apollo boilerplate 22 press kit

8/8/2019 Apollo Boilerplate 22 Press Kit

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NATIONAL AERONAUTI(S AND SPACE ADMINISTRATION TELS W) ?-41',WASHINGTON D C 20546 W(O 1-'/"9'.FOR RELEASE: SUNDAYp0i May 9, 965RELEASE NO: 65-145R PROJECT: APOLLO BOILERPLATE 22

SCHEDULED LAUNCH:

CONTENTSs REGULAR RELEASE. . ...... ............ .. . 1-3BACKGROUND INFORMkTIONO ................... 4-11

Flight Plan............................... 4-6S Test Vehicle Components andCharacteristics........................ 6-11

CONTRACTOR PARTICIPATION................O... 11-12D IAG AMS...R......... 12-17

KTTo be launched no earlier than May 19.


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NATIINAL AERONAUTICS AND SPACE ADMINISTRATION TELS WO 2-4155E AdA WASHINGTON, D.C. 20546 WO 3-6925FOR RELEASE: SUNDAYMay 9, 1965

IflEA"AE NO: 65-145

NASA TO TESTAPOLLO ESCAPE SYSTEM

AT HIGH ALTITUDEThe National Aeronautics and Space Administration will

conduct the fourth in a series of Apollo spacecraft launchescape system test at White Sands Missile Range, N. M., no earlierthan May 19

The spacecraft, called Apollo Boilerplate 22, will belaunched by a Little Joe II rocket to an altitude of 112,000Ieet above the ground where the Apollo launch escape subsystemwill be fired. The escape motor will carry the spacecraftto a peak altitude of about 175,000 feet

The spacecraft is expected to land about 110 miles up-range near Williams Ranch, private property leased by thegovernment to extend the White Sands Range.

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MaIn objectives of this test are:1 To determine performance of the launch escape vehicle

at an altitude apDroximating the upper limit of the canardsubsystem. Canards are small wings on the forward section.of the escape rocket to orient the'Apollo command moduleaerodynamically in an escape situation in the atmosphere.

2 To demonstrate orientation of the launch escapevehicle to a relatively stable position with the main heatShield forward, using the canards, for proper deployment ofdual dRogue parachutes.

During a launch of the three-man Apollo spacecraft,the launch escape subsystem would be used to propel the space-craft and its crew to safety in the event of a Saturn launchvehicle failure either on the pad or during powered flight.

The Apollo Jiolerplate spacecraft will incorporate for thefirst time a Jettisonable forward heat l. ld which will beseparated from the command module by thru-sters prior toparachute deployment A new pilot and main parachute designalso will be used Uor the first time.

Previous tests of' Apollo spacecraft launch escapevehicles conducted from Wi.te Sands were:

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Boilerplate 6 - Nov. 7, 1963 - Successful abort from thelaunch pad.

Boilerplate 12 - May 13, 19164 - Successful high dynamicpressure tests dispite failure of one of' the three main space-craft parachutes to deploy fully.

Boilerplate 23 - Dec 8, 1964 - Successful abort atmaximum dynamic pressure region. (This abort was at about31.000 feet.)

Last December's test was the first using canard sub-system, dual drogue parachutes, a command module boostprotective cover and a Little Joe II with control fins fo rguided flight during the boost phase, all of which will beused fo r this test

Two more abort tests are planned this year at WhiteSands including an off'--the-pad abort using Boilerplate?3 again (redesignated BP-23A), and a fourth Little Joe IIabort test using a flight production Apollo spacecraft (Space-craft 002) instead of' an engineering test "boilerplate."spacecraft 002 will be th"? first actual Apollo spacecraftto be 1aurlikef

(BACKGROUND INFORMATION IOL1LOWS)L- ;Wmnk -r


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- l -FLIGHT PLAN

The test vehicle will be launched from Complex 36 atWhit_ Sands Missile Range in a northerly direction at an angleof about 34 degrees to the horizontal A launch signal, viaelectrical ca'bles from the blockhouse, will ignite threefirst stage Algol solid propellant rocket motors in the LittleJoe II launch vehicle.

The three second-stage Algol motors will be ignitedabout 40 seconds after liftoff by an onboard timer ignitioncircuit as the first stage burns out The second-stageAlgols will propel the test vehicle to the test point,about 112,000 f' t Flight trajectory will be programmed byan autopilot aboard the Little Joe II, "sterring" thelaunch vehicle by actuating aerodynamic control surfacescn the launch vehicle's L'ins.

Abort will take place about 89 seconds after liftoff,commanded by radio from the ground The abort signal willbegin separation or the Apollo command module frumn theservice module, ignition of the pitch control and launchescape rocket motors, and (1.1 seconds later) depolyment of' thecanard surfaces

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The Apollo launch escape vehicle will coast in tumblingflight to an altitude of about 175,000 feet, then begin itstumbling descent. Canards and the launch escape subsystemwill stabilize the spacecraft with its aft heat shield for-ward and downward.

