BEST COPY 

AVAILABLE 

Approved for Release: 2018/11/16 COS11480S 

111111111111111111111111111 14 1111111111111 

--'------'-'=--

.'f<. 

',"'., MANUFACTURER'S MODEL SPECIFICATION 

<. ' .. '.:/ ~ 

Clarence L. Jo 

Vice Pre s ident 

Advanced Deveiopment Projects 

PACL'i A;+fU(t; .. -........ _<._ .... -.. ~.-.. ,.-'--':-'" .. -~ ... --... ---.. ,.,. , ..... - ." .. ,,--.... ----.----.~-. 

Approved for Release: 2018/11/16 COS11480S 
Approved for Release: 2018/11/16 COS11480S 

TABLE OF CONTENTS 

1 . 0 Scope ar:.d elas s ificatbn 

2.0 Appllcable Spec ilicat ions, Other 

Publications, and Drav. tng s 

3 " .U Requiren,ents 

3. 1 Characterisi ks 

3. 1. 1 Configuration 

3.1.3 Mission Requirerncnt 

3. i. 4 Li.fe 

3.1. 5 Weights 

3. 1.6 Cente: tJf Gravity Location 

3. 1. 7 Ji. reas 

3. i. 8 Din;ens ions and General Data 

(\V eight Staternen~) 

3.2 General 

3.2.1 General L:terior A::'ran2,ement: 

3.2.2 Materials 

3.2.3 \Vorkrnanship 

3.2.4 Prod:'lctioil, Mab~.ellajJce and ReL~ai::: 

3.2.5 Interchangeability and Rc:)laceabi1i~y 

3.2.6 Finish 

3.2. 7 Identification and Mar1dng 

3.2.8 Extreme Temperature Operation 

3.2.9 Ground Climatic Requiren:ents 

3.2.10 Lubrication 

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3.2. 11 

3.2.12 

3.2. 13 

3.3 

3.3. 1 

3.3.2 

3.3.3 

3.4 

3.4.1 

3.4.2 

3.4.3 

3.4.4 

3.4.5 

3.4.6 

3.4.7 

3.5 

3.5. 1 

3.5.2 

3.5.3 

3.6 

3.6.1 

3.6.2 

3.6.3 

3.6.4 

Approved for Release: 2018/11/16 COS11480S 

TABLE OF CONTENTS 

(Contd) 

Standard Parts 

Crew 

Equipment Installation 

Aerodynamics 

General 

Stability and Control 

Jettbon 

Structural Des ign Crite !:'ia 

General 

Maximum FliJht Desig:1 Gross INeight 

Landing Design Gross Weight 

Limit Flight Load Factors 

Lin--lit Landing Load Factor 

Lin1i.t Speed 

Lin-;'it Taxi and Ground Handl ing 

Load Factors 

\V i.ng Group 

Descripti.on and Components 

Construction 

ELevons 

Tail Group 

Description and Components 

Construction 

Rudder 

Ventral Fin 

________________ ~A:J:p~p ___ ro ___ v_=e~d for Release: 2018/11/16 COS11480S 

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~age 

10 

10 

10 

13 

14 

14 

14 

14 

14 

14 

14 

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15 

15 

15 

16 

16 

16 

16 

17 

17 

17 

17 

17 
3.7 

3.7.1 

3.8 

" r; J . " , 

3. 'j. 1 

3.9.2 

3.9.3 

3.9.4 

3. t). 5 

3. 10 

3. 10. 1 

3. 10.2 

3. 10.3 

3.10.4 

3. 10. 5 

3.10.6 

3. 10. 7 

3. 11 

3.11.1 

3.11.2 

3.11.3 

3.11.4 

3.11.5 

3.11.6 

Approved for Release: 2018/11/16 COS11480S 

Body 

Fuselage 

Ai ightiag Gear 

TABLE OF CONTENTS 

(Contd) 

Surface Control System 

Primary Flight Control 

Secondary Flight Controls 

Lift and Drag Increas ing Devices 

Trim Control System 

Automatic Flight Control System 

Engi.ne Section 

De scription and Components 

Construction 

Engine Mounts 

Vibration Isolators 

Firewall 

Coviling and Co'\vl Flaps 

Access for Inspection and Maintenance 

Pl."opuls ion 

General Description and Components 

Auxiliary Propulsion Units 

Engine-Driven Accessories 

Air Induction System 

Exhaust System 

Engine Compartment Cool ing 

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SP-1214 

Page iii 

Pa~e 

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17 

18 

18 

18 

19 

19 

19 

19 

19 

19 

19 

19 

19 

10 

L I 

19 

19 

20 

20 

20 

20 

20 

20 

20 
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TABLE OF CONTENTS 

(Contd) -

3. 11.7 Luhrication System 20 

3. 1 ~. 8 Fl..:el System 20 

3.11. 9 I.L;nition System 23 

3.12 Auxiliary i.JO\;.er Uidt 23 

3.12.1 Descri:,tion ane Con'ijJone:lts 23 

3.12.2 Ram Ail' Tm'i.'ine 23 

3. 13 Electric Sy"tcm 23 

3. i3. 1 Descrirtioll - ?ower SO'.\l'ce 23 

3. l3. 2 Eatteries 24 

3.13.3 Receptacles 24 

3. 23.4 Eq!lipmc;1t hstaUati::m 

25 

3. :.3. (;. P.ol1cHng 

3.,;3.7 Controls 25 

3. 13. 8 Light ing 25 

3.13.9 I:.;;niLion System 25 

3.13.10 bdi.cators 25 

3.13.11 Electric D:dves 25 

3. 1 3. 12 Relays 25 

3.13. 13 Booster Coil 25 

3.13.14 Filters 25 

3.14 Hydraulic System 25 

3.14.1 Description and Components 25 

3.14.2 Emergency Hydraulic System 27 

________________ ~A~p~p'_'ro~v_'"'e~d~fo':"r__'R~e""':'lease: 2018/11/16 COS11480S 
3.15 

3.15.2 

3.15. 3 

3. 16 

3. 16. 1 

3.16.2 

3. 16. 3 

3.16.4 

3. 17 

3. 17. 1 

3.17.2 

3.17.3 

3.17.4 

3.17.5 

3. J.8 

3. 19 

3.20 

3.21 

3.21. 1 

3.21.2 

3.21.3 

3.21.4 

3.23..5 

3.22 

Approved for Release: 2018/11/16 COS11480S 

TABLE OF CONTENTS 

(Contd) 

