pad abort press kit

8/8/2019 Pad Abort Press Kit

1/9

N 63 23754NEWS RELEASENATIONAL AERONAUTICS AND SPACE ADMINISTRATION400 MARYLAND AVENUE, SW, WASHINGTON, D. C. 20546TELEPHONES: WORTH 2-4155 -------- WORTH3-6925FOR RELEASE: PMv's TuesdayNovember 5, 1963

jRELEASE NO. 63-247

NASA TO TEST APOLLO SPACECRAFT ESCAPE SYSTEM

The National Aeronautics and Space Administrationwill conduct the first off-the-pad abort test involvingthe Apollo spacecraft launch escape system no earlierthan Nov. 7 at the White Sands Missile Range, New Mexico.

NASA's Manned Spacecraft Center, Houston, is conductingthe test.

An engineering test vehicle that duplicates the sizeand weight of the three-man command module of the Apollospacecraft will be used. It will lift off a concrete padpowered by the Apollo launch escape motor mounted on alaunch escape tower attached to the module.

- more -


2/9

-2-

Purpose of the test is to determine the stability andoperational characteristics of the escape configurationduring a pad abort. The test vehicle is identified asBoilerplate No. 6.

Manned Spacecraft Center engineers say the pad-aborttest is developmental in nature. The engineers have onlywind tunnel data on which to predict the sequence of eventsin the test and they must extrapolate the wind tunnel datato actual flight dynamics. This is the first rocket-powered test of this particular spacecraft-tower configuration.

- more -


3/9

TEST OBJECTIVES

This mission has the following test objectives:1. First-order objectives:

a. Determine aerodynamic stability characteristicsof the Apollo configuration during a pad abort.b. Investigate the capability of the escape systemto propel a command module to a safe distancefrom a launch vehicle during a pad abort.c. Investigate proper operation of the launch escapetower release mechanism.d. Investigate proper operation of the tower jettisonmotor.e. Investigate proper operation of the parachuterecovery system.

2. Second-order test objectives:a. Investigate satisfactory abort and recoverytiming sequence.b. Determine spacecraft dynamics during jettisoningof the escape tower.c. Investigate the operation of research and develop-ment instruments and communications equipment tobe used on subsequent flights.d. Investigate compatibility of prototype groundsupport equipment.e. Determine initial separation trajectory of thelaunch escape tower.f. Determine escape tower vibration during a pad abort.

- more -


4/9

-4-

GENERAL FLIGHT PLAN

The test vehicle will be launched vertically fromtl-a White Sands Missile Range, an area about 4,000 feetabove sea level. A ground command abor\. signal will ac-tivate the abort sequencer in the command module. Planscall for the test to proceed on the following timetable:

T to T plus 8 seconds Launch qcape and pitchcontro mo-tors ignite, es-cape mom burns eightseconds, veZLcle attainsaltitude of 4,100 feet aboveground level at burnout.Vehicle continues upward onballistic trajectory.T ;lus 15.5 sec"nds - Jettison motor ignites andlaunch escape towei releasesat 4,900 feet. Escape towerand motor and apex heat shieldfall to earth in free trajec-tory.T plus 18.5 seconds - Dr'ogue chute deploys at 4,700feet, assisting in orientingblunt end of coimniand moduleforward for main chute deploy-ment.T plus 23.5 seconds - Drogue chute releases, pilotparachutes deploy and extractthree main chutes at 4,150 feet.T plus 27., seconds - Main parachutes at line stretchcondition at 3,400 feet.

-more-


5/9

-5-

I plus 29.5 seconds - Main chutes inflated in reefedcondition at 3,200 feet.T plus 33,5 seconds - Main chutes disreefed at 3,000feet.T plus 37.5 seconds - Main chutes fully inflated at2,800 feet. Equilibrium descentof approximately 24 feet per sec-

ond established.

-more-


6/9

-6-

TEST VEHICLE COMPONENTS AID CHARACTERISTICS

Weight of test vehicle is approximately 15,800 pounds.A breakdown and description of the major components of thetest vehicle is as follows.

COMMAND MODULE - The Command Module is of conical (resignapproximately 134 inches high and 154 inches in diameter atthe base, with a nominal Weight of 9,000 pounds. It His con-structed of aluminum alloy.

The apex heat shield or forward compartment cover formsthe forward section of' the outer structure and protectsthe parachute subsystem.

The main hatch provides access to the Command Module in-terior. The hatch is constructed of' reinforced aluminumplate and is bolted into pbice. It t As located on theCommand Module sidewall over the head of the center couch

position.The simulated aft heat shield consists of a sandwich typeconstruction wi h aluritinum alloy inner and outer skinsseparated by rloin-impregnated glassi laminations.

The -arch IanV nr.g osyste'b5LItc of pyrotechnics and pyro-technicall - ia.attc devico,3, one coni. :al ribbon drogueparachute, h:,->oe rLng-sai1 main parachutes, deployment bags,bridle~s, p>.lot pa.-acL,'tes, risers, an impact switch,

- m.ore


7/9

-7-

and a sequence controller. The drogue parachute is13.7 feet in diameter and is deployed by a mortar.The main parachutes are 88.1 feet in diameter and aredeployed by three mortar-deployed pilot parachutes whichextract the three main parachutes from their deploymentbags.

LAUNCH ESCAPE SYSTEMThe launch escape tower is a truncated rectangular pyra-mid constructed of welded tubular titanium alloy. It isapproximately 120 inches long with the base measuring 46by 50 inches. The tower forms the intermediate structurebetween the Command Module and the Escape and tower jet-tison motors.

The Launch Escape motor is a solid propellant motor withfour nozzles canted 35 degrees. The motor weighs approxi-mately 4764 pounds of which approximately 3200 pounds isfuel. The average thrust developed is approximately 155,000pounds.

The Pitch Control motor is a solid propellant reactionmotor which provides 3400 pounds of thrust for one halfsecond in a direction perpendicular to the vehicle centerline. This produces the required lateral displacement fromthe pad to insure crew safety.

-more- -


8/9

The tower jettison motor propels the expended launchescape system away from the Command Module to precludeinterference with the operation of the earth landingsystem. The tower jettison motor develops 33,000 poundsof thrust for one second and weighs approximately 540 pounds.

The tower release mechanism consists of four explosivebolts. Each bolt contains a single explosive charge andemploys a dual ignition feature to increase reliability.Positive release is assured when either one or both of theinitiators is fired.

GROUND ADAPTER - The ground adapter structure is a truncatedhexagonal pyramid approximately 200 inches in diameter at thebase and 48 inches high. The adapter, which simulates the launchvehicle interface with the Command Module, is leveled in thehorizontal plane and is mechanically attached to the concretelaunch pad.SUPPORT - Photographic support is required from launch throughimpact, for determination of position, acceleration, velocity,and attitude data. It will also supply data to fill requirementsfor engineering sequential and documentary films.Meteorological support requirements include wind direction andvelocity, air density, temperature, relative humidity up toaltitudes of 10,000 feet and is supplied by the White SandsMissile Range. General forecasts are also required to supportscheduling of the launch.

-more-


9/9

-9 -

RECOVERY REQUIREMENTS - Recovery of the tape recorded dataimmediately after impact is considered the primary requirement.The entire launch vehicle is to be recovered including theCommand Module, the recovery parachutes, forward compartmentcover and the entire Launch Escape System for post flightanalysis.

-END-

pad abort press kit

Documents