40 times as larger as the engine's throat. It operates at anominal chamber pressure of 300 pounds per square inch.

-more -


25/53

- 25 -

S-IV's six engines are canted six degrees outwardfrom the vehicle's center line and can be gimbaled throughabout eight degrees. The S-IV vehicle is controlled bygimballing the six engines in response to signals from thevehicle instrument unit.

S-IV TESTING--The RL-10 engine was designed for ignitionand operation above 200,000 feet altitude. Therefore, addedcomplexity in the form of an altitude simulation system, wasrequired for static testing.

Special test facilities have been constructed-atSacramento to test the stage. A blockhouse, two largestatic firing test stands and associated support facilitieswere required for the static firing.

The new altitude simulation system consists of a steamboiler plant, two steam accumulator tanks at each teststand, six two stage steam operated air ejectors, and thesix engine exhaust diffuser assemblies.

- more -


26/53

-26-.Instrument UJnitThe SA-5 Tehicle maintains stability and flies a pre-

determined flight path by changing the direction of the thrustvectors of the S-I's iour outboard engines or the six enginesof the S-IV, Commands for engine eimbaling as well as infligthoperations of the engine propulsion systems and staging opera-tions originate in the Instrument Unit (IU). In addition tocontrol signals, all primary timing signals originate in the IU.

The IU is located between the S-IV stage and the payload.It has five temperature and pressure-controlled tubes forenvironmental control of the electrical/electronic equipment.

The unit's overall height is approximately 91 inchesand the outside fairing height is 58 inches. The 154-inchdiameter unit weighs some 5,200 pounds.

The SA-5 IU houses the vehicle control system, a develo-pmental guidance and control system, six tracking sub-systemsand four telemetry subsystems. Service systems include apower sypply and distribution system, a cooling system anda gaseous nitrogen air bearing supply system.

Four 40-ineh diameter tubes arranged at 90 degrees arounda vertical 70-inch diameter center hub make up the air con-ditioned portions of the IU. Most of the stage's instrumen-tation is housed within the five temperature and pressurecontrolled tubes. The antennas, horizon sensor system, and a

-more-


27/53

27-connector panel for use in ground checkout and servicingare located on the outside skin, as is the liquid nitrogencooling system.

SA-5's guidance and control system is incomplete -- an"open loop" system. This vehicle will be controlled, butnot guided. The vehicle control system -- basically an ST-90Sgyro-stabilizec platform, an analog control computer andhydraulic actuators -- gimbal the stage engines for the pro-grammed pitch and roll angel. If the vehicle is moved bywind or other conditions from the planned trajectory, theguidance system does not correct the error.

A passenger in the SA-5 IU will be a developmentalguidance and control system for use in future Saturn Ivehicles. An advantage of this developmental system willbe that it will be adaptive -- it will not try to adhereto a predetermined trajectory, but will adapt itself to anyforeseeable and program-provided situation.

The future system is basically an ST-124 stabilizedplatform, platform electronic box, guidance signal processor,ASC-15 digital guidance computer and the presently-operationalflight control computer.

The instrument unit also has two control accelerometerswhich are used to measure the lateral acceleration in thepitch and yaw plan-C.s. The purpose is to bias the vehicle into

-more-


28/53

- 28--the wind direction and thus reduce engine swivel angle,thereby reducing structural loading. These devices wereflown first on SA-4, replacing the local angle-of-attackmeters used previously.

Several other systems flown on SA-4 are being testedagain, including a radar altimeter and a Q-ball transducer.

Six separate on-board tracking systems will includesubsystems, that, together with subsystems being flown onother SA-5 stages and their respective ground subsystems,comprise the radio frequency system used in determiningtrajectory, range safety, and vehicle performance. Threeof the tracking systems are operational and used for flightevaluation; and other three systems are in the developmentalstage.

The four telemetry sub-systems housed in the IU includeone which incorporates a tape recorder. The recorder willmonitor transmitted data at the time of injection into orbit.The recorded data will be available for delayed transmissionif telemetry signals are lost during this period.

Some 185 measurements will be transmitted through thefour telemetry links to ground stations during the flight.