Pneumatic System 

Ground Cooling 

Anti-Ie bg Provis ions 

Utilities and Eqllipmc:lt Subsystems 

Instrurnents 

Furni.shings 

Oxygen System 

Emergency Rescue 

Communi.cations, Navigation, and 

Guidance 

Communication Equit)ment 

Navigation Equit1ment 

Autopilot 

Tel.emetry 

Antenna bstallations 

Reconnais sanee Systern 

Fire Control System 

Arrl1ament System 

Ground Handling and Servicing Provis ions 

Tow ing Provis ions 

Jacking Provi.sions 

Mooring Provisions 

Hois tingProvisions 

:r:vleasuring and Level ing Provis lons 

Aerial Refueling System 

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27 

27 

27 

27 

27 

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27 

27 

28 

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28 

28 

29 

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4.0 

5.0 

6.0 

6. 1 

6.2 

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TABLE OF CONTENTS 

{ConLd} 

Quality As surance Provis ions 

Preparation For Del ivery 

Notes 

Intended Use 

Revi.sions 

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Page 

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sp- :214 

Page 

AIRCR.f\F'T - RAMJET - HIGH ALTITl:DE - RECONNAISSANCE 

1.0 SCOPE AND CLASt:IFICATION 

1..1. Tll10' spe\.i,·k:ati.on coven' the follo\. ing aircraft: 

Service 1/10de1 De:~i.:'.naLi<)n 

De~· igncrf' Name 

Muc:e 1. 1'e f igna! Lm 

NUlnber and 1. lace!,' for ere,-'. 

Nltn,ber and Kind of E:n:4i:1es 

Ra et.P. (;-1 ica:)ic ::;l'OC 

Booster 

- Reconnaissance 

- Lockheed 1', i.rcra£t Corporation 

- D-2 'B 

None 

- One; RJ -·13 Rarujet 

Model MA2CiS-4 

(1\,k c: if L: a; i [) n of MA - 1 ~ ) 

- MIL-E-82l ' 

- unc; Solid r'ro, cHant Rocket 

:Motor Ll~C Model A'·2 

2.0 AU1-'LIC;\BLE SlECIF'IG.l''.TIONS. OTHER I·UBLICATIONS. 

AND DRA'v\ INGS---

1he fclL>\\ bg t,UIJU a-L,ns. \' ilh da CE <lc, listcd below, form a 

,Jan ()f 'he 5,.e' Lka:iun. 

2. 1. 1 

2. 1. 2 OthcrF'ublir-a: hns* 

"Hancbook of In~;tr rctioYl;-: for Airtla'le De~'i~ner:::" -

BrAD Tench EdLion 

3.0 REQUIREMENTS 

3. J CharacterLti.cs 

<~ , i -" • .l .. ,_ Configurat ion - (See Ge;ceral Arranuerlent dl'awins') " u 

3.1.2 PerrOrl:,ance 

3.1. 2.1 Guaranteed t'erfornjance -

Perforrr;ance data are guaranteed for the design mission. 

~The<'e d')Cl'D,ents arc H;ade ,arl of this S[,edficalion and are coml~lied \',ith 

to the eXlent ,.ern i!.ied by the radical nature of this vehicle and its 

in~ended n.is~iun. 

Approved for Release: 2018/11/16 COS11480S 
3.1.2.2 

3.1.2..3 

Approved for Release: 2018/11/16 COS11480S SP-1Z14 

Page 2 

Perforn:ance Curves 

The pcrf(>l'l~)anCe s;;ccified herein if' based on the folL'Jwlng atmospheric, 

fllel, and en~;ine chai:acteriELic G. 

A trno 8" he 1"C: 

FueL 

Engine: 

Booster: 

:Coost Phase: 

Free Fli:,;ht: 

Recovery: 

ARDC Model Atncosr,here defiaed in AFCRC TR-5'}-267 

PW A S23C Hydrocarbon Fuel 

Heating Vallte l' • h "OoF {y Cl'; t. at ) 

18,900 BTU/Lb. 

6.6 Lbs. / Gal. 

Engiac :t\,1a.nufactllrer's S[lec ideation 

ASD 1\.-(,3-1 forrns a [)art of this sveci.fica;ion. 

Maxir:lLlm thrust at 85,000 feet altiLlde at 

Mach 3.3 at 76% inlet recovery:: '., 70t) lb8. 

Speciik il.el consun-,ption at 85,000 fee: 

aLi:ude at Mach 3.3 at 76% ialet recuvery :: 

2.08 10. /Hr. Itb. thrust. 

LocLheed Report DP-l 'fAvanti Booster 

Speci:'ication" Lll"mS a part of thi.s sl-,eciiicatioll. 

The D-21B is la~mched froni a B-5ZH carrier 

a ire raft. 

Lal.lt1ch Alt:Ltiltle 

Launch Mach No. 

Final Boost Alti.~IHle 

Final Boost Speed 

FinaL Boost Mach No. 

InitiaL Cruise Altitclde 

F bal Cn: is e All it~de 

Speed (Constant) 

Range 

40, 000 Ft. 

.80 

80,000 Ft. (Nom. ) 

370 KEAS (Nom.) 

3.4 (Nom.) 

80, 000 Ft. 

(}5, 000 Ft. 

Mach 3.3 

3,000 N. M. 

The ~)ayload is jet' isonable, a:1d i.s recovered by 

a rr,odiHcat iun of an cxi::;~ing , t)arachute and 

snatch" systew. A JC-130B is used as the 

recovery aircraft. The ,'ayload parachllte is 

installed in a f'ui,able COl'L~}artnrent adjacent to 

the l-,ayload. 

Approved for Release: 2018/11/16 COS11480S 
3.1.4-

3. 1.5 

3. J.. 6 

3.1.7 

Approved for Release: 2018/11/16 COS11480S 

SP-1214 

Page 3 

Life - The origi.nal deeign life of t".;!enty-five hours at elevated 

~l-.eratues '.vas governed by electrical and hydradic components. 

I:1 order to i~reeerve these COU,;)O:1entf:' during n;ated Hi;ht an 

auxi.liary [iO\.er unit (RAT) be i.nstalled i.n the nose of [he boostel' 

and this unit provides electrical ano hydraulic poy:er to the D-21B 

during the extended carry out il ight S. Th~l6 the high speed (M :: 3.3) 

life of the D-21B is Etill tv:e;'lty-[tve hours. The D-21B ai.rframe 

fatigue Life for mated flights if. at least ten til-nes this figure. 

Vi eights - (:':,ee follovi ing tabulations) 

3.1.S.l GrossWei;;ht 

3. j 5.2 Zero Fuel Vo/ eight 

3. L 5. 3 Booster Gross Weight 

3. 1. 5.4 Total Launch \\/ eight 

C~nte r of Gravity Location -

3. 1. 6. 1 Vi ith B 008 te r 

Forward Limit 

Aft LinJit 

3. 1.6.2 At Booster Burnout 

3.1.. 6. 3 D-2lB Alone 

Areas -

FOr\-\ard Limit 

Aft Limit 

Vi iug a:t;'ea incl uding elevons 

Elevon area each 

Vertical tail area including 

rudder at W. L. 100 

Rudder Area 

Flap Area 

Di.ve flap area 

Approved for Release: 2018/11/16 COS11480S 

11,200 Lbs. 

5,300 Lbs. 

13,150 Lbs. 

