Project Apollo End Item Specification, Boilerplate Number 23A

8/6/2019 Project Apollo End Item Specification, Boilerplate Number 23A

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(NBSA-CR-116766) PBOJECT APOLLO END ITEPIPECIF ICAT ION , BOILERPLATE N U R B E R 23A (NorthAmerican A v i a t i o n , I n c , ) 28 p N79- 764 6Unclas I

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Acce8sion NO. 05249-65N0

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I Copy No. 6 SID 65-197r n - O J E T APOLLO

E N D ITEM S P E C I F I C A T I O NB O I L E R P L A T E NUMBE3 23A (U )

I 12 March 1965 NAS 9-150

Paragraph 4.2 Ekhibit I

This document ccntai fecting the national defense of theUnited States within the Espionage Laws. Title 18 U.S.C.or revelation of its contents in anySection 79 3 and 794.manner to an unauthori

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C C E S SI O N N U M B E R

TECHNICAL REPORT INDEX/ABSTRACTD O C U M E N T S E C U R I TY C L A S S I F I C A T IO N

C O D E

Project Apollo Rld Item Specification Boilerplate No. 23A

O R I G I N A T I N G A G EN C Y A N D O T H E R S O U R CE S D O C U M E N T N U M B E RNctrth American Adation Inc.,S y s t a m Did8ion - Down ey , C a l i f .(EAA/Sm) space aad Information 3ID 65-197

L. W. U r h - Bmon6ible EngineerU T H O R ( S )P U B L l C A T I O N D A T E12 Marah 1965 C O N T R A C T N U M B ERNAS 9-150

D E S C R I P T I V E T E R MS

This documant i r an End Itaa Spmcification, BoilerplateMumbar 23A, a part of the Aceepta?ltt Data ?achge require4under Exhibit I, paragraph 4.2 of the negotiated contractdated 25 Janrpary 1963.

-B S T R A C TThir Specification dofinem the require monte^ for arimulated A p o l l o Spacecraft aexmirting of a Launch EscapeSy&m and a Canrpnd Module hereinafter referrad t o aaBoilerplate Number 238.8 f t e a pad abort f'roln a Saturn launch vehicle i n themmt of an emergemay.

Boilorplate Number 2 3 A 8 U

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, I N O R T H A M E R I C A N A V I AT I O N, I NC . S P A C E and INFO RM ATIO N SYSTEM S DIVISION--TABLE OF CONTENTS

1. SCOPE1.1 Scope1.1.1 Specification Organization1.1.2 Mission2.2.12.2

3.3.13.1.13.1.23.1.33.1.43.1053.1.73.1.9

3.1.63.1.83.1.103.1.113.1.123.23.2.13.2.1.13.2.1.23.2.1.33.2.1.43.2.1.53.2.1.63.2.1.73.2.1.83.2.1.93.2.1.103.2.1.10.13.2.1.10.23.2.1.10.3

APPLICABLE DOCUMENTSProject DocumentsPrecedence

REQUIREMENTSGeneralWeightMaterialsFabricationDesign CriteriaElectromagnetic InterferenceEnvironmentCheckout ProvisionsInterchangeability and ReplaceabilityIdentification and MarkingIdentification and TraceabilityLubricationReliabilityConfiguration

LAUNCH ESCAPE SYSTEM (LES)Q-Ball AssemblyBallast EnclosurePitch Control MotorCanard SyatemTower Jettison MotorLaunch Escape MotorStructural SkirtLaunch Escape TowerBoost Protective CoverLES Electrical SystemLES Electrical W i r i n g HarnessLES Hotwire Igniter CartridgesLaunch Escape Tower Sequencers

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C I C

3 . 2 . 1 . n3.2.1.11.13.2.1.11.23.2.1.11.33.2.1.123.2.1.l.33 . 2 . L l 3 . 13 . 2 . 1 . u3.2.23.2 .2 .13 ,2 ,2 ,1 ,13.2 .2 .1 .1 .13.2.2.1.1.23.2.2.1.1.33.2.2.1.23.2.2.1.2.13.2.2.1.33.2.2.1.3.13.2.2.1.3.2

TABLE OF CONTENTS (Con't)

LES Pyrotechnic SystemPgrotechnic BatteriesEl ec tri ca l Wire BussesHotwire InitiatorsLES Umbilical SystemLES R and D InstrumentationLES Camera SystemLE3 Tower-CM S eparation SystemCommand Module StructureForward Bulkhead and Egress TubeForward Crew CompartmentA f t Crew CompartmentApex Forward Compartment Heat Shield CoverApex Forward Compartment Cover Heat ShieldAttachmentA f t Heat ShieldAccess HatchAccess Doors

C W N D MODULE (CM)C 8 ? b fCXSkIlg

3.2.2.2 EARTH LANDING SYSTEM (EIS)3.2.2.2.1 ELS Sequencer3.2.2.2.2 Parachute System3.2.2.2.2.1 Drogue Parachute System3.2.2.2.2.1.1 Drogue Parachutes3.2.2.2.2.1.2 Drogue Parachute Deployment Bag3.2.2.2.2.1.3 Drogue Parachute Mortar Assemblies3.2.2.2.2.1.4 Drogue Parachute Risers3.2.2.2.2.1.5 Drogue Mortar Pyrotechnic Cartridge3.2.2.2.2.2 Drogue Disconnect Assembly3.2.2 .2 .2 .3 Main Landing Parachute Assembly3.2.2.2.2.3.1 Pilot Parachute System3.2.2.2.2.3.1.1 Pilot Parachute3.2.2.2.2.3.1.2 Pi lo t Parachute Deployment Bag3.2.2.2.2.3.1.3 Pilot Parachute Mortar Assembly3.2.2.2.2.3.1.43.2.2.2.2.3.1.5 Pi lo t Parachute Riser3.2.2.2.2.3.2 Main Parachute Pack Assembly3.2.2.2.2.3.2.1 Main Parachute3.2.2.2.2.3.2.2 Main Parachute Deployment Bag3.2.2.2.2.3.2.3 Main Parachute Riser3.2.2.2.2.3.33.2.2.2.2.3.4 Vehicle Harness Assembly