-more-


29/53

-29-

SA- Tiesting, TransportationSA-5's S-I stage was static fired three times during

February and March at the Marshall Space Flight Center,Huntsville. The firings were two short duration shots - 30to 45 seconds - and a full duration firing of more thantwo minutes.

The MSFC barge "Promise" arrived at the Cape in lateAugust with the booster, the instrument unit and the pay-load.

S-IV was successfully static fired twice at the DouglasSacramento, Calif., test installation in August, once forfull flight duration of nearly eight minutes. Previouslya battleship version of the vehicle had been ground-fired26 times totaling 72 minutes of successful static testingof S-IV systems.

The SA-5 second stage arrived in Florida aboard aspecially-modified aircraft, a Boeing 377, in late September.

-more-


30/53

OPTICAL SYSTEMSSA-5 will carry optical systems consisting of eight motion

picture cameras and one television camera. These cameras willview the interior of two LOX tanks, first stage separation,retro-rocket firing and S-IV stage ullage motor and propulsionsystem operation. All cameras are mounted on the perimeterof the spider beam assembly (the main structural member atthe top of the S-I stage) and are slanted outward for ejection.All will carry color film except the ones monitoring theinterior of the two LOX tanks.

This is the first time such an elaborate opticalinstrumentation has been carried on a launch vehicle. Thecameras will provide a visual record of events in severalcritical areas of the rocket, especially the activitiesinvolved in the separation of the S-I and S-IV stages and inthe ignition of the six RL-10 engines in the second stage.

Similar camera systems will be carried on SA-6 and SA-7.This technique is being developed to assure that all possibleinformation is gleaned from each launch, in view of thegreatly reduced number of R&D firings possible in rocketsof this size.

The advantages of photography are that high pictureresolution is obtainable, in full color if desired, andaction -nay be photographed at a high frame rate and viewedlater in "slow motion". A chief advantage of in-flight


31/53

-31-

television cuverage is that the image is viewed initially inreal-time, and can be used as a basis for human decisions.Motion Picture System

Twvio film cameras will view the interior of two LOX tanks,the center and one outer, by means of optical-fiber bundles.Four cameras will view forward along the outside of thevehicle to monitor retro-rocket and ullage rocket firing,coasting and firing of the S-IV stage. The third interiorcamera views separation of the stages and the piping ofengine number four, and the fourth camera uses a: optical-fiber bundle to monitor the effect of the solid oxygen-gaseous oxygen disposal system.

The external view cameras and the camera monitoringthe engine piping will operate at 64 frames per second, thecameras filming the outer LOX tank and the lox-gox systemwill operate at 24 frames per second, and the remainingcamera will run at 12 frames per second. The two camerasviewing LOX tank interiors will start at ignition. Theother six will start about 40 seconds before the boosterseparates from the S.-IV and will continue to run forabout 20 seconds after separation.

The optical-fiber bundles are made up of about 675,000optical quality cladded glass fibers one micron in diameterfused together in blocks of 36 fibers each. Those blocks


32/53

- 32-are encased in hydraulic hose with stainless steel wirebraided over a teflon core,

Each camera is enclosed in a camcra capsule with anoptically clear quartz window at the forwarc ind. Imagesare recorded on 16 mm film in a compact camera made by theD. B. Millikem Co., Arcadia, Calif. The cameras arepowered by 28 volts d c. supplied by the booster'selectrical system.

Interiors of the LOX tanks are lighted. 30-volt,250-watt lamps with pyrex windows in cannisters 12 incheslonug and six inches in diameter. Strobe lights are used withthe camera monitoring the plumbing of the nrumber four engine,The strobe unit w:ll provide 16 hi.gh intensity flashes persecond, synchronized with the camera shutter to illuminateevery fourth frame.

All eight film camneras will be, ejected at about 400,000feet altitude from individual e3,oction tubes, Ejection willocuur about 20 seconds after stage separation and at about125 miles downrange.

Each capsule consists of an alumirum shell, a quartzwindow, the camera, re-entry equipment and recovery aids.Several "0-rings" are used to prevent water leakage aroundthe window alfter re-entry and impact. An inner lining oflighitweig1t J. ulation material keeps the internal temperatureat an -^ceptable level. The capsule shell is waterproofed


33/53

to withstand salt water immersion. The lens is also4immersion-proofed to prevent film damage if the quartz

window is broken on impact or during recovery.Each capsule has eight stabilization and deceleration

flaps which are extended by spring action and locked at a30-degree angle upon ejection from the tube. The capsulevrill re-enter the atmosphere at about Mach 10.. or more than7,000 mph, and impact in the Atlantic Ocean about 500 milesfrom the launn'- -4te.