24,350 Lbs. 

F.S. 2::'0 

F.B.294 

F.S. 319.1 

F.S. 300 

F.B. 320 

388.5 sq. ft. 

48.08 sq. it. 

3.77 sq. it. 

None 

None 
:3. ;.8 

Approved for Release: 2018/11/16 COS11480S 

D inlcns ions and General Data -

'>tV ~ng 

Elevons 

Chord 

Theore~ kal Root 

(Centerline aircraft) 

Reference MAC 

Locati.on of 25% MAC 

Airfoil Section 

Airfoil Thic1mess (constant) 

SVJeeilbad,: at 25% Chord 

NeBati'/e Dihedral 

Inc idence 

S[lan 

Chord 

Root (\d::i 40) 

Actual Ti.L=- (1/'1 S li5. 30) 

A \'crage 

Hhlge Line 

Ve r t i cal T cC il 

.-

SP-1214 

:Pa<~e 4 

'" 

lS.08ft. (228.(;0") 

0.'?37 

40.0 ft. (480') 

20.54 ft. (246.50") 

F. S. 2 cJ/).5 

Modified B i- convex 

2.3% (Max. thickness 

at .63C) 

6.26ft. (75.l") 

2 77 it. (33. 3") 

o 

2.076 it. (24. ()i2' 

F. S. 448.5 

S.58£t. (67.0") 

0.648 

Approved for Release: 2018/11/16 COS11480S 
3.1.8 

Approved for Release: 2018/11/16 COS11480S 

D tmens tonG and GeT1cl'al Data - (ConLd) 

Rudder 

BooSler 

Chord 

Root (W Li 00) 

Tip 

MA C (V·; L 1 27. 1 6 ) 

Airfoil Section 

Airfoil Thickness 

Sweepback at 25% Chord 

Span 

Chord 

Root 

Ti[.) 

Average 

Hinge Line 

Over-aLL Length 

(Including Fairings) 

Case Di.a. 

Max. Dia. 

Ventral Fi:l. S~lan 

(From Booster Centerline) 

Fin Root Chord 

(At Booster CenteriilJ.e) 

Fin Til:' Chord 

Approved for Release: 2018/11/16 COS11480S 

SP-;214 

Page 5 

13.5 it. (162") 

3,72 ft. ("lA:.66') 

9.54 ft. (114.43") 

Modified Bi-convex 

2-l/20/0 at WL 170 

(Theoretical) 

4% at \VL l25 

(Max. thi.cknes s 

at ,70C) 

]. . • 0,'. OOit (227") • 

2.225 ft. (26.7") 

1. 758 it. (21.1") 

1. 992 it. (23.9") 

F.S. 492 

44.25 ft. (531'1) 

2.51 it. (30.16") 

2 . .., Ie. 2 {< (-::: oJ_ ? 6 0 " ) 

3.90 ft. (46.8") 

7 12 ft. (85.49") 

4. 87ft. (58. 47") 
3. L 8 

Approved for Release: 2018/11/16 COS11480S 

DiE;ens ions and Genelal Data (Contd) 

ASIJect Ra::i.o 

Fln Area 

Fin Travel 

General 

(Not including Booster) 

Over-all Hei.ght 

(FRL Horizontal) 

Over-all Length 

Launch An~_;ie (angLe between 

\\ing reiereace [lanes of the 

D-ZiB anG the B-52H) 

Approved for Release: 2018/11/16 COS11480S 

SP-1214 

Page 6 

.650 

23.38 sq. ft. 

7.08 ft. (85 '1 ) 

42.85ft. (514.21") 
Approved for Release: 2018/11/16 COS11480S 

\~ f~IGHT STATE1IENT 

Lbs. 

634 

Tail 104 

Fuselage 1. 708 

Surface ControL; 163 

Pror:'uls ion 1, 32() 

90 

Hydraulics 121 

Electrical 204 

Elcctl'onics 268 

il.. ir Coadition bg 80 

Re cove ry E:y,~ ten, 138 

Furnishingf (Interior Il1sdation) 84 

t'<:l.yload 318 

Unusable Fuel 59 

Zero Fuel \'.eio:ht -.-.-----_.-------,._---- -~-~-

5,300 

Fuel. 5,?OO 

D - 2: V'I c i ( h L ---_:...:.£<1- I l. 200 

Rooster \:; c i·,rht , \-_'- 13,150 

Launch V, eight 24, 350 

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3.2 General 

SP-12l"! 

Page 8 

The ai.rcrait i.," a rl1i.d\\ i'lt~ rronor.lane type, of metal and Flastic 

constr'-lction. Dedgn is as simlJle as posdble consif,:tent 'I, ith 

the Lec.:Cf'sary o[_eral.tonal. n-Jaintenance, and checkout charactertsLics. 1ho jade aircraft veith its Fov.er \ni~ is expendable. 

3.2. l 

3.2.2 

3.2 3 

G~~al!Ll.~~_:~l,~.E Arral~~ef);ent - The interior arrangen;ent is es se',: ta.lly di.vided beo four sections located in 

a Lore to aL reta!.ionshiii. The Hrst f3e .. :tton is the circular 

engine ai.r inl.:;t v. ith appropriate fixed spike and bYl,ass 

instaLlations to control air flow and boundary layel· removal. 

The second sect:ion is the eqLliliment inGtallation bay, v.:hich 

honses the ~_,ayl()ad. recovcl'Y parachute, and nlajor 

electronic ,gear. This com()artmcnt is suitably cooled. 

The thil·d section c:xJe;1(Hl1g for 200 inches comr::ri!:'es three 

fl~cl tanks, suitably interconnected to jJrovide the ent ire 

fuel sUl-:"ly for Lhe e:lgiae. 

The f()L~rth section is devoted to the installation of the engine 

\\ ith its integral tail i;iL.e and nozzle. 

Materials The main structural material is titanium alloy, 

except for those areas where temperature reqL:irements 

dictate the ,:se of stai.nless steel and/or other high temperature alloys. Non-metallic materials are llsed in areas 

found to be suitable or as requi.red for njission accomplishrncnt. 

The desi.gn procedures, male:rial propertier3, and rnaterial 

~,rocesse6 conform to the standards estahlished in Contractor's 

Reports, LAD-IOS, LAD-I08, SI'-153D, Sl-'-156B, Sl--154C, 

and SP-377. Standard (-,arts and usage are as described in 

Report LAD ~ i OC). 

'IV orkrnanr:hil ; - Cons~ruct ion of the aircraft, including 

suchopera<.ions as detail fabrication, assembly, and 

eqliipr_;ent ins:allatlon l!'o accorrJ;ilished in a I:horou;h and 

\'.'orkn,anlike rr,anr~er con~' istent \\ Lh hLyh-0rade aircraft ,.j ..... i 

manlliacturin.g r.:.ractices. 