At an altitude of about 21,000 feet above the rangethe tower jettison rocket motor will carry away the launchescape subsystem and boost protective cover. The forwardheat shield will be jettisoned 0.4 seconds later, exposingthe compartment which contains parachutes, the egress hatchand other equipment.

Dual-drogue parachutes will be deplbyed in reefed conditiontwo seconds after jettison of the launch escape subsystem.The drogues will be reefed for eight seconds.

At an altitude of about 6,000 feet above the range,the dual-drogue parachutes will be jettisoned and three mainparachutes will be deployed in reefed condition b. mortar-actuated pilot chutes. Eight seconds later the main parachuteswill be disreefed and inflated fully, lowering the spacecraftto a landing approximately 110 miles from the launch point.

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An approximate time sequence follows:T Lift-offT plus 40 seconds Second stage ignition atabout 27,000 feet altitudeabove range. *T plus 89 seconds Abort initiation at about112,000 feet altitude aboverange.T plus 100 seconds Canard deploymentT plus 152 seconds Peak altitude, about 175,000feet.T plus 300 seconds Launch escape subsystem jettisonat about 21,000 feet above the

range. **T plus 302 seconds Drogue parachutes deploy atabout 19,000 feet above therange.T plus 348 seconds Main parachutes deploy atabout 19,000 feet abovethe range.T plus 547 seconds Command module landing about

110 miles from the launch site.TEST VEHICLE COMPONENTS AND CHARACTERISTICSTotal Height: 85 feet, 7 inchesLittle Joe II: Height, 32 feet, 10 inches; diameter, 154

inches; powered by six Algol motors of 103,200 pounds thrusteach.

* Range is about 4,000 feet MSL in launch area.** Range is about 5,500 feet MSL in recovery area.

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The Little Joe II has an attitude control subsystemcon;isting oi' clevons (aerodynamic control surfaces) andhydrogen-peroxide reaction controls actuated by an autopilotin the airframe. Two radio frequency command receivers insidethe launch vehicle initiate abort upon receipt of a groundsiirnal .

Oerv cc Module (Boilerplate): Height, 13 feet, 2 inches;ilar-eAer, r)) nC'!(S: we.:ght. 10,000 pounds.

Command Module (Boilerplate): Conical shape; height, 11feet, 3 inches; diameter at base, 12 feet, 10 inches; weight,about 11,000 pounds. A main hatch provides accessto the interioroi' the command module. Four tracking beacons and four telemetryantennas are inzi..alled in the structural shell.

The command module exterior surface has a boost protectivecover which provides protection from aerodynamic heatingduring boosted fl.ight and from heat and soot generated by thelaunch escape and Jettison motors. It is made of ablativecork and Tet'lon-impregnated glass cloth, supported by glasshoneycomb in the upper third portion.

The forward (apex) heat shield forms the upper third ofthe exterior shell oF the command module, protecting parachutes,egress hatch and other equipment. Separate thrusters will beused to jettison the forward heat shield for the first time.Previously, the forward heat shield was bolted to the launchescape tower and jettisoned with the launch escape system.

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The dummy aft (base) heat shield on the command moduleis used to protect the command module frofl Earth landingdamage.

It is of sandwich construction with an inner and outerglass laminated skin with an aluminum honeycomb core.

Two tape recorders, each recording 14 tracks, and threemotion picture cameras are installed in the spacecraft. Thetape recorders will be recording telemetry and other data.A total of 230 measurements will be received from thermo-couples, vibration sensors, rate and attitude gyros, break-wire systems, accelerometers, pressure transducers and othersensors during the flight. One camera is in the command module,one in the service module and one in the LES tower.

The Earth landing subsystem consists of three ring-sailmain parachutes 833-I feet in diameter, three pilot chutes 7.2feet in diameter, two conical-ribbon drogue parachutes 13.7feet in diameter, and Pyrotechnics to actuate the parachutes,reefing lines, ree ing cutters, deployment bags, bridles,risers and sequencers to program events.

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-9-A new main parachute suspension system is being flown for

the first time, causing the spacecraft to hang at a 30-degreeIngle during descent. This will allow the command module toimpact properly into water. Although BP-22 is being flownover land, actual Apollo manned flights will re-enter forrecovery at sea.

Launch Escape Subsystem: The launch escape subsystemconsists of a launch escape rocket motor, a pitch controlrocket motor, a tower jettison rocket motor, a tower releasemechanism, a canard subsystem, a Q-ball assembly, ballastand tower structure. Total height is 33 feet.

The launch escape motor is 26 inches in diameter, 15feet, 3 inches long and burns approximately 3,200 pounds o.solid propellant while providing normal thrust of 155,000pounds.