Ships and airplanes will be stationed in the impactarea to watch for the falling capsules and make speedyrecovery. Para-divers will attach additional flotationdevices to The capsules when they are reached. The primaryrecovery aid is a SARAH beacon. A self-erecting springsteel antenna in the transmitter case atop the balloon isdeployed at 14,000 feet.

At 14,000 feet a para-balloon will be inflated by ahigh-pressure gas container. This will shear the coverretaining screws and jettison the flaps. The balloon willthen serve as the stabilizer and will decelerate the capsule'svelocity to about 90 feet per second before impact. Alternateoanels of the balloon are inte-iational orange for easysi.Cht-in, in sunlight. Th ' -other panels are coated withwhilte Class beads for easy spotting with a searchlight at

1I


34/53

- 34 -

night. Upon contact with water, a yellow-green fluorescentdye will be released, as well as a water soluble plug ofshark repellant.

Packed with the radio transmitter is a high-intensityflashing light which produces a flash every two secoi.ds.Television System

The television systeri is designed to provide real-timevisual information on the functioning of selected items andto provide a permanent visual record for future study andanalysis. The camera will operate at 30 frames per second,beginning before 1.ftoff and running until the S-I impacts.The television camera will not be ejected. Images will berecorded on video tape at the ground monitoring station, anda kinescope record will be kept as a backup to the video taperecordings.

The camera, equipped with a 12.5 mm lens, is mountedforward on the spider beam in position to monitor stagingand ejection of two motion picture camera capsules.

Video signals are preamplified in the camera and passedon to the camera control unit for amplification. Controlunits provide aperture correction and focusing control ofthe camera, generate the sweep signals for the cameravidicon, amplify the video signals from the camera andintroduce the blanking signals to the video output. Avideo signal of 30 frames per second is provided. A solid-


35/53

-35-stage synchronizing generator in the camera control unitkeeps the operation of var.'.ous system components in sequence.

The transmitter will have a carrier signal of 860 mc.Input power required is about 50 watts. Nominal output isfive watts. A separate power supply will provide the necessaryvoltage for transmitter operation. The antenna is installedon a special instrumentation panel near the number four finon the S-I. The ground receiving, monitoring and recordingstation, in an eoll-nment trailer, consists of an antennasystem, a parametric amplifier, tape recorder, kinescoperecorder, viewing unit, study unit and a monitor for theflight camera.

The output from one of a pair of receivers will be fedinto the ground station video processing system while theoutput from the other is monitored at all times for selectionof best picture conditions for recording or display. ohoutput from one receiver is fed into four parallel 1istpibutingamplifiers which increase the video signal strength and serveas buffers between the receivers and other subsystems.

The video recorder has been Venally modified toimprove its resolution to & ji deo bandwidth of 5.5 me at atape speed of 15 inches per: seconds

Output from another1 dtsi;it uting amplifirJ ,x will beapplied to the kinescoe recorder, a 16 inn motion picturecamera facing an eigh;-inch standard c;det. Image monitor.


36/53

- 36 -All information from the receiver is reproduced on the monitorand photographed at 30 frames per second.

Output from the third distributing amplifier is appliedto a processing amplifier where the video information isstripped from the synchronizing signals and applied to thesync lock unit. The sync lock and a ground system synchronousgenerator are tied together in a servo-loop configurationto form a slaved block which serves as a master timer forthe entire ground station.

^ more -


37/53

- `7 -SATURN INDUSTRIAL PARTICIATION

Active research, development and production contractsin thee Saturn program include 72 contracts in excess of,500,000 in value. 'lhe contracts are held by 35 industrialfirms. Seventeen contracts concern Saturn I only, two combinework on Saturns I and IB, four concern IB and V, 28 are forI and V, three cover all three configurations and 18 are forf1aturn V only.