Pi lo t Parachute Mortar Pgrotechnic Cartridges

Main Parachute Pack Retention Flap

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TABLE OF CONTENTS (Conttd)

3 2.2.3 EIJWI'RICAL PaJER SYSTEM3.2.2.4 ABORT SEQUENCER3.2.2.53.2.2.5.1 RF Ele ctro nic Equipnent3.2.2.5.2 Data Equipment3.2.2.5.3 Antenna E @ p e n t3.2.2.5.3.1 Telemetry Antenna System3.2.2.5.4 * B a l l System3.2.2.6 R AND D I N S T R ~ A T I O N3.2.2.6.1

RESEARCH AND DEVELOPMENT COMMUNICATION (R&D)EQUIPMENT

R and D Instrum entation Equipnent3.33.3.14.4.14. 24.2.14.34.3.14.45.6.6.1Figure

5.1

12345

PERFORMANCELAUNCH ABORT MISSIONQ U A L I T Y ASSURANCEGeneral Quality Assurance ProvisionsCo ntractor? Qu ality Assurance ProgramReliability DataEscamination

CamponemtsTestsPREPARATION FOR DELIVERYPreservation, Packaging, and PackingNUITSReference Documents

Configuration, Boilerplate Number 23ABoost Protec t ive CoverInstrumentation Block D i a g r a m , Boilerplate No. 23ALaunch Abort Mission, Boilerplate No. 23Acanard Systenl

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P R W T APOLLOEND ITEM SPECIF'ICATIONBOILWPLATE NUMBER 23A1. SCOPE1.1 Scope.- This specification defines the requirements f o r a s k l a t e dApollo spacecraft consisting of a Launch Escape System (US), and a CapnmandModule (CM), he re in aft er re fe rr ed t o as Boilerplate Number 23A.1.1.1 Swcif icat ion 0mani~at ion.- This specification i s organized as abasic section only.2.1.2 lfLssion.- The mission of Boilemplate Number 23A i s t o simulate apad abort frcan a Saturn launch vehicle i n the event of an emergency.fiight s h a l l consist of the IES propelling the Launch Escape Vehicle (IEV)away frcnn th e launch pad and subsequent recoverg -em operation forsafe CM landing.

The

2. APPLICABLEDOCUMENTSThe following documents, of the exact i ssue shown, shall form a part ofthis2.1

-specification t o t h e extent specified herein;Project Document8SPECIFICATIONS

MItL6880B25 August 1954 Iabricating, Aireraft, GeneralSpecification forNorth American Aviation, Inc., Space & Information SystemsDivision (NAA/s&U)SID 63-31322 February 1965

STANDARDSMilitaryMTGSTD-13OB24 April 1962

CSM Technical Specif ica tion,Block I

Identification Markirrg ofU.S. Military Property

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* c2.2 Precedence.- The order of precedence in instance of conflictingreqpirements shall be as follcms:

a. The Contract, NAS 9-150b. This specificationC. Other documents referrencod herein

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03.1 General.- The following paragraphs de fine the requirements f o r design,fa br ic at io n, assembly, and performance f o r Boi le rp la te Number 23A. Systemsand subsystems developuent plan philosophy i s reflected i n the NAA/S&ID,Apollo Program Plan (see Section 6 ) .3.1.1 WeiRht.- Weight, center of gra vit y, and moments of iner t ia data fo rBoilerplate Nwnber 23A shall be defined i n the NAA/S&ID Actual Weightand Balance Report (see Section 6).3.1.2 Materials.- Materials sh al l be campatible with design, weight, andload cri teria.3.1.3 Fabrication.- S tr uct ur al design concepts of Boi le rp la te Munber 23Amp3asize auplqmentof m e r ?manu_rScr.tur?hgechniques and methods t o th egreatest possible extent. Maximum use shall be made of developed off-the-shelf' ccanponents fabricated by dependable manufacturers.3.1.4 Desim Criteria.- Design c ri te ri a sh al l be i n accordance withrational design principles as specified i n Specification SID 63-313.3.1.5 ElectrcaaaRne ti c Interference.- Electramgnetic interference controls h a l l be invoked t o preclude po ss ib il it y of comprcdse of range safety or3.1.6 Environment.- The env irom ent al design c r i t e r i a f o r Bo iler pla teNumber 23A s h a l l be as specified i n Sp ecif ica tion SID 63-313.degradation of analytical data.

3.1.7 Checkout pKwlsions.- Boile rpla te Number 23A shall be designed withprovisions for system and integrated systems checkout and t es t capabil i t ies.3.1.8 Intercharuzeability and Replaceabilits.- Mechanical and e l ec t r i ca linterchangeabil i ty sh al l d s t between li k e assemblies, subassemblies, andreplaceable parts of opera ting subsystems (electro nic, el ec tr ic al , e tc )rega rd le ss of th e manufacturer or supplier. Non-operating subsystems suchas structure need not comply with this requirement. Interchangeability f o rthe purpose of this paragraph does not mean iden ti ty , but re qu ir es that asubs t itu t ion of such U e ssemblies, subassemblies, and replaceable partsbe easily effected without physical or el ect ric al modifications t o any partof th e equiplent o r assemblies,including cabling, connectors, wiring, andmounting, and without re so rti ng t o selectio n; however, adjustment ofvar iable res is tors and t r i m e r capaci to rs may be made.th e e qu ip en t, provisions s ha ll be made f o r design tolerances suffic ient t oaccamnrnrlate various sizes and characteristics of any one type of a r t i c l e ,such as tubes , re si st ors , and othe r components having the limiting dimensionsand characterist ics s et fort h i n th e sp ecificat ion fo r the pa rticu lar com-ponent involved without departu re from th e speci fied performance. Wherematched pairs are required, they sh al l be interchangeable and identified asa matched pair or set .

