little joe ii apollo escape sytstem press kit

8/8/2019 Little Joe II Apollo Escape Sytstem Press Kit

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fby- /031Y* NATIONAL AERONAUTICS AND SPACE ADMINISTRATION TELS WO 2-4155

- d WASHINGTON, D.C. 20546 WO 3-625FOR RELEASEt SUNDAYDecember 6, 1964

RELEASE NO: 64-299

APOLLO SPACECRAFTTO TEST ESCAPE SYSTEM

IN WHITE SANDS TEST

The National Aeronautics and Space Administration willflight test the Apollo spacecraft from the White Sands MissileRange, N.M., no earlier than Dec. 8.

Major objective of the flight is to demonstrate satis-factory performance of the Apollo spacecraft launch escapesystem under conditions simulating a catastrophic launch ve-hicle failure at the altitude the spacecraft is under maxi-mum aerodynamic pressures. At the Whit( Sands Range, whichis 4,000 feet above sea level, the maximum pressure region

(Max-Q) is about 31,000 feet above the range.

The launch escape system, a 33-foot tower configuration,atop the spacecraft, is an emergency unit designed to jetti-son the command module and the astronauts to safety in theevent of booster failure before or during launch.

The test will employ a Little Joe II launch vehicle,producing approximately 34aLit ounds thrust, to boostApollo boilerplate command and service modules with a pro-duction launch escape system.

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In this test that launch escape system will utilizecanards -- a pair of wings or fins -- located near the topof the tower jettison motor. The canards deploy to turn thecommand module heat shield forward to lessen descent oscma-tions during an emergency abort.

Another spacecraft subsystem to be flight tested forthe first time is the boost protective cover. Consistingof a shell contoured to fit the sloping section of the com-mand module, the cover is designed to protect the lunar ex-cursion module docking mechanism from excess heating duringfirst stage boost, protect the command module windows from ( )soot and erosion caused by the launch escape motor. It alsoprotects the thermal control paint on the ablative material,The boost protective cover is Jettisoned with the launchescape tower,

Also, during this test, two spacecraft drogue parachuteswill be used instead of one.

Previous tests or the Apollo launch escape system con-ducted from the White Sands range were:

Nov. 7, 1963 - Successful pad abort simulation testMay 13, i963 - Successful high dynamic pressure best,

altnough one or the three spacecraft parachutes failed todeploy.

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FLIGHT PLAN

The test vehicle will be launched frot White SandsMissile Range (4,000 feet above sea level). It will beoriented in a northerly direction at avi angle of approxi-mately 84 degrees with respect to the horizontal. Thesignal to launch, transmitted by land-line from the block-house, will ignite the two Algol and four Recruit solidrocket motors simultaneously.

The test vehicle will follow a controlled trajectoryto the test point. Approximately two seconds prior toabort, on a radio command, the launch vehicle attitude-control subsystem will execute a pitch maneuver to attainan angle which approximates the emergency escape attitudefor the spacecraft.

The abort will be initiated by a launch vehicle ti.;iershortly after the radio command for the pitch-up maneuveris received. The abort is scheduled to occur about 37seconds after liftoff. The abort signal initiates the separa-tion of the command module from the service module, ignitionof the pitch-control and launch escape rocket motors, andactivation of the mission sequencer 11-second time delay.Eleven seconds after abort initiation, the canard surfaceswill be deployed causing launch-escape vehicle turn-aroundand stabtization with the command module aft heat shieldforward. Altitude of the launch-escape vehicle will be about46,000 feet above the range, 65 second .after liftoff.

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-4-The launch-escape subsystem, boost-protective cover,

and forward heat shield will be jettisoned as a unit by thetower jettison rocket motor, initiated by a baroswitch atabout 21,000 feet above the range. The dual-drcguepara-chutes will be deployed in a reefed condition two secondslater and will be opened six seconds after deployment. At8,000 feet above the range, the dual-drogue parachutes willbe released and the main parachutes will be deployed in areefed condition for a period of six seconds at which timethe main parachutes will be opened. Command module impactis scheduled for about seven minutes after liftoff.

Following is the detailed test sequence:T minus Zero LiftoffT plus 35.5 seconds Pitch-up maneuver at about

26,000 feet above the rangeT plus 37.5 seconds Abort initiation at about

31,000 feet above the rangeT plus 48.5 seconds Canard deploymentT plus 116 seconds Launch-escape tower, boost

protective cover, and for-ward heat shield, jettisonat about 21,000 fpet abovethe range

T plus 118 seconds Drogue parachute deploymentat about 19,000 fees abovethe range

T plus 133.8 seconds Launch vehicle and servicemodule impact about 32,000feet uprange

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-5-T plus 165.4 seconds Main parachute deployment

at about 8,000 feet abovethe range

T plus 166.1 seconds Launch-escape tower impactabout 31,500 feet uprange !

T plus 416.9 seconds Command module landing about34,000 feet uprange

TEST VEHICLE COMWONENTS AND CHARACMERISTICS

Height: 85 feet, 7 inchesLittle Joe II: Height, 32 feet, 10 inches; diameter,

154 inches; weight at launch, approximately 66,ooo poundsincluding approximately 40,000 pounds of fuel. Powered bytwo Algol motors, each with 103,200 pounds of thrust; andfour Recruit motors, each with 33,395 pounds of thrust. Totalthrust of the launch vehicle, approximately 340,000 pounds.

The Little-Joe II launch vehicle incorporates an atti-tude control subsystem which consists of aerodynamic andreaction control subsystems controlled by an airframe auto-pilot,

The launch vehicle command subsystem will receive theground-transmitted, coded radio signals to initiate thepitch-up maneuver and the launch vehicle abort timer.