Thebe contracts uere awarded directly to the finms bythe 11RASA-Ilarshall Spa. e Flight Center, technical manager ofSaturn development. In addition, hundreds of companies arenarticipating to a lesser degree. Most holders of prime con-tracts from the government have numerous subcontractors.

Five majcr firms hold a total of 17 contracts for workin the Saturn I, IB and V programs. Each firm has contractstotaling more than 100 million.

The Boeing Co. of Seattle, flash. heads the list with twocontracts listed at $482,671,058. hloeing is charged withmanufacturing S-IC stages for the maimothl Saturn V moon rocketat the Michoud Operations plant. Both contracts are relatedto this work.

-more-


38/53

North American Aviation's Rocketdyne Division, CanogaPark, Calif., and Space and Information Systems Division,Downey, Calif., have seven contracts totaling $L33,119,392for H-1 engir s for Saturn I and IB and for J-2 engines andS-II stages for Saturn V.

Douglas Aircraft Co., Santa Monica, Calif., holds threecontracts with a sum of $313,781,688 for S-Iv itages forSaturn I and S-IVB stages for Saturn IB and V.

Chrysler Curp., Detroic, Mich., has three contracts witha total value of $235,822,653 for modifying and maintainijigfabrication facilities at Michoud and manufacturing firststages for Saturn I and IB.

Pratt and Whitney Division of United Aircraft Corp.,West Palm Beach, Fla., and East Hartford, Conn., has twocontracts in support of the Saturn I program. P & W suppliesRL-10 engines for the S-IV stage. These con'racts total$108,728,651.

M.1,ason-Rust Co., New Orleans, is sixth largest with threecontracts totaling $29,937,122 for facility maintenance andsupport services at the Michoud plant.

Four contracts totaling $24,735,464 are held by BendixCarp., Teterboro, N.J. in support o,' Saturn I, IB and V.Bendix is producing stabilized platform systems for the 3rickets. more-


39/53

Browm Engineering Co., Huntsville, Ala., is next largestwiti-i five contracts totaling $18,452,431. Brown is furnishingresearch and development engineering services and fabricationmanpower in the Saturn I and V programs.

International Business Machines Corp. of Rockville, Md.has four contracts adding up to $14,356,965 for flight com-puters, data adapters and other electronic equipment forSaturns I, IB and V.

Hayes International Corp., BiJmingham, Ala., has fivecontracts totaling ]P",415,997 to pr'ovide R & D engineeringservices and for fabirication and rclaoed services.

Radi. Corporatio;-, of America, V n Nuys, CaliC., has fourcontrate, totaling :1O,01, 49 providing for gro;und computerstatni;, display and console sy,-;emz and data (lannels forSaturn L.

Arrowhead Products Division of Federal ',.ogul Bower Bear-inis, Inc., Long Beach, Calif., is designing and testing sixitems of S-IC ductinC in the Saturn V program under a contractfor $7,635,407.

Booster fuel ana nxygen tanks are being produced by theLing-Temco-Vought Corp. in Dallas, Tex., under a contract 1r0r$7,615,82h.

-more-


40/53

- 40Republic Aviation Corp. of Farmingdale, N.Y., has two

contracts totaling $7,049,461 providing for fabrication ofS-I components, ground support and test equipment.

Packard-Bell Electronics Corp., Los Angeles, is providingautomatic checkout systems under a contract for $6,985,28C.

Spaco, Inc., Huntsville, Ala., has two contracts totaling$3,365,515 for R & D eng:ilneering and fabrication services.

AVCO Corp. of Cincinnati, Ohio, and Nashville, Tenn.,has three contracts to provide digital decoders and otherelectronic equipment and components. The contracts total$2,839,261.

A contract in the amount of $1,931,940 with WhittakerControls of Van Nuys, Calif., provides fuel and LOX pre-valves for the Saturn V S-IC stage.

Flexonics Division of Calumet and Hecla, inc., Bartlett,Ill., is manufacturing propellant feed lines and connectorsunder two contracts totaling $1,913,120.

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

Cornell Aeronautical Laboratory, Inc., Buffalo, N.Y.,$1,799,400, base heating studies on Saturn stages.

AIResearch Division of The Garrett Corp., Photnix, Ariz.,$1,779,4O9, Uavelopment of S-IC fuel and LOX pre-valves.