The pitch control motor is nine inches in diameter and22 inches long. The housing forms the structure between theQ-ball assembly and forward end of the jettison motor. Itburns solid propellant.

The tower jettison motor is 26 inches in diameter and47 inches long, uses solid propellant and develops 33,000 poundsthrust. -mcr e


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The tower release mechanism consists of four explosivebolts, each containinlg a. 7riit cxplosl.vo charge with a dualignition feature to increase ieliabi.lity.

The canard subsystem is mounted in the Pi 'cch controlmotor housing between the Q-ball. assembly and the forwardend of the jettison motor. !'ach of the two canard surfacesis about 18 inches wide and 2)1 inches long. These aerodynamicsurfaces are Pyrotechnic-actuated 11 seconds after the escapemotor fires, acting as "wings" to stabilize the launch escapevehicle in a blunt-end-fox'ward pos~ition and reduce descentoscillations.

The Q ball assemibly is a conical-shaped unit on the for-ward end of the pitch control mIctor riousing. Four pressuresensors in the forward section ort the Q-ball system are usedto determine I'light angles c, attack and dynamic pressure.It is used fo r postflight test v1-ehicle trajectory analysisand evaluation.

Ballast is installed in thr.e launch escape subsystemto achieve desired dynam1.e: characteristic-Sc of the launchescape vehicle durln;, th( abort V

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Launcher: The launcher for Little Joe II is fabricatedsteel, using heavy I-beams for main supports. It uses apivot frame mounted on a crane-type truck for rotation to therequired launch azimuth, a support platform adjusted by jacksior launch angles, and a launcher mast.

CONTRACTOR PARTICIPATION

North American Aviation, Inc., Space and InformationSystems Division, Downey, Calif., prime contractor for space-craft command and service modules.

General Dynamics/Convair, San Diego, Calif., Little JoeII.

Aerojet-Genera] Corp., Sacramento, Calif., Algol motors.

Lockheed Propulsion Co., Redlands, Calif., launch escapeand pitch control motors.

Thiokol Chemical Corp., Elkton, Md., escape system, jetti-son motor.

Northrop Ventura Division, Newbury Park, Calif., landingsystem.

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American Wiancko, Los Angeles, Calif., Little Joe IIguidance gyros.

Walter Kidde, Belleville, N.J., Little Joe II reactioncontrol system.

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700 -- -Lr _- ! Command module nominalRange extension le landing point600 - -/

| ___ jLaunch vehicle nominal.i landing point500 - FWhite SandsMissile Range400 - 40|-Nominal flight path

o I .300 -

White SandsI 2National Monument0200-L

Alamogordo

N,/ Launch!/ -site0

US70WSrifR Post Area

I I I -200 100 0 100 200Distance, thousands of feet

Mission A-003 launch and landing areas at WSMR- . 4- . - = . -- - - ----


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LEV apogee

160-

E i -Canarddeployment Vn)120 - LeEVF LEV igitiob trajectory

~tr Launch: d4> veh icle A0/ trajectory

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/ Tower 3ttison tl'drogue parachuteStagirig deployment IMain parachutedeployment

0 160 320 480 640Range, thousands of feetMission A-003 nominal mission profile


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NOSE CONE ANDQ-BAL- ASSEMBLY

CANARDS (DEPLOYED)-- PP ITCH CONTROL MOTOR 'A

TOWER J TT ISON MOTOR

_____ LAUNCH ESCAPE MOTOR

LAUNCH ESCAPE TOWER

COMMAND MODULE(BOILERPLATE STRUCTUR BOO ST PROTECTIVECOVERDUMMY SCIMITARANTENNAS DUMMY UMBILICAL(2 PLACES) CONNECTION

SIMULATED AIR VENTSIMULATED STEAM VENT

SERVICE MOOULE/ (BOILERPLATE STRUCTURE,REACTIONSUBSYSTEM'4 PLACES)

_-__ S-SRVICE MODULEEXTENS IONLITTLE JOE IIINTERFACE

Spacecraft external configuration


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Note: All dimensions in inches

Pitch control motorTower Jettison motor 26.0Lunch escape motor CommandmoduleLaunch escape tower Spacecraft

-' 633.4Boost protective cover 135.0 Service1 / moduleAccess door +z 161.75 Test vehicle

__|_L_1027. 2-> : tAdapter ,

oJG- 10,0Access doorsLittle Joe IIlaunch vehicle

393, 843.8T -N 344.0


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Nose cone andQ-ball assembly Ballast enclosureCanards- .Ci

Pitch control motorcompartment

Tower jettisonmotor

Launch escape motor- r

+XC -- Structural skirt

C +zC Tower structureTower separationbolts

Boost protective cover

Commana moaule

apollo boilerplate 22 press kit

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