In th e design of

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3.1.9 Ident i f icat ion and lbrldnj?.- SpecificatLon MILSTD-130 sha l l beconsidered as a reference guide i n i den ti f i ca t i on marking of equipzlent,assemblies, and parts.3.1.10 Ident i f i ca t ion and Traceability.- Apollo identification andt r aceab i l i t y sha l l be i n accordance with th e co nt ra do r* e approvedqaality control plans.3.1.11 Iubricati0n.- Iubrication of ccmponents, where required, shall be i naccoMance with the requirements of Specification MILL6880.base lubrican ts sh al l be used. Iubricants shall be of the s i l i cone base,f h l u b e , q l u d e 702, and dry f i lm type. Iubricsitlon shall not cause anyt d c or ilanrmrrble substances t o occur in t h e CM or in th e environmentalcontrol aystam.

NO petrol-

3.l.U Reliability.- NAA/S&ID shall establ ish a r e l i a b i l i t y program i naccordance wi th the provisions of Coiltr&ct?$AS9-159.3.2 Configuration.- The configuration of Boilerplate Number 23A is showni n Figure 1.3.2.1 Launch Escape System (IES).- The IXS sh al l consis t of the followingmajor component8 :

&B a l l assemblyBallast enclosurePitch Control motorcanard SgstaTuwer jet t is on motorLaunch escape motors t ruc tu ra l skirtLaunch escape towerBoost protective covetrIES e l ec t r i ca l ggstanIES pyrotechnic systemLIB umbilical systemIES R and D instrumentationLES Tawer - CM separation system

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3.2.1.1 Q-Ball Assembly.- The Q-Ball Assembly which is located in the apexof the XES, shall be installed on Boilerplate Number 23A at the White SandsMissile Range (WSMR).Q-Ball to the PAM/FM/FM telemetry system in the CM.component description and functional operation of the Q-Ball System).A w i r e harness shall transmit the signals from the(See 3.2.2.5.4 for

3.2.1.2 Ballast Enclosure.- The ballast enclosure shall be constructed ofstainless steel and shall be capable of housing up to 960 pounds of ballast,the pitch control motor, and the canard system.3.2.1.3 Pitch Control Motor.- The pitch control motor shall be a solidpropellant reaction motor 8.8-inches in diameter and 22-inches in length.The motor shall provide 1750 2 32 pound-seconds total impulse in the minusZ direction, producing pitch about the Y axis in the minus Z direetionwhich shall provide lateral displacement. The rocket motor shall beignited by a pellet basket igniter wnich is initiated by two hetwbeigniter cartridges.3.2.1.4 Canard System.-consist of two aerodynamic surfaces, an actuating system, stops, and lockingdevices. The canard system shall be designed to orient the blunt end of thelaunch escape vehicle forward to minimize tumbling following aborts from thepad to approximately 8,500 feet. "he canards shall be hinged longitudinallyon opposite sides of the LE.5 ballast compartment.the winged surfaces shall remain flush with the LFS motor body and shallconstitute a portion of the upper cylindrical conical sections of theballast compartment.

The canard system shall be deployable and shal l

In the stowed position,The canard system is shuwn in Figure 2.

3.2.1.5 Tower Jettison Motor.- The tower jettison motor shall be a solidpropellant motor 55.6-inches in length and 26-inches in diameter.shall have two fixed nozzles canted 30-degrees from the mean motor centerline.The resultant thrust aJds shall be located approximately k-degrees plus orminus 30-minutes from the mean motor centerline of the pitch plane. Thejettison motor shall weigh approximately 534-poundsY (which includes theinterstage structure) shall develop 33,OOO-pounds force of thrust and shallfire for 1.2-seconds.igniter which is initiated by two hotwire igniter cartridges.

The motor

The rocket motor shall be ignited by a pyrogen type

3.2.1.6 Launch Escape Motor.-propellant motor with four nozzles nominally canted 35-degrees from the meanmotor centerline. The resultant thrust vector of 2-degrees 45-minutes plusor minus 15-minutes in the pitch plane shall be obtained by a difference intwo opposite nozzle throat areas.3200-pounds of solid propellant fuel and shall have a gross weight ofapproximately 48oepounds.515,000 LBF seconds total impulse. The average effective thrust developedduring the first 2 seconds of firing shall be approximately 155,OOO-pounds

The launch escape motor shall be a solid

The mobor shall contain approximatelyThe motor shall be designed for a minimum of

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Cforce at 36,000 feet altitude and 70 degrees Fahrenheit temperature. Themotor shall be ignited by a pyrogen type igniter which is initiated by twohotwire igniter cartridges. The motor shall have a burning time of about3.5-seconds at nominal thrust and 70 degrees F with burnout at 8-seconds.3.2.1.7 Structural Skirt.- A structural skirt assembly shall be utilizedto mount the launch escape motor to the tower.of a forged ring with longerons welded to a shear skin that shall transferuniform loads from the launch ercape motor to four points at the launchescape tower legs. The structural skirt shall be bolted to the LES tower.

The skirt shall be constructed

3.2.1.8 Launch Escape Tower.-legged, truncated, retangular cross-sectioned, pyramid structure of weldedtubular titanium alloy. The tower shall be 120-inches in length with abase 46-inches by 50 inches.between the CM and the escape, jettism, u d pitch control motors.bolts at the bottom of the tower shall attach the tower legs to the CM.