Approved for Release: 2018/11/16 COS11480S 
3.2.4· 

3.2.5 

Approved for Release: 2018/11/16 COS11480S 

SP-12:4 

Page 9 

Production! Maintenance and Re~Jair The first 

con!:'ideratiollE in the deslgn and construction of the 

aircraft are performance and reliabEity. Secondary 

cons idcratiol1.s are ease of ac,:es!;, rna intcnance and 

rer;air. All factors l{~ading to rapid producibUity are 

given carefui conFideration. but are not incorporated 

at the expense of periorn12.ClCe, reliability or ease of 

maintena.nce. The desizn, ""hile uti.lizing high 

strength titanbr:J alloys and high temperature ?lastic 

mater tal E.;. emiAoys conventional fabrication and 

as sembi y technique s to the maximum degree pos sible. 

~:)l'ecautions are obeer'ved in the handli.ng. processing. 

and installation of titani'.;n: alloys to inhibit corros ion 

and fatigcl,c. Such design t)ractices and production 

[Jrocedurcs as defined i.n the documents outline i.n 

l'aragrai.Jh 3.2.2. 

The desi~~n (-,oliey affecting the flight control system; 

and hydraulic. fueL and electrical sYi:,terns, is to 

c lirr inate insofar as pos s hle. any i.ncorrect installation 

or re-installacion of comr,onents or assen;blies. Fluid 

linee. linkage:> and wire. etc., are so designed that 

incorrect L-lstalLation is not possible by inadvertent 

action. '\,\'here such errol' would involve damage, malfunction, or safety of il ight. 

The design of the vehicle l,ermits effective inspection, 

nla.i.ntenance, and repair p:'ocedures to be utilized in 

production and service. Accessibility is provided to 

permit scheduled rna intenance and prefl ight check-outs 

as rcquired for rn is s ion accomplishrnen~. Emphas is is 

placed on ease of repiacement of n1ajor units such as 

engine, subsystetn COITlpOnentf', electronic equipment. 

a~ld payload. 

Interchangeability and Ret,laceabUity The folio\', ing 

components are interchangeable substantially in 

accordance '.vitl1 MIL-I-8500. 

Rudder 

Equil)ment Bay Hatch and Installed Components 

Elevons 

Booster 

Booster NOf:e Cone 

Booste1:' Tail Cone (incl. fin) 

The foltov.ing components are considered to be replac.eable 

with n;t;-lor trln', and hole transfer. 

Miscellaneous Doors 

Vertical Fin 

Wing Leading Edge 

Inlet Spike 

Approved for Release: 2018/11/16 COS11480S 
3.2.6 

3.2.7 

3.2.8 

3.2. :) 

3.2. ; 0 

3.2. 11 

3. 2. ~ 2 

3.2. 13 

Approved for Release: 2018/11/16 COS11480S SP-!Z14 

f.·age 10 

FLdsh - The standards used for the finish of the vehicle. 

both interior and exterior surfaces, are defined in the 

documents listed in r"'aragrarh 3.2.2 of this specification. 

Identification and Marking - No exterior markings other 

than the 1vlanufacturer's serial nurllber and access cover 

identification are applied to the ai.rcraft. 

E;,::tren:e Terr,:..;eratu:re Operation - The aircraft as a whoJ.e, 

v,ith its equip~en.t and a~cessori..es, is designed to meet the 

req~i.rement for satisfactory function throughout the extrerr,e 

environmental ope rat ion ambi.ent flight temperature range 

of -90 0 F to + 110°F. The ARDC temperature variation vvith 

alti:'Llde (Ref. AFCRC TR-5S'-267. {fIlS, dated August l')5C)} 

is assulT;ed for performance determination. 

Ground Clhy.a~ic ReQ

66rements - A ground ambient temperature range of _65°F to +1· OF isa-s6umed for the basi.c design of the 

airel·ait. Specia.l deviations to this temperature range must be 

given for the tYtCe of fuel, hydraulic oil and over-aU cooting 

systems used. It is assumed that ground shelter will be provided 

sO that normal ground envil'onment is + 35 OF to+ 1 OOoF. 

Lubrication - Provisions made for lubricating the ai.rcra.ft 

and t~s equiiiu;ent and accessories are generally in accordance 

with the reQLltrelY,ents of Specification MIL-L-6880B. Hovlever, 

dLle to unusual environn}ental conditions> 801":Oe lubricants are 

selected as a l'esult of Contractor's tests and are not necessarity in compliance with this Specification. 

Sta~1c1ard 'Parts - Standard parts are as t isted in the Lockheed 

En2ineorlrl0' Standards Manual, selection to be made in accord- ~ c) 

ance with the requhements of MIL-STD-143. 

Crev; - Not Appl icable. 

Equi[::,ment Installation - The ai.rcraft incorporates major 

items of eql:i(;ment, or provis ions therefore, as noted, listed 

in the follow ing sub- paragraphs. 

3.2.13.1 

3.2.13.2 

Armament - Not Applicable. 

Inertial Navi~ation System 

A Honeyv. eU MH-3S'O(d} bel'ttal Navigation 

System is installed on the equipn;ent bay 

hatch. Output signals from the INS v, ill be 

used as steering signals in. the autotj Hot, 

and i.nformation signals i.n the payload. 

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Pagc 11 

3.2.13.2 

3.2.13.3 

3.2.13.4 

Inertial Navigation Sxster:n (Contd) 

The systerr. w ill provide point to point steering 

signals for up to 32 pre-deternjined destinations. 

Tr4c D-21B position error may be upda.ted to the 

accuracy of the B-52H irllrnediately pdor to 

launch. Jlv1aximum position error at launch, 

er.1ploying the stellar trad;:er instaLled i Ii. the 

B - 52H vdll be + 1. 7 naLlticat n: iles, During 

free fli.i~ht the nlaximum rate of error build-up 

v. ilL be 1. 2 nautical miles/hour. 

The computer section is also used in conjunction 

\\ llh Lhe In w £1ight Check-out System. 

Instrun~ents - Not Applicable. 

'pyrotechnic Devices 

3. 2. 13.4. 1 De struct System - A de structor 

::;ystem caua'hle of dCl3troying the 

a ircraft and its payload is provided. 

The system conforms to the intent 

of USAF Spec x-ZS663. The destruct 

system is armed by time / command 

after launch. and is actuated by: 

(l) altitude during free fliGht phase. 

or by (2) altitude cornmand during the 

term tnQ.l phase after payload ejection. 

Thero is no provision for destroying 

the payload and electronic equipnlent 

after hatch ejecti.on. 

3.2.13.4.2 Payload Pyrotechnic devi.ces, (Gas 

Generator, Initiator, and Thrusters), 

are utilized to release and eject the 

payload (inc1t~ding beacon) irom the 

vehicle at the to rm ination of the fl ight. 

Payload recovery is acconJplished by 

a drogue gun deployed stabilization 

and recovery parachute systern having 

cartridge actuated release pbs. 