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Service-Module (Boilerplate): Cylindrical design;height 13 feet, 2 inches; diameter, 154 inches; weight,9,600 pounds.

Command-module (Boilerplatel: Conical design; height11 feet, 3 inches; diameter at base, 154 inches; weight,10,000 pounds. The command module shell consists of twosubassemblies: the forward and aft sections of the crewcompartment. The forward section of the crew compartment isattached to the launch-escape tower attach fittings in theforward bulkhead. Other attach fittings are provided forthe aft heat shield struts, service module tension ties,ground support equipment, and service module thrust bearingand shear points.

The main hatch provides access to the interior of thecommand module. Eight openings are provided in the forwardcrew compartment shell fo r antennas.

The forward cover consists of an inner shell (the for-hard heat shield for flight and reentry protection) and anouter shell (boost-protective cover) ior protection from aero-dynamic heating during boosted flight.

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-7-The forward heat shield is a truncated cone shaping

the upper third of the command module and protecting theparachutes, egress hatch and other equipment. It is attachedto each of the four tower legs of the launch-escape subsystem.This shield, along witn the boost-protective cover, is removedwhen the launch-escape tower is jettisoned.

The boost-protective cover extends over the entireconical surface of the co.mnand module. The upper third ofthe cover (hard cover) consists of abl_ , cork, supportedby glass-honeycomb over a Teflon-impregnated glass cloth. Thelower two-thirds of the cover (soft cover) consists of abla-tive cork over Teflon-impregnated glass cloth. The Teflon-impregnated glass cloth is used not only for structural sup-port, but also to assure a smooth surface for ease of removalwhen the tower is Jettisoned.

The aft heat shield consists of an inner and outer glasslaminated skin with an aluminum honeycomb core. Its purposeis to protect the command module from aerodynamic heating andearth impact during the Earth-landing phase.

The electrical power subsystem consists of one 1,500watt-hour' an(i fcur 140 watt-hour silver zinc batteries. On--oard instrumentation consists of a telemetry system, motionpicture cameras and a cape recorder.

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The Earth-landinu ;paracnute) subsystem consists of pyro-technics and protechnic-actuated devices, dual-conical-ribbondrogue parachutes (1,. feet in diameter), three pilot parachutes,three ring-sail main parachutes (88.1 feet in diameter), deploy-ment bags, bridles, risers, and an Earth-landing subsystem

sequencur.

Launch-Escape System: The launch-escape subsystem con-sist;s of a tower sructure, launch-escape motor, pitch-controlmotor, tower-jett's(n motor, tower-release mechanism, canardsubsystem, Q-ball assembly, and ballast.

The tower stru ture of the launch-escape subsystem isthe intermediate structure between the command module and thelaunch-escape motor-mounting skirt. It is approximately 120inches long and has a base approximately 40 x 50 inches. itis attached to the command module by the tower-release mechanism.

The la.unch escape motor weighs approximately 4,800 pounds,is 26 inches in diameter, 183 inches long, and burns approxi-mately 3,200 pounds of solid fuel while providing a nominalthrust of 155,000 pounds for approximately six seconds.

The pitch-control motor is a solid propellant reactionmotor, 9 inches in diameter and 22 inches long. The housingfor the motor forms the structure between the Q-ball assemblyand forward end of the Jettison motor.

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-9-The tower-jettison motor is also a solid-propellant re-

action motor. It is 26 inches in diameter, 47 inches long,has a gross weight of 550 pounds and develops 33,000 poundsof thrust for one second.

The tower-release mechanism consists of four single-modeexplosive bolts. Each bolt contains a single explosive chargewhich incorporates a dual ignition feature to increase re-liability.

The canard subsystem is mounted in the pitch-control motorhousing between the Q-ball assembly and the forward end ofthe jettison motor. The canard consists of two pyrotechnic-actuated stabi~king "wings" about 18 inches wide and 24 incheslong which are deployed about 11 seconds following the launch-escape subsystem rocket motor ignition. The canard effectsthe turn-around maneuver to turn the command module to theblunt-end-forward position to minimize command module descentoscillations. Tumbling actions within acceptable limits areexpected during the turn-around maneuver.

The Q-ball asf.-mbly !'a a conical-shaped unit placeu onthe forward end of the pitch-control motor housing. Itsweight is approximately 23 pounds. By means of four staticpressure pickups in the front section of the Q-ball system,angles of attack can be obtained for use in test vehicletrajectory analysis and evaluation.

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Dynamic pressure can also be determined Prom these pressurepickups.

The launch-escape subsystem has provisions for the in-stallation of ballast which will be used to achieve desireddynamic characteristics of the launch-escape vehicle duringthe abort sequence.

Launcher: The launcher is a fabricated steel structure,using heavy I-beams for main supports. The components includea pivot frame mounted on a double flange, crane-type truckfor rotation to the required azimuth position, a supportplatform incorporating pads and pins for vehicle support, screwJacks for tilting the support platform to required elevationangles, and a launcher mast.

CONTRACTOR PARTICIPATION

North American Aviation, Inc., Downey, Calif., primecontractor, spacecraft command,service module.General Dynamics/Convair, San Diego, Calif., LittleJoe II.Aerojet-General Corp., Sacramento, Calif., Algol motors.Thiokol Cnemic&l Corp., Bristol, Pa..R(:cruit Motors.Lozkheed Propulsion Co., Redlands, Calif., launch escapeand pitch control motors.Thiokol, escape system Jettison motor.Northrop Corp., Beverly Hills, Calif., landing system.

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little joe ii apollo escape sytstem press kit

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