The launch escape tower shall be a four-

The tower shall form the intermediate structureExplosive

3.2.1.9to completely enclose the conical portion of the CM.the cover shall extend from the CM apex to station X, + 81 and shall beconstructed of hard honeycomb fiberglass with an outer layer of ablativematerial. The cover shall be used to demonstrate the dynamic effects andthe separation capabilities with the LES during an abort mission as definedin 3.3.1. The cover simulates the spacecraft cover in basic design, however,no provisions are made for the RCS orifices, window, or hatch provisions. Asimulated hard structure over the rendezvous windows are incorporated in thecovers. The individual covers shall be assembled in eight sections to allowaccess to the CM. The cover shall be attached with brackets to the LEStower legs and shall be jettisoned with the US. The boost protective coveris shown in Figure 3.3.2.1.10 LES Electrical System.- The LES electrical system shall consist ofthe following:

Boost Protective Cover.- The boost protective cover shall be usedThe forward part of

(a) U S electrical wiring harness(b) LES hotwire initiators(c) Launch escape tower sequencers

3.2.1.10.1 LES Electrical W i r b Harness.- Redundant wiring harnessesshall be bonded to the exterior of the launch escape motor and associatedredundant harnesses shall be integral to the tower structure. The wiringharnesses shall provide the means of connecting the rocket motor andseparation circuits with the sequence controllers and the tower sensorinstruments with the communications equipment.breakaway type plug that shall permit the harness to be detached at theseparation plane when the launch escape tower is jettisoned.

Each harness shall have a

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3.2.1.10.2 LES Hotwire Igniter Cartridnes.- The LES hotwire igniter cart-ridges shall be electroexplosive (pyrotechnic) devices which shall ignitethe launch escape, pitch control, and tower jettison motors.shall detonate the explosive bolts which tie the tower and CM together. Theigniters and firng circuits shall be redundant to ensure reliable activationof each function.

Similar devices

3.2.1.10.3 Launch Escape Tower Sequencers.- Two U S tower sequencers shallbe installed on the underside of the structural skirt. The sequencers shallreceive input signals from the mission sequencer and transmit electricalsignals in proper sequence to (1) detonate the launch escape tower - CMattachment explosive bolts (2) energize the launch escape and pitch controlmotors and the tower jettison motor by igniting the motor igniters and (3)to detonate the thruster squibs (signal to mission sequencer transmittedthrough 0.4 second time delay relay) to jettison the apex forward compart-ment cover. The sequencers shall provide circuits for mnitoririg thefunctional status of critical control circuits by GSE during checkoutoperations. The sequencers shall be totally redundant for reliability.3.2.1.U. LES Pmotechnic System.- The U S pyrotechnic system shall consistof the following major components and shall be redundant to ensure reliableactivation of each function:

(a) Pyrotechnic batteries(b) Electrical wire busses(c) Hotwire initiators

3.2.1.11.1 Pyr technic Batteries.- ?he four pyrotechnic batteries (2each,backup) located in the CM, shall be the power source for supplying dc currentto the pyrotechnic devices.3.2.1.11.2 Electrical Wire Busses.- "he electrical wire busses incorporatedin the w i r i n g harness, shall transmit current from the pyrotechnic batteriesto the low resistance hotwire initiators.3.2.1.ll.3 Hotwire Initiators.- The low resistance hotwire initiatorsshall ignite the launch escape, pitch control, and tower jettison motorsand detonate the explosive bolts which tie the tower and CM together.3.2.1.12 U S mbilical System.- The U S umbilical system shall providemeans by which the LES and CM are linked electrically.connectors shall join the LES-CM electrical systems.be located in the LES-CM separation plane adjacent to an escape tower leg

Two electricalThe connectors shallwell in the CM forward heat-shield. -The receptacle portion of theshall be attached to the nearest tower leg by a lanyard. When thetower separates from the CM, the lanyard shall pull the plugs fromreceptacles.

co me torescapethe

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3.2.l.l3 IES R and D Instrumentation.- The IES R and D instrumentationshall consist of the follcrwiag:0

(a) LES Q-Ball(b) Accelerometers(c ) chamber pressure transducers(d) IES camera system

Data acquired by the measurement devices shall be transmitted t o the R and Dtelemetry equipent by means of the electrical w i r i ng harness for trans-mission t o the ground sta tio n. Measurements s h a l l also be obtained froon thetuuer sequencers.Number 23A (see Section 6), for list of measurements and sensor locations.The component description and function al opamtfon of the !&E& sssak~lyi s described i n 3.2.2.5.4.

Refer t o Apollo baauramnt Requirennents Boilerplate

3.2.l,l3.l U S C y ystem.- The IES tower camera gJrstam consists of acamera (with lens , rotective case, control unit with i ne r t ia switchactivated time delay mechanism, timing generator u n i t , battery power supplyand intercon necting el ec tr ic al CabUng. Bracketry for mounting the cameraassembly sh a l l be *shed.The 16nrm high-speed cine camera sha l l be hcrusd i n a protective case mountedon the IES tower s t ruc tura l ring, viewing damward.the CM protective boost cover and IES engine flame impingement, and LESt c m e r / C M separation sequence. System functions shall be sequenced by acontrol unit, start i n i t i a t i on by inert ia switch activated delay timingmechaniam.

The camera sh a l l view

3.2.1.U, IES Tower - CM Separation System.- The IES tower - CM ssparationSgstem contains four explosive bolts that secure the tower t o the CM. Hot-w i r e i n i t i a t o r s shall supply th e current necessaq t o detonate the explosivedevice, which effect release of. the tower. The hotwire initiators shall beenergismd by positive ;?&volt dc signals received fromthe tower sequencersthrough the IES-CMumbilical.escape tcmar jetti so n, th e tower sequencers shall simultaneously applydetonation s i g n a l s t o the separat ion s y s t e m hotwire initiators and energizeth e igniters of the launch escape and pitch control motors.sha l l be parted by force on the laqmxbtype disconnects when the separa tionoccurs, ash th e tower assembly sh al l be propelled c lea r of the boi lerp latetra ectorg.

To accomplish IES-CM separation and launch

umbilical cables

3.2.2 Canand Module.- The CM sha l l consist of t h e follcming:(a ) CM s t ructure

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C

(c) Electrical power system (EPS)(d) Abort sequencer(e) R and D conmnUrications equipnent(f) R and D instrumentation

3.2.2.1 Command Module Structure.- 'Ihe CM shall be of conical design,approximately 135-inches high and 154-inches i n diameter at the base witha weight of approximately ll,OOO pounds (on launch pad). The structureshall be fabricated from aluminum with a skin thickness of approximately0.190-inch. Cork insulation shall be applied to the exterior s k i n of theCM as required to protect the aluminum s k i n of the CM as required fromcritical temperatures during boost and abort. Attach fittings shall beprovided at the forward buikhead to engage Yna h i m h escape t m s r .configuration of the CM shall be similar to the ultimate spacecraft CM.The CM structure shall include the following:The

Cabin housing(1) Forward bulkhead and egress tube(2) Forward crew compartment(3) Aft crew compartmentHeat shield structureSeparation systemCabin Housing.- The CM she3 s,.al l be constructed of aluminumalloy welded into two subassemblies, (1)the formud crew compartment and(2) the aft crew compartment. The subassemblies shall be bolted togetherand the aft skirt frames and skin shall be attached by mechanical fasteners.

3.2.2.1.1.1 Forward Bulkhead and Egress Tube.- The forward bulkheadstructure shall consist of a double skin with riveted stiffeners. Thecloseout sk i n shall be attached to stiffeners by blind fasteners. Theegress tube shall consist of a welded sheet tube of aluminum welded tothe forward bulkhead. A cover plate shall be bolted to the top of theegress tube.

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3.2.2.1.1.2 Forward C r e w Compartment.- The forward crew compartment sh a l lco ns ist of multi-s tiffener s welded t o the ou ter skin. The st iff en ers sh al lco ns is t of four main longerons attached t o th e launch escape tower fittingsi n the forward bulkhead and terminate i n th e mid-ring sp li ce j o in t a t thea f t end of the forward section of the crew compartment. Sev er al secondarylongerons s ha ll be uti l iz ed f or load tr an sf er from the forward bulkhead t oth e mid-ring. 'Ihe remaining st if fe ne rs sh a ll assist the skin in resistingairloads.3.2.2.1.1.3sh al l consis t of a sidewall with sti ffe ne rs, corresponding t o those of theforward section of the crew compartment, from the mating af t sec tion of th ecrew compartment mid-ring t o the machined ring forging a t the junction ofthe sidewall and the floor.

A f t Crew ComDartment.- The a f t section of t h e crew compartment

3.2.2.1.2 Apex Forward Corn-wx=tiaefit He& Shield Cvrer;- The apex forwardcompartment hea t sh iel d cover st ructu re s h a l l form th e forward s ec tio n ofthe CM structur e and s ha ll consist of an aluminum allo y skin and st i ffe ne rsut il iz in g riveted and bolted construction. A l i gh t weight inner skin sha llbe used t o ensure a smooth surface so t h a t the forward compartment covers h a l l not i nt er fe re with th e parachute bags or equipment upon ejection."he cover s h a ll be jettiso ned 0.4 seconds after tower separation.nose cone s h a l l ab aluminum.3.2.2.1.2.1 Apex Forward Compartment Cover Heat Shield Attachment.- Theapex forward compartment cover heat sh iel d s h a l l be fastene d t o the CMs t ructure by two tension bolts located a t the launch escape tower legfittings.connected i n diagon ally opposing pairs thrusting against free piston rodst h a t are attached t o the upper ring of the heat shield.thrus te rs i s connected t o an independent gas pres sure source consi sting ofa breech and an ele ct ri ca ll y in it ia te d gas producing cartridge.

The

Separation w i l l be obtained by four thrusters (e jectors) inter-Each pair of

3.2.2.1.3attached a t the space craft ablativ e mold l i n e and sh a l l form the outer,blunt s ection of th e CM.sh a ll be fab ricated of gla ss cloth laminations with an aluminum honeycombcore sandwiched between inner and outer surfaces. "he heat shie ld sh al l bemounted to th e CMlower str uc tu re ring by four at tach fittings installed onthe heat shield inner surface.design) shall be ins tal led through the heat shield f o r positioning on thepad adapter (U-013).

Aft Heat Shield.- The a f t compartment heat shield s h a l l beIt s h a l l simulate the spacecraft heat shield and

Six hard compression pads (b al l and socket

3.2.2.1.3.1 Access Hatch.- The main hatch sh al l provide access t o t h e CMi n t e r i o r . The hatch shall be constructed of reinforced aluminum plate ands h a l l be bolted in to place. I t sha ll be located i n the CM sidewall over thehead of the center couch position.

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3.2.2.1.3.2 Access Doors.- Access doors s ha l l be provided in t he sk i r tstructure for servicing the heat shield attach struts.be provided in th e forward crew compartment st ru ct ur e, approximatelySO-degrees apart, for telemetry antennas.Four openings shall

3.2.2.2 Earth Landinn System (Em).- he ELS s ha l l cons ist of an EL5sequencer and a parachute subsystem, and s h a l l be located i n the apex forwardcompartment around the egress tube,3.2.2.2.1 E I S Sequencer.- The ELS sequencer shall control dual drogueparachute deployment, dual drogue parachute disconnection, and p i lo t para-chute deployment. The E I S sequencer s h a l l con sis t of relays , baroswitches,and timing devices.3.2.2.2.2 Parachute Subsgatem.- The CM s ha l l be equipped with a parachutesubsystem designed t o decelerate anci safe iy land Q CX xeighhg zp tg ll.,NM-pounds (af ter eje ct io n of th e apex fornard compartment cover and chutedeployment) following mission abort. The subsystems sh a l l co ns is t of:

(a) Two drogue parachute systems(b) Three main landing parachute assemblies, including pilotparachute systems(c) A vehicle harness assembly

3.2.2.2.2.1 Drogue Parachute System.- Each drogue parachute system sh a l lconsist of one each of the following:(a) Drogue parachute(b) Drogue parachute deployment bag(c) Drogue parachute mortar assembly(d ) Drogue parachute r iser(e ) Drogue mortar pgrotechnic ca rtr idges .

3.2.2.2.2.1.1 Drome Parachutes.- l k o dual-conical-ribbon drogue parachutess h a l l be mortar deployed reefed for eight seconds, then disreefed.parachute s ha ll be 13.7 f ee t i n diameter and w i l l exert a maximum t o t a lload of 20,000 pounds on the CM.

Drogue

3.2.2.2.2.1.2 Drome Parachute Deplo-went bg.- The drogue parachutedeployment bag s h a l l enclose and pro tec t the drogue parachutes and ri s e r swhile contained i n the drogue mortars and during ejection. The deploymentbag s ha l l cont rol the parachute and ri s e r s t o insu re orderly deployment ofthe parachute into the airstream.

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3.2.2.2.2.1.3 Drome Parachute Mortar Assemblies.- The drogue parachutemortars shall contain a drogue parachute and riser packed in a deploymentbag, and shall eject the package into the airstream to provide positivedeployment of the drogue parachutes.3.2.2.2.2.1.4 Drome Parachute Risers.- The drogue parachute risers shallbe of sufficient length to place the drogue parachute in a favorable position,with respect to the airstream around the CM.3.2.2.2.2.1.5 Drome Mortar Pyrotechnic CartridRe.- Drogue mortar pyro-technic cartridges shall provide the necessary propulsive force to ejectthe drogue parachute package a sufficient distance to provide fu l l deploy-ment of the drogue parachute.3.2.2.2.2.2 Drome Disconnect Assembly.- The drogue disconnect assemblyshail connect the drogue parachxte risers to the CM.shall release the drogue parachute risers upon the signal from the sequencercontrol system.

The disconnect assembly

3.2.2.2.2.3 Main Landing Parachute Assembly.- The main landing parachuteassembly shall consist of three pilot parachute systems and three mainparachute pack assemblies.3.2.2.2.2.3.1 Pilot Parachute System.- The pilot parachute subsystem shallconsist of the following:

(a) Pilot parachute(b) Pilot parachute deployment bag(c) Pilot parachute mortar assembly(d)(e) Pilot parachute risers

Pilot parachute mortar pyrotechnic cartridges

3.2.2.2.2.3.1.1 Pilot Parachute.- The pilot parachute shall be capable ofextracting and deploying main parachute.3.2.2.2.2.3.1.2 Pilot Parachute Deployment Bag.- The pilot parachutedeployment ,bag shall contain and protect the pilot parachute prior to, andduring ejection from the pilot mortar.ment of the pilot parachute riser and pilot parachute.

They shall also control the deploy-

3.2.2.2.2.3.1.3 Pilot Parachute Mortar Assembly.- The pilot parachutemortar assembly shall contain and eject the pilot parachute upon s i g n a lfrom the sequence controller.

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3.2.2.2.2.3.1.4 Pilot Parachute Mortar Pyroteclm5.c Cartridges.- The pilotparachute mortar pyrotechnic cartridges shall provide the propulsive forcenecessary to eject the pilot parachute and riser from the mortar to adistance sufficient to a l l o w the pilot parachute to inflate and deploy themain parachute.3.2.2.2.2.3.1.5 Pilot Parachute Riser.- The pilot parachute riser shallretain the pilot parachute during deployment and operation.shall be of sufficient length to place the pilot parachute in a favorableposition with respect to the airflow around the CM.

The riser

3.2.2.2.2.3.2 Main Parachute Pack Assembly.- The main parachute packassembly shall consist of three main parachutes contained in separate packs.Each pack assembly shall consist of the following:(a) Ope main parachute(b)(c) One main parachute riser

One main parachute deployment bag

3.2.2.2.2.3.2.1 Main Parachute.- The main parachute shall be designed tooperate in a cluster of three parachutes and to comply with the performancerequirements of Boilerplate Number 23A. Dual reefing systems, each consist-ing of one reefing line and three cutters shall be incorporated in each maincanopy to reduce the probability of premature disreef, Consideration shallbe given to possibilities of inadvertent arming during parachute packing,3.2.2.2.2.3.2.2 Main Parachute Deployment Bag.- The main parachute deploy-ment bag shall contain and protect the individual main parachute and riserp r i o r to and during extraction from the CM and shall ensure orderly deploy-ment of the parachute and riser.3.2.2.2.2.3.2.3 Main Parachute Riser.- The main parachute riser shall beof sufficient length to place the individual main parachute in a favorableposition With respect the airflaw around the CM.3.2.2.2.2.3.3 Main Parachute Pack Retention Flap.- The main parachute packretention flap shall retain the main parachute and vehicle harness prior todeployment.3.2.2.2.2.3.4 - The vehicle harness assemblyshall attach to the four parachute attach fittings on the CM forward egresstube and extend to the main parachute confluence assembly.from the parachute attach fitting plane to the confluence assembly shall be70-inches measured along the centerline of the harness assembly.assembly shall allow the CM to land at S-degrees plus or minus 0.5-degreefrom the vertical.

The distanceThe harness

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The 120-ampere hours ba ttery will be connected t o ins tru-Two 5-ampere hours ba t te r ies w i l l be connected

3.2.2.4 Abort h ts s io n S8auencer.- The abort/mission sequencer s h a l l providea sequenced abort mode that shall be in i t i a ted while Bo ile rp lat e Number 23Ai s on the launch pad.abort hot line relays, pyrotechnic fir in g relays, and time delay relessnecessary t o provide the functio n required fo r th e abo rt mission.sequenced events s h a l l be a s follows:The sequencer shall include abort lockout relays,

The

(a ) Abort lock-out rela y activate1. I S ogic busses armed2.3. LES ~rgro usses armed

(b ) GSE pre-launch arming s i g n a l s

Activate abort hot line relay

(c) Lift-off1. Abort lock-out rel ay deact iva ted2.3.4.

Abort hot line relays deactivatedLES logic busses activated (abort init iated)Launch escape and pitch c ont rol motors fi re d

(d ) Canard deployment(11 seconds after sbort in i t i a t ion)

(e) LE3 and BPC j e t t i son(3 seconds after canard deployment)

(f) Forward heat shield jettison and E I S pyro bus armed(0.4 second a f te r U S e t t i son)

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(g) Dual drogues deployed(2 seconds after U S jettison)

(h) Drogues released, pilot parschutes deployed extracting thethree main parachutes(12 seconds after drogue deployment)

3.2.2.5 Research and Development Communication (R and D) Eauipment.- TheR and D equipment shall provide a means of acquiring data pertinent to themission of Boilerplate Number 23A.tape recorders and FU? telemetry transmission.Equipment Block Diagrq.Acquisition will be by means of on-boardRefer to Figure 4 for R and D

3.2.2.5.1 RF Electronic Eouipment,- The RF telemetq equipment for Boiler-plate Number 23A shall consist of an IRIG PAM/FM/FM system containing apower supply, sixteen subcarrier oscillators, one 90 x 10 commutator, onemixer, one transmitter, one five point calibrator, one RF power amplifier,and an antenna system. The telemetry transmitter will have a total paveroutput of 10-watts.3.2.2.5.2 Data Eauipment.- The primary data gathering device shall be anonboard tape recorder. In addition to recording 90 x 10 commutator infor-mation and a l l T/M continuous channels, those measurements requiring high-frequency response will be tape recorded. The tape recorder unit willconsist of a tape recorder and tape recorder electronics and a remote controlbox. Capacity w i l l be 750-feet of 1-inch tape operated at 15-IF'S withapproximately 10-minutes recording time.3.2.2.5.3telemetry antenna system.Antenna Equipanento- The R&D antenna system shall consist of a

3.2.2.5.3.1 Telemetry Antenna System.- The R& D telemetry antenna systemshall consist of four slot antennas. These antennas shall be located justbeluw the separation line of the forebody apex section of the CM and. shallbe spaced approximately SO-degrees apart.3.2.2.5.4 &-Ball System.- Three differential pressure transducers withassociated attachment fittings an d electronic w i r i n g shall form the NAA/S&IDfurnished Q-Ball system. Data acquired fromthe Q-Ball shall include angleof attack, angle of sideslip, and dynamic ram pressures.shall be located in the LES nose cone and shall sense airflow direction andpressure through ports in the nose cone surface.approximately 28-Lvolts dc.with conversion of input power to 8-kilocycles.

The transducersThe input voltage shall beThe transducers shall be capacitive-balancedThe output of the

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transducers will be proportional t o the three dif fer en tia l pressuresmeasured.ment a f t e r amplifica tion and coversion of t he o utputs t o dir ec t current.The transducer outputs ui l l be applied t o t he telemetry eqyip-3.2.2.6 R&D Instrumentation.- A telemetry system shall provide means ofdata acquisi t ion from Bo il erpl at e Number 23A during flight.stat ion will be positioned on t h e ground f o r the f l ight ,system will be used f o r tel em etry cnmmunications.i n s t a l la t i on fo r t he CM i s shown in Figure 1.

A telemetryA PAM/FM/FMT e l e m e t r y antenna

3.2,2.6.1 RgeD Instrumentation Esuipn nt.- The in st ru ma ta ti on and ins tm-ments will consist of, but not be llmited t o , accelerometers and pressuretransducers. These signal conditioning devices will shape the informationreceived f rom the sensors in to a modulation voltage f o r the subcarrierremotely calibrated f o r both R (range -85 percent full scale) and Z$Zerooscillators. The amplifier portion w i l l have the capability of be=l5 percent Full S C ~ ~ S ] ; efer to the Apo l lo Measurement RequirementsBoilerplate 23A (see Section 6) , f o r sensor locations.3.3 Performance.- The IES will l i f t the CM off the pad adapter andtranslate the CM t o a safe distance from the launch area.IES sh al l permit a l l res ult an t motion t o be within the U t s of humantolerance and provide sa ti sf ac to ry conditions f o r the depluyment of th erecovery ssytem.

Design of the

3.3.1 Launch Abort Mission.- The f l igh t plan f o r Bo ilerpl ate Number Z3Ash al l consis t of (1) abort fram launch pad, (2) IEV turn-around, utilizingcanards, (3 ) LES and forward heat shield je ttis on , and (4) recovery systemoperation.Boilerplate Number 23A will be launched from the White Sands H s s i l e Rangea t appmdmately 4OOO-feet above mean sea level. The f l ight path will bet o th e North with a launch elevation angle of 9Me gree s, fo r a distance ofappraadmately 5ooO-feet. The IEV shal l consist of a spacecraft XZS and eBoilerplate CM. Theabort shall be ini t ia ted by a land I lne s i g n a l from th e blockhouse t o t heabort re-,operations, and will be deenergised during the countdown.S ~ ~ ~ ~ W O U S ~ ~gnites the launch escape and pitch control motors.

A special adapter will be used as a base f o r the T,Abort enable GSE w i l l lockout this s ignal during grouadThe abort signal

Eleven seconds after abort ini tia tio n, the canards will be deplqed causingIEV turn-around t o a main (aft) heat shield forward at ti tu de. The apogeeof t he trajdctory will be about 8,000-feet above mean sea level reference.The 24,OOO feet and 1,OOO feet barcmetric switches will be closed out duet o the al t i tude; therefom, three seconds af te r the canards are deployed,the IES nclud ing the BFC, will be jettisoned by the tower jettison motor.Four hundred milliseconds (0.4) af te r IES jet tis on , th e apex cover thrusterswill be fired, thereby jettisoning the forward heat shield.

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Reefed dua l drogue parachutes w i l l be deployed two seconds a f t e r LESje t t i s on t o s tabi l ize and decelerate the CM f o r main parachute deployment.The drogues w i l l be di sree fed eight seconds af t e r deployment. Four secondsa f t e r disreefing the drogue parachutes w i l l be released, and simultaneouslythe three pilot parachutes w i l l be deployed.w i l l extract the three main parachutes, which w i l l be inf la ted in the reefedcondition t o reduce opening shock.main parachutes w i l l be disreefed and fu l ly inf la ted t o es tab l ish a descentr a t e of 27 f e e t per second prior t o touchdown.approximately 1.5 minutes af te r abort in it i at i on .

0

The pilot parachutes i n tu rnEigh t seconds af ter l ine s t retch, the

Landing w i l l occur a t

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4. Q U A U T Y ASSURANCE04.1 General Quality Assurance Pr0vlsions.- The cont ractor ( N A A / S&l D )shall be responsible for the performance of all inspection requirementsas spe cif ied herein. Except as oth md se specified, the contractor mayu t i l i z e his cmn or any other inspection fa ci l i t i es and services acceptablet o NASA.ccnnplete and avirilable t o NASA as specified i n the contract.Inspection records o f t h e examinations and tests sh al l be kept4.2 Contractor's Quality Assurance proRI.am.- The contractor sh al l esta blisha qu al it y assurance program i n accordance wi th th e requirements of paragraph6 of Exhibi t 1 f the contract .formance of Boilerplate Number 23A to contract and specification requireslentssh al l be conducted prio r t o submission of the a rt ic le t o the NASA f o racceptance.4.2.1 Reliability Data.- The contractor 8hall ac t as a t e s t h i s t o r i a n andaccumulate applicable data on spacecraft tests, pians, and performance i r a npreparation t o delivery. The data shal l be used i n qual i ta t ive and qyanti t iveassessments of re l i ab i l i ty and performance of each syfstan, and of the ultimatespacecraft.ance data, sha l l integrated with that accumulated from prior t es t s t o formassessments. Thus, a probabil i ty of success may be provided fo r any givenphase.order t o assure that these have been attained.4.3 &amination.- Each assembly and a l l major ccunponents submitted f o racceptance shall be subjected t o a visual examination t o d e t e m h e con-formance t o materia ls, design, construction, dimensions, color and f inish,product marking, and workmanship.

Inspections and t es t s t o determine con-

This data, togethe r with other appropriate data, such as accept-The re li ab il i t y data may also be cmpared with program objectives i n

(See paragraphs 2, 4.1, and 4.2).4.3.1 Capnp0nents.- The cont rac tor sh a l l asce rtain th at , pr io r t o assembly,a l l parts, ccunponents, assemblies, and systems procured under separatespecifications or drawings have been inspected, tested and accepted i naccordance with their respective specifications or drawings.4.4 Tests.- Each assembly, major cmponent, and system submitted foracceptance sh al l be subjected t o performance t es ts .interference control i s defined i n the Electramagnetic Compatibility Testfor Boi lerplate Number 23A (see Section 6).

The electromagnetic

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5.1 andpackinR.- hservat ion, packaging, andpa- provisions s h d l not be applicable fo r Boilerplate Number 23A.6. NOTES6.1 Reference Documents.- The following documents are intended f o rinfomat ion plrposes only ami do not const i tute a part of this specif icat im.

SID 63-57416 April 1965sm 65-29-119 March 1965

SID 62-22328 Ncrvssnber 1962MAO201-054321 July 1964

A p l l o Measurement RequirementsBoilerplate Number 23AVehicle Test F'lan, Apollo Mission

Actual, Weight and BalanceReport, Boilerplate Stack No. 23APA-2 (BP23A)

Apollo Program PlanElectromagnetic CaanpatibilityTest f o r Bo iler pl ate Number 23A

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XL 399.668PITCH CONTROL MOTOR CANARD SYSTEM(DETAIL: SEE FIGURE 2)

TOWER JETTISON MOTOR

LAUNCH ESCAPE MOTORSTRUCTuWi SKiRi

XL 120.0IMLES TOWER 8, C MINTERFACE SEPARATION

BOOST PROTECTIVECOVED

1 X c 132.0EARTH LANDING SYSTEMFORWARD HEATSHIELD

XA 1083.476X c 83.476ORK/INSULATION xL o.oI\ .TELEMETRY ANTENNA

(DETAIL SEE FIGURE 3)

HEAT SHIELD (GLASSCLOTH LAMINATED)PAD ADAPTER

Figure 1. Configuration, Boilerplate No. 23A.

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a

Figure 2. Canard System

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