-more-


41/53

-41-Ry-n Aeronautics of San Diego, Calif., $1,674,463,

fabrication of bulkhead segments for the Saturn V rocketfuel tanks.

Progressive Welder and Machine Co,, Pontiac, Mich.,$1,618,574, tooling and fabrication of major fixtures forSaturn V construction.

Lockheed-Georgia Co,, Marietta, Ga., $1,303,367, R & Dsupport on the first ten structural componentsr in the SaturnV program.

J.T. Schrimsher Construction Co., Huntsville, $1,279,009,facility modifications at Marshall Space Flight Center.

Martin-Marietta Corp., Baltimore, Md., $1,274,761 formanufacturing horizon sensors and associated power suppliesand for designing manufacturing and testing high pressurehelium storage bottles.

Reynolds EleqtTical and Engineering Co., Freeport. Tex.,$1,172,468, electrical checkout facilities.

Vitro Services, Ft. Walton Beach, Fla., $1,027,751,mission support of NASA and prime contractor for test instru-mentation control.

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

Edwards Air Force Base, $800,000, study of blast hazardsof rocket propellant.

-more-


42/53

- 42 -Telecomputing Corp., $777,833, operation of computer

facility at Slidell, La.Ryan Electronics of San Diego, $759,100, design and

fabrication of radar altimeters.A.0. Smith of Milwaukee, wisc., $622,137 for pressuri-

zation spheres.Wyle Laboratories, Huntsville, $607,669 for vibration

testing.Electronic Communications of St. Petersburg, Fla.,

di531,579 for development and fabrication of two prototypeflight control computers.

-more-


43/53

-43-SA-5 GLOBAL TRACKING 4

The Saturn SA-5 orbital vehicle will be tracked by anunusual combination cf national tracking and data acquisitionfacilities. Portions of the manned space flight newtorkand the STADAN (Satellite Tracking and Data Acquisition Net-work--formerly Minitrack) will be supported by the SAO(Smithsonian Astrophysical Network) and elements of theDepartment of Defense national ranges in forming a uniqueglobal tracking network for the SA-5 mission,

The Smithsonian network will cooperate in supplyingorbital tracking information through the use of its opticaldevices called Baker-Nu.nn cameras.

DOD participating stations are: Hawaii, Point Arguello,Calif.; White Sands, N. M.; Corpus Chtisti , Tex.; CapeKennedy, Fla.; and certain other stations of the AtlanticMissile Range.

Manned space flight network stations involved includethose located at Bermuda, Canary Islands, Woomera, Australia;Guaymas, Mexico; and NASA's net duai-purpose tracking stationat Carnarvon, Australia, should become operational by launchdate. ThesE s'9ions will record telemery for one orbitand "skin-track" with C-band and S-band radar fo r an indefinite

- more -


44/53

-44 -

period. The precounc, countdown and firisU ';o olbi;o willbe 1 ;recated in a i-iarincr similar so Mheercul'y-Altas missions,with The network under tuie control of a neCwork director a'.Ghe space opcrations .control center at Goddard Space FlighiVCenter.

Although the air-to-ground voice links and command sub-systems will not be used, svandard operations procedures willbe employed. Radar data will be transmitted to Goddard inreal tlime and the standard station-to-station voice communi-cation network will be used.

The S-IV seconc stage, the instrument; unit, and thedummy payload are e,;pekrted Jo be placed in an orbit ofapproximately 160 statute miles perigee and 400 statutemiles apogee and should thus give the radars a rood target.The telemetry beacons of the vehicle may operate for onecomple'e orbit, Beyond this, radar look angle data will becomputed at GSFC and determination of daily individualstation tracking assignments will be made.

A minitrack beacon on board the inert payload willpermit the STADAN stations to constinue tracking for possiblya period of weeks, and computers will periodically updatethe look angles fov up to 45 days.


45/53

- 45 -BLOCK I TESTING

The four Saturn I rockets launched to date were knownas "Block I" vehicles. SA-5 is the first "Block II"vehicle; all remaining Saturn I's will be of this design.

The Block I's all performed satisfactorily and weredeclared complete successes.

All consisted of boosters with water ballast in thesimulated upper stages. The boosters were each powered byeight H-1 engines rated at 165,000 pounds thrust.