3.2.1. 3.4.3 Launch Systern - The D-Z1B launch is 

accomplished by electrically activating 

three exrlo~ iva bolLs at the three pylon 

attach points. 

3,2.13.4.4 Booster Jettison - After booster burnout 

the empty case is jettisoned by electrically activati.ng two explosive bolts 

and a gas generator which pressurizes 

a cavity and drives a pi.ston attached to 

the booster. 

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Page 12 

3.2.13.5 

3.2.13,6 

3.2.13.7 

"' 

3.2.13.4.4 (Contd) 

This action applies a separating 

force to the booster and insures a 

clean jettison. The booster may be 

jettisoned during mated flight aLso, 

however for aerodynar.:-. ic reasons 

this \\ i.ll preclude any subsequent 

D-21 B jettison. 

In-Fl i.ght Check-out (!FCO) -

In order to iasul'e a safe launch and succeesful 

n,tssion cOTIl;-;letion, an in-flight check-out 

system is monitored in the B-52H. The following 

D-21D systems are tested prior to launch from 

the B-S2H (Launch Control Officer Station): 

1. Automatic Fl ight Control System 

2. Inertial Navigation System 

3. Payload 

4. Electric Power System 

5. Comn"and Receiver System 

6. Hydradi.c System 

In-Flight Mon itor (IFM) -

The follow iug sys tems of the D-Zl B are monitored 

continuousLy at the LCO station: 

1. 

2. 

3. 

4. 

5. 

6. 

7. 

8. 

i O. 

11 .. 

Destruct System Temperature 

Altitude Switches 

Comn1and System 

Hydraul i.e System 

Fuel System 

APU Speed 

Battery 

A PU Overspeed Lockout 

Launch Sens ing System 

INS Pes Hion Error 

D-21B Mach No .• Altitllde and Heading 

In-Fli.ght Suhsy~ten: Control -

During mated flight the following D-21B Systems 

al·e controlled from the LCO station: 

1. Fuel System 

2. Hydraulic Systerr. (Pressure only) 

3, Electrk Power System 

4. INS Positi.on Update 

5. Telen.etry Transmitter 

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Approved for Release: 2018/11/16 COS11480S SP-1214 

Page 13 

3.2.13.8 

3.2.13.9 

Launch Control -

The following launch functions are controlled 

from the LCO station: 

1 

~ . 

2. 

3. 

4. 

Positioning of Booster Ventral Fin 

Engi.ne Fuel 

Engine Ignition (Backup) 

APU A ir Transfer 

Note: Functional Systems transfer from mated 

to free Hight occur s automatically on electrical 

umbilical separation. 

Pa yload Hatch -

The payload hatch is located bet\veen Stati.ons 

141 and 222.5, on the underside of the fusel.age. 

The foUGW tng eqllirment is mounted on the 

hatch and is ejected..,-,f ith the hatch: 

1. Payload 

2. Payload ELectronics 

3. AFCS A ir Data Compnter 

4. AFCS Electronic Components Assembly 

5. INS Power Supply 

6, INS Computer 

7. INS Gimbal Control Electronics (GCE) 

8. INS Inertial Electronics Unit (lEU) 

9. INS Platform 

10. Recovery Beacons (2) 

11. Beacon Antenna Transfer Relays 

12. Beacon Antennas 

13. Generator Control Box 

14. Command Receiver 

15. Electrical Breakaway Couplings 

16. Air System Breakaway Couplings 

t 7. Telemetry System (excepting Transmi.tter) 

AU of the above components are enclosed by a 

housing comprised of the hatch and hatch cover 

so as to provide a water tight and bouyant unit. 

In addition, the aerodynamic decelerator and 

recovery system is mounted on the hatch, but 

not within the '<vater tight housing. 

3.3 Ae l'odynam ic s 

3.3. 1 General - The external configluation of the aircraft is based 

on a modified delta vdng ptanform. The body incorporates the 

drcdar air blet: '\vith its spike in the extreme forward nose. 

Approved for Release: 2018/11/16 COS11480S 
Approved for Release: 2018/11/16 COS11480S 

SP-1214 

Pa~4e 14 

3.3. General (ConLd) 

3,3,3 

3.4.2 

3.4.3 

The fCHebody i.ncorporales chines which act as a canard-1U~e 

sn·fa(e. The enghe i:: in the afterbody, and because of its 

C01!!i,le;ely i.n!errFll il1staLlation, resLl:s in a SHlOOth strean,-

lli1t:':d aL)loa:::ance fo.r the enL ire a i..:.' craft. In general, all 

external st.afaces an~ Hush, utilizing t)L;tt joi.nts and flush 

attachnlents. 

Stability and Control The aircraft is aerodynal1:i.cally 

s tal~r8-:--'11lC-To\~~odyrLar i.e daHl!, i::-l.g at high ali itucle s 

recr:i:'e!3 a1', ii.:bl sta:jiLi.:y augme:-:la~io!l. S~;ecial. eHort 

i.s mace to obtain the r,ost 5table L)latiorn~ at hi:;h altitude 

~hat t1:c staLe ()I 'he art allav; s. 

Jel!.tson - The D-2IB n,ay be jettisoned, with no engine 

pO', e,', arc~ \' Lh qOun (Y)a1'o': electrical or normal 

hY(~l'a'.Jic~'(J\'.er available. The D-ZIB cDntains an 

er;;el';.,e'··cy LyCl'a'.Ll.k sYSl.enl \1;hk11 e:lcrgi.zes the control 

sy",ten: in the event of a jettison. The booster l:'lay also be 

jettisoned dllrirlg l"',jated £li:~ht, but it i.s to be no~ed that for 

aerxlynani.c reasons the D-2IB cannot be jettiQolled alone. 

Gener~.;.l - The structural desiGn cri::eria i:; ~)ased on the 

'Fit8Jl.tol the req (1 ~ rcn:ents of St,ecification MIL-A -8860 

(ASG), dated 18 May IS60. 

Maxi:uuy; fL:"ht Desicrn Gross '.'.'ei.;ht - The maxi.mum flight 

dCbl':;,T1""'"""::')"ross ~, '-~'.eid1L <..J i~ 2.4,3~O !:'JoLH~cls for cart.ltivc Hif.::ht:, 1. __ launch, 

and boosted n £:..;ht. Free n i:;ht rlJ;.txir:1LlIn groB s \\'eight i.s 

1 J, zoe pounds. 

Lin. it .Fl i(}ht Load Fllctors - Limit 11 ight load factors are 

po-si.t-Lve 1. G~~ aH.1 O. 5g for captive fli,,:;ht.Fl'ce Hi.:;ht mancaver 

load factors are positi.ve 5. Og and negative 2.0 g. 

The n:axi.n lIm iree flight gnst load factor i.s based on an empty 

wei:~ht and a gust velocity of 27.5 ft. Isee. (rough air). 

Crit kaL ait il:ude anet 5 peed are 60, 000 ft. and 400 KEAS 

res;)cctivcly . 