The four vehicles were launched from Cape KennedyComplex 34 on an azimuth of 100 degrees with primary missionsof flight testing the booster propulsion system, vehiclestructure and the control system and to deteinmine the com-pabibility of the booster with ground support equipment.

SA-1, the first, was launched at 10:06 a..., iST, Oct.. 27,1Q, '- ' ;oui; 4;ocbli-aJ. holds in sGhe countdown. Two weather

holds we c oal ld to allow clouds to clear sufficiently fo rcamera coverage of the flight. One hold was for 34 minutesat T-120 minutes, and the second was for 32 minutes at T-20minutes.

Liftoff weight of SA-1 was 929,000 pounds, with a liftoffthrust of 1,300,000 pounds. The rocket reached an altitudeof 85 statute miles and traveled 215 statute miles down theAtlantic rdnge.

- more-


46/53

-46-

The inboard engines were cut off after 110 seconds whenthe rocket was 26 miles above the Earth traveling at 3,400miles per hour. Cutboard engines were cut off six secondsltser at 30 mines altitude and at -'3,600 miles per hour.

The only slight cause for concern waG a higher degree ofpropellant sloshing than was expected. This occurred duringthe later phases of the flight but did not affect vehiclestability.

SA-2, aith "Project Highwater" as a secondary mission,left the launch pad at 9 a. m., EST, April 25, 1962, withoutany technical holds during countdown. A 30-minute hold wasmade at T-10 to allow an unidentified ship to clear therange area.

Liftoff weight was 940,000 pounds with liftoff thrustat 1,280,000 pounds. SA-2 reached an altitude of 65 statutemiles and traveled 5u miles down range before being destroyed,after 162 seconds of flight, to release the water ballast intothe lower ionosphere and successfully complete "ProjectHighwater. "

Inboard engines were cut off after 111 seconds of flightac an altitude of 31 miles and at a speed of 3,500 mph. Outboardengines were cut off after 117 seconds at 35 miles altitudeand at ,,'715 mph.

- more-


47/53

47-

Additional propellant tank baffles prevented the excessivesloshing experiences in SA-1. The control system performedOa'-isfactorilw.

MIore missions .ere given SA-3. Particular interest wasput on the operation of the umbilical tower and the Block IIliquid oxyger-loading swing arm, both of which were beingused for the first time, A full propellant load was alsocarried.

As secondary missions, another Project Highwater wasscheduled as well as a flight test of live retrorockets.

SA-3 left the pad at 12:45 p. m., EST, Nov. 16, 1962, aftera 45-minute hold at T-75 minutes due to a ground generatorpower failure. Lift off weight was 1,100,600 pounds andthrust was 1,260,000 pounds. The rocket reached 104 statutemiles altitude and went 131 miles down range before destructionfor Project Highwater.

The inboard engines were cut off after 141 seconds offlight at an altitude of 33 miles and at a speed of 3,750 mph.Outboard engines were cut off after 149 seconds at 38 milesaltitude and at 4,000 mph.

- more -


48/53

-48 -

Launch pad equipment funct: led normally e:,cept for theLOX fill arm which failed to retract at lift off.

Damage co pad equipment wias less than was e:;pectud. Moredamage was anbicipated because she vehicle was 160,uju poundsheavier than SA-2, which reduced the rate of liftoff accolera-tion of the vehicie.

The retrorockets were fired 12 seconds after the lastengine cutoff. Performance was within the predicted limits.Project Highwater also wleas a success.

SA-4 took on an unusual experiment in addition to theprimary missions. In this flight, one engine was to be cutoff to determine the booster's ability to carry on with onlyseven engines.

Three technical holds delayed the launching 102 minuteson March 28, 1963. The first, for 20 minutes, was to correctan out-of-tolerance indication in the ST-90 stabilized plat-form. The second hold was for 40 minutes and was due toproblems with the ST->' theodolie :and telemetry groundc-libra,;ion sys'tem.

The las: hold, for 4_ minuses, ;:as caused by the lack ofa LOX bubbling valve open indication.

- more -


49/53

-49-SA-4 was launched at 3:11 p, m., EST, with its liftoff

weight of 938,000 pounds being pushed by a thrust of 1,289,u00pounds. The rocke- roso to 81 mile.x above she earth andtraveled 22i miles cown r'..nge.

The inboard engines were cut off at 113 seconds at 25miles altitude and at 3,420 mph. Outboard engines were cutoff at 120 seconds at 30 miles altitude and 3,660 mph.

Propulsion system performance was well within designparameters. Shutdown of engine number 5 at 100 secondspresented no probelsm. The feasibility of the engine-outconcept was proven.

Retrorocket performance was well within the\pxedictedlimits although they induced some vehicle roll as they didin SA-3.

Umbilical tower static pressure and vibration measure-ments were higher than expected, confirming SA-3 measurements.The first engineering test of the Missile Trajectory Measure-merit device and radar altimeter were successful.


50/53

-50-

LAUNCH COMPLEX 37The fifth Saturn rocket, SA-5, will be launched from

the largest, newest and most sophisticated launch facility atCape Kennedy--Launch Complex 37.

Encompassing 120 acres, Launch Complex 37 lies just northof Launch Complex 34, where the four previous Saturns werelaunched successfully.

Construction of the $65 million complex was begun in thefall of 1961 and was completed earlier this year. The facilitywas checked out and accepted by the NASA Launch OperationsCenter last spring.

Launch Complex 37 has dual launch pads (Complex 34 hasonly one) and associated facilities.

The two launch pads 1,200 feet apart, are designated"A" and "B". Pad B has been completed and will be used forthe launch of the SA-5. Work is still underway on Pad A,which will be utilized in later Saturn launches.

Each pad has its own umbilical tower, launch pedestal andautomatic ground control station. A single launch controlcenter serves both pads as does a hug6, mobile servicestructure which moves between the two pads on steel railes PadsA and B also share a central propellant storage and transfersystem. - more -


51/53

-51-

A distinguishing feature of Launch Complex 37 is thedual umbilical tower arrangement. Each tower is 268 feethigh and has a 32-foot-square base. The towers can beextended to a height of 320 feet should the need arise forfuture programs.

The two launch pads of Complex 37 are served by a central"brain"--The Launch Control Center--located 1,000 feet away.It is a half-sphere 110 feet in diameter and 37 feet high.Its blast-resistant dome is more than 12 feet thick. Morethan 3,000 cubic yards of concrete and 400 tons of steel wereused in constructing the Launch Control Center.

From the Center, the entire SA-5 missioi will be conducted--launch, tracking, observation and test supervision. It isfrom here that Dr. Kurt H. Debus, director of the LaunchOperations Center, will supervise the team charged with theentire launch phase of the SA-5 mission.

The laddscape of Complex 37 is dominated by perhaps thelargest mobile facility in the world--the seven million poundservice structure. It rools between Pads A and B, to provideaccess for technicians and scientist who must check out everyloot oI' the Saturn rocket. The service structure soars 328feet to the base of a derrick boom at its top. The mast


52/53

- 532

uf Wis derrick--or crane--extends to a maximum 60 feet and canlift a maximum weight of 60 tons.

The service structure's 120-foot-square base rides on72 wheels, each three feet in diameter, as it moves along itsmassive tracks at 40 feet per minute. In working position ateither of the pads, the service structure's weight is removedCrom the wheels by hydraulic arms, lowered onto foundationanchor assemblies and locked into place.

The SA-5 will be launched from a pedestal which is 47feet square, the same size as the pedestal on Pad A. In thecenter of the pedestal is a 12bsided, 32-foot-diameter ringwhich allows engine exhaust to eszape during launch.Triangular platforms rest on top of the pedestals to providea work area around the base of the rocket.

Complex 37 has a complete fuel ctorage and transfersystem for both liquid o;ygen/RP-l and liquid oxygen/liquidhydrogen engines. (Complex -4 had no liquid hydrogen facilitiesoriginally; the complex is now being modified to include them.)Among the facilities on Complex 37: A 125,000 gallon storageunit and a 28,000 gallon replenishing tank for storing RP-l(kerosene) fuel; a 125,000 galloi storage tank for liquidhydrogen.


53/53

-53-

In addition, a high-pressure gas facility providesnitrogen and helium for purging fuel lines, actuatinghydraulic systemsetc., for both Complex 39 and nearby Complex34.

END

sa-5 press kit

Documents