. 0. n z (~~u6t) 

n z (total) 

:: 

= 

2.00:; 

3.0015 

Maxinmr.n ca~'t ive flight gust load factol' is based on a 

B-52H/D-2.1B gross weight of 2!,O, 000 pounds, a gust velocity 

of 50.0 it. I sec., an altitL',de of 20, 000 ft. and VH"'250 KEAS. 

6. n z (gust) 

... n z (total) 

:: 1. 38g 

2.38g 

Approved for Release: 2018/11/16 COS11480S 
3.4.3 

3,4.6 

3.4.7 

Approved for Release: 2018/11/16 COS11480S 

3 4:.6.3 

j. 4:.7. 1 

3.4 7.3 

SP-J214 

Page 15 

L in it S r-eed in captive n i~hl b 2SC KEAS or 

M :: . BO. 

Doooted Fli:~ht 

Limit sreed in hoopted nh~ht iq 5(lO KEAS or 

M '" 3.6. 

_____ Free Fli--,ht >i!.._ 

L tE it F l,ced in hee n ighl iF' 4') U KEAS or 

1\1 '" 3 . .:3. 

'1 axi Luads 

Taxi of ·he B-S2H or the t()\'.al>le transporcer car: 

docs not ~:enera:e t );:u} iactort. \'. itLin the a.il'crai:, 

;~reater than '.hu~e listed Clr ground handli.rlg 

(' U lU . .:i t i '.H1 S • 

For ~he l [, 20n i--)O'X'l(~E gr0ss y. eight condit.ion 

Lhe gr()\l!ld hanclli:ll; Lad fal:tor", are: 

Vert kal: ..:.. 2. Og 

LateraL: .:O.5g 

Fore & Aft: ~ O. Sg 

Air T ra.ru.: rt Load!:: 

For the 5, 30e t=ounds gro::: s weigh~ condit ion 

(no fuel) the {,)llv\\ ing combinations are 

at>plied: 

Ver ieal: 

Lateral: 

Fore &: Aft: 

+ 2. Og 

.,. 2. Og 

:.::. O. 5g 

________________ :...A:.r:pJ:.p.:..::ro:..:v-=e~d__'_fo=__r___'R__'_=__elease: 2018/11/16 COS11480S 
3. 5. I 

3.5.2. 

3. '). 3 

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Page 16 

3.4.7.4 

3 4.7.5 

Stnlctural strength is t;rovi.ded for hoi5~ ing 

the vehide at a[;,;ropriare [Joints anJ. lor 

tra1l5[:orting the vehicle on a towable carr 

Cra~h Loads 

For a cra;:h condi~iun whereb. the D-2.:B is 

u ated to the B -S2H, ELrength i.s ,l'ovicicd to 

\. i: h::;tar d a forv ard had factor of 3. ug (ui.t. ) 

c()Lb t;lCO ·v. i, h a dov. ny ard Load factor of 

2. Og (~l'.) at a D-21B gross \\ei.ght of ; 1, 200 

tjounds. 

Elevon travel is 17° up a.cd ; 80 down. 

There arc no [:l'ovL,it)ns for balance \\ei:::;h~:[.; or trim tabs. 

Approved for Release: 2018/11/16 COS11480S 
3.6. 1 

3 (,.2 

3.6.3 

3. {" 4 

3.7 Body 

3.7. 1 

Approved for Release: 2018/11/16 COS11480S SP-IZI4 

~age 17 

De~"crirtion ared Con~rjonents The tail grour.:: consist" of 

avcr:i.cal ifabilizci:"-n.mmtcd on the centerline vf the ·,l[;f.er 

aft Llseta;;c. c(.m:ainh,: a hinged nlddcr, Rudder traveL i.s 

100 each f'ide of ce ~!ral. There i3 also a ventral fin located 

on 1.he bOOE':cr. 

Construc:i:Jn - The vertical stabilizer, rudder and ventral 

lin are d:ar.ilw thl'ou;;hout and are of conventional skin and 

r iL con ti L rllcL lUll.. 

Rudder - The l':;<.kler i.s 0lJerated by a torqae tube mounted 

in ~hc ("tub fin. The r,,:dder f'ervO uni.~ \s connected t.o the 

t:orq~le tUDe a"1.d is mounted on the up,'er surface of the 

fU8elage ,,'.,t'hin lhe b~llb fin, 

Ventral Fin - 1 he ve~ltral lin is a conventionaL airfoil sect ion 

\'.11[(11 can Le rotated (~5° about the booster so ;:U:' to i,;rovide 

grc\l:ld clearance, The ro~atim nlechani~m \". hi<h is driven 

by an electrkal actuator, is activated ",,.hen airborne, caUf~i.ng 

the vC:ltral fin LO swing dov,n tu a bottom centerline position. 

Fuselage 

3.7.1. i 

3.7.1.2 

Essentially, the fuselage if a cylindrical shape 

extending fron: the engine air inlet to the engine 

tail Fil,c. The general configuration contains the 

n,ajor elements nece,; sa1'Y for the aircraft 

n~ is::: ion, The :;;niooth E'treaml ined [orr.ll is the 

re s ult of aerodynam ic and functi.onal cons iderations. 

Cons tl'uct ion -

The prime fuselage structure i:=: a titanium alloy, 

serlli-monocoque constrllcti:Jn, cn-:ploying sHJOoth 

sLin attached to formed frames. 

Tv/o ty;ajor ol;enhgs are L~rovided in the fuselage: 

One. in the fOT\\ard to\'. cr body \~et\".een 5tatit'm8 

1,11 and 222.3, and at):~rexirr;ately -10 inches 

wide. This Ot.cuing accorr::modaces ~he equi,Jrnent 

COTl"lparLtLent hatch ,,''.hich is cjectable. 

Approved for Release: 2018/11/16 COS11480S 
Approved for Release: 2018/11/16 COS11480S SP-1214 

3.7.1.2 

3.7.1.3 

3.7.i.4 

Pase 18 

Construction (Contd) 

The :iecond opening i" on the top centerline of 

the mid-fuselage over the fuel tank area; al,proximately ZZ i'1ches w ide, it extends fron! Station 

235 to S;ati.oa 385. Thi.s 0;. ening c,rovides access 

for servicing and i.n!:~Jecting the fuel tanks. 

Sllitable insulation i.s apij1ied to the outside of the 

iUEeiage in the vicinil:y of the fuel tanl<,s. 

The eqd;:jment com;)artrr.ent is constructed b. the 

forward secti,)n of the fuselage bet-;veen Station 

141 and Station Z35. Titanium strllctL<.re is 

designed to ?rovidc the necessary s~,ace and 

mounting [Hovis ions for the allxil iary power 

uni.t and other subsy:-Eenl eq'.lttJrLent. 

The major electron ic eq'.1 t[Jment, the payload, 

and the l'eCOvcl-y parachutes are all mounted 

on the compartment hatch in the o;)ening provided 

in the fuseLage. The hatch i.s ejectablc to serve 

as a platform for the tJayload and electronic gear 

in their recovery descent. 

Dive Flaps - None 

3, 8 Al igh! i.ng Gear 

None 

3. Sllrface Control System 

3. C). 1 Frimary Flight Control The ·bas ic fl ight cont rol s ystcm 

consists Ol an autol:--ilot, servo control valves, hydraulic 

actuaL hg cylinders and the 5 urfaces. The t·rime mot ivat. ion 

will be lhe si.gnals derived in the autopilot and stability 

auglYlenta.tion system. These signal.s v.Hl in turn control the 

positioning of the servo valveE, thus establishi.ng the £10\.\' 

of oil to the hydraulic cylinders located at the surfaces. T\\() 

sets of t\VO cyl iader::; actuate the elevon and one cylinder 

actuates the rudder. Automat ic fC:pring-loaded locks are 

provided to Frevent flutter in the event of compl.ete los s of 

hydraulic system dl.iring mated fl ight. Emergency jettison 

control valves actuated and ~.JO'\V ered by the ernergency 

jettison hydra'Lllie o-:ystem meter oil directly toPthe t)rinJary 

cylinders to [-.osition the surfaces for jettison. The major 

coulFonerlts of the f1 i;.;ht control t'ysten, are des igned as 

subassemblies '\,,11e:;:-e l:.racri.cablc to facilitate bench asseulbiy 

and check-ollt. The alltoFilot is located in the eq;li,:lment 

cornpartr:nent hatch and the servos and cylinders in the tail 

grollF. Acce;;sibility is provided for insiJection. removal 

and rel,lacement. 

Approved for Release: 2018/11/16 COS11480S 
3. 10 

3. '). Z 

3. Cj. 4 

3.9.5 

Approved for Release: 2018/11/16 COS11480S 

Secondary Flight Controls - None 

Lift and Drag hcreasing Devices - None 

Trim Control 6ys [em - None 

SP-12I4 

Page 1 (} 

Automatic Flight Control Syst~m The automatic flight 

control system consists of tEe air data computer, :he 

stability augmentation syutem and the autopilot. The air 

data computer provides a source of data for the stabil ity 

augrnent.ation system, the guidance systen:, and the payLoad. 

The stability augn,entation Fysten~ incor;,:;orates logic: 

circuitry to in'·l1re nlaxirrum relia1:_-';.lity. Stability auglTentat ion is pro?iclecl on three axes. The alltopUot modes 

are talltlch, cn:.ise or Ma,:h hold. and recovery n,ode. 

Enoine .;;> Se·~tion 

'"' . 0 . ..). 1 • ~ 

3. ~ 0.2 

3. ) 0.3 

3.: O. 4 

3. 10.5 

3. 10.6 

3. J 0.7 

De seri.ot ion and Components The engine i.s conta illed in 

the aft \)ort ion oi the 'fuselage. 

Construe! ion - The fuselage structure in this area 1.8 aU 

t:netai. ':,cn-. i-rnonocoque structure utilizing titanium alloy 

as lhe fJrime n.a::e:dal. 

Eng inc Mounts - The eng ine is rcounted by means of 

S[::11erical ball fittings located in two fuselage planes. At 

t:itatiol1 435. ')3 a single bail fitting attaches to the lnlk.head 

on the top canted inc. This fi.tting is deu igned to tal::.c full 

engine thrust loads. At Station 4tJ8. 13 the monnting consists 

or three spherical ball fictings located at 120 degree htervals 

arollnd Lhe en~~ine. Thebe fittings are attached to the fuselage 

fran:c at this station through suitabl.e linkages designed to take 

eng i.nc radial loads. 

Vibration Isolators - Nylon vihration isolators are provided 

at all metal to metal contacting loca(ionl:l betvvcen the D-21B 

and the rocket booster. The:se are to isolate high frequency 

vi:)ration generated in the rocket motor. 

Firewall - Fuselage Station 435 bdkhead serves as an aft 

tank bulkhead as well as a firewall. 

Access for lns;)ection and l\1aintenance - Access to the 

engine if) by removal of the aft fuselage structural c-hell. 

Approved for Release: 2018/11/16 COS11480S 
3, i: 

3.11.1 

3. l ~ . 2 

3. 11 . 3 

3. 1 !, • (; 

3.:t.7 

3. i. L 8 

Approved for Release: 2018/11/16 COS11480S SP-1Z14 

'eage 20 

General Dcscri~,ti.on anu Components - One Marqi1.arclt 

RJ -43, Mc;dcf MA -205-4 Ramjet engine canst itutes the 

free flight i~ro~,LIlsion [,ystell] for the ai.rcraft. 

Allxil iary P rOFutE; ion 'Cl' i.ts One LocLheed Prof/uls ion 

Con'tany solid i,ropcllant rocket booster, LPC Model A<)2, 

"Avan'ri . 

None 

.A i1' I:ccbct i,)n Systern The a i.r induct ion system cons ist s 

of a ri1'(:1.113.r inle:"located in the extrerr e forward portion 

of t.he fusela~c. A duct. circular in cross flection, connects 

the air inlot to the ent:i.lle. An inlet fixed s[,;,ike and by,;ass 

velt i!'1stalLlt ions are provided to control i.nlet shock pos ition 

al~c1 b')l~ndary lare r ren'Ioval. 

Exhaust Systel'n The exhaust t·yster;; is sU[J~;licd \', ith the 

enl-lneandconsir,ts of a tail,)i ,e and a nozzle. , ) ~ I.. 

En'~ine Cor;;,artment Cooling The engi.:le comi,artmenL is 

cooLed by bleednTi:Taken Iron. thl' l'Ca in a i.r inlet duct throll dl • 0 

a iixcd anrL:l~ls rhe locat.ed at fusela'Je Station 4:35. The S.'<h ,.' ,_, ,-:.l ~ 

in the eill~i:te tail,;ipe ts calUn<ated to forovide a coolint; atr 

flo\,. around the engin.e. 

F !lei Sys tem 

3. 1.1.8.1 

The lubrication sY5tem is ii1.tcgral 

The fuel is conta i.led in three il~tegral tanks, 

with the center tank as the s llml~' tank feeding 

the engine. The fuel tra()s1er system consists 

of an AC electricaLLy driven fllel pump, one 

each h the to 1'\', ard and aft tanks, pumping to 

the center sump feed tank for C. G. controL 

The center feed tanL has an AC electrically 

dri.ven booster ,iump to mai.ntab adeqaate 

pressu!,'c and flow to the engi.ne. 

A ni.~rogen i.nert ing systerr, is i.n"talled to 

r;ressLlrize the fuel tanks to l. 5 + 0.5 lJst. 

The nitrogen is carried in iiq' .. ll.d-in a Dev,ar 

flask. The quantity of nitrogen is EuHk:i.cnt 

lor the n,axir:: un) D', is s ior. uuraCion, or lor a 

return to base ic1 case of an abort at the launch 

poi.nt. 

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SP-IZ14 

Page 21 

3.11.8.2 

3.1.1.8.3 

3.l.l.8.4 

3.11.8.5 

3.11.8.6 

Fl:eL System Mana~ement -

The fuel in the D -21 B is used as the heat sink 

for the environn~entat control system during 

free flight. 

The normal fuel load of 9 i 5 gallons is loaded 

on the ground before T. O. There are no inflight fueling Frovisions. Fuel i.s loaded to 

give the maxhnum forv;;ard C. G., 1. e., tanks 

if 1 and #2 are filled to shut-off levels and the 

remainder goes into tank #3. 

Dl:ring carry-out portion of the D)tSsi.on the fuel 

system is shut-down until approximately one 

hour before launch at which time the number 3 

tank transfer pun,p is turned on to transfer to 

tanks 1 and 2 any fuel that might have leaked 

aft, and thus ensure a forward C. G. for launch. 

All pnmps are the submerged centrifugal type, 

three phase, 200 volts. 400 cps AC, induction 

\\ct rnotol'S, which are able to operate at 230/ 

520 Hz, 

The fuel is contained i.n three tanks integral with 

fuselage and hner v, ing structure. Total usable 

fLwl is 5,900 pounds at 6.6 pounds per gallon. 

A 3% air space is utili.zed for fuel expansion. 

Vent System -

Tanks # 1 and #2 vent into a comr.:,on mani.fold 1 ine 

into #3 tank and relieve th~op~r.a pressure relief 

valve set at a. normal 3 ps L _ 0 J , and vacuum 

relief set at 2 to 4 inches of water. 

Piping and Fitti.ngs 

Aluminum alloy piping and fittings are utilized 

for fuol, the nitrogen, and vent systems. 

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Page 22 

3.11. S. 7 

3.11.8.9 

3. ll. 8.10 

3~11.8.11 

3.11.8.12 

3.11.8.13 

3.11.8.14 

Valves -

Electrically operated solenoid shut-off valves 

are installed on the engine £'lel feedli.ne. Dual 

float-operated shut-off valves are i.nstalled 011 

the fueling lines in each tank. Pressure 

fueting is utilized for ground fueling. SelfEealing breakaway fittings are utilized. Sc;l.table 

check valves are used as required. 

Strai.ners and Filters 

il. 200 mesh fuel filter is instaLled in the engine 

feedline. 

No quantity gages are instaLLed. 

Fuel Vapor Inerting -

The quanti.ty of nitrogen aboard i.s sufficient for 

the carry out and free fli::;ht portions of the 

rr"ission. The qua'1.tity of ni.trogen aboard is 

determined by overfilling the system. 

Dr~5nage Provis ions 

Each fuel tank has adeq nate provls tOns :for 

drai.ni.ng sedir.nents and 'water at low tank points. 

Fuel Evaporation Control -

Fuel evaporatbn is controlled by use of low vapor 

pressure fuel and 1y tank pressurization in excess 

of the fuel vaLjor pres sure. 

Fueling Provhi ions -

The vehicle has a [_lre6sure fueling fitting i.n the 

bottom of the fuselage. This connects to a 

tr~nk line leading to all tanks. Dual shut-off 

valves in each tan1>:: are controlled by dual pilot 

valves which are located at a [_,oint \vhich gives 

approximatel y 3% air space when the D-21B 

aircraft i.s fueled. 

Defue 1 tng Provis ion~ ~ 

The vehicle is defueled through a breakaway 

fitting in the bottom of the fuselage. The AC 

booster pump in Tank No.2 is used for defueling. 

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3.[2 

3.13 

3. 11. ') 

3. l2. 1 

3. } 2.2 

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Page 23 

I~?:.ition Szstem - A triethytborane ignition/re-i,:;nition 

systcn~ is provided, and i.s an integral part of the engine. 

Descri;: ... tion ar~d Cornponents - An auxiliary power unit is 

provided to drive thel1yclradk pamp, the J\C/DC generator, 

a:1.d to furnish cooLillg air for the electronic uni.ts and the 

['3.yLuad. ThL: nl~it consists of a variable area nozzle air 

turb inc, gear box and pov, er pads, h:bricati.ng system, speed 

control systen', ;].nd an olltiet air tercperature control ~;ystern. 

Turbine exhaust temncratlll'C , is fierlsed bv , thermistors 

connected through the temperature control systerr, to the fuel 

flow bY-l;a5s valve which r":eters heat exchanger inlet fuel 

as reqdred to re~date ,~o('ling air within set limits. Up to 

20,000 it. aloe i:i:cle, Le(;;:lllFe of the possL)i1ity of freezing, 

e}~hallst air is contr(lLLcc: to a n-.ininnaJ:1 terDperature of 40°F'. 

Above this a1 ~ i~ ude a control temperature of OOF is maintained 

to provide sreater cool ing capac ity where r:co~sture is not a 

probiel"l.", . 

Rani Air Turti:w - j\ tur 1 ,i:'e <1ssernhLy consisting of a two 

blJ:CIed, self governing rani air tllr~)i.ne directly dri.ving an 

integral gC1":e1'<;.lo1' and a hydraulic pump is iJTovided to sUDply 

electrical and hydraulic::: \:-,ower for the carry out and boost 

jJhase of the n:lsslon. (See the electrical and hydrauli.c 

se:tions for descri~)tions of !ho electrical and hydraulic 

systems driven by the RAT. ) 

Electric Systern 

3. 13. J Description - Pov,er Sources The prin:e power source for 

tl1eelectrk system 15 a combination brushiess AC/DC 

generator. driven at 12,000 rprnt 5% by the auxiliary power 

unit. The generator has a capacity of 4 kva, 120/208 volts, 

400 Hz AC plus 100 ar:-lps 28 volts DC. 

Auxiliary electric l)o"ver for electric system operation during 

the boost F-hase is supplied by a ~-;erna-;-lCnt magnet AC genera.tor, 

installed on the nose cone of the hooster rocket and driven by 

a ran) air tur:)ir:e. This ge:'.erator has a rating of 4.5 kva, 

:20/200 volts, 400 Hz AC. Part of the AC output is supplied 

to a transiorn;er recti..fier \-.hich supplies 60 amps 28 volts DC. 

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3. 13. 1 

3. 13.2 

3. ;.3.3 

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Page Z4 

De scritJtion- Powel' Source s (Contd) 

AC and DC t)o\ver is suppli.ed to utilization equipments via 

s imr}ie distri'Yl;tion systems. 

A 600 VA solid state inverter i.s suppUed to provide 400 Hz 

+ 1%, 115/Z00 volts AC power to the Inertial Navigation 

system and the Autol,ilot. 

Batte:d.es 

3.13.2.1 

3.13.2.2 

Gen.eral Conformance -

The electrical system conforms to the btent 

of MIL-E-25366. 

Aircraft -

A 28V, 25 ampel'e hour silver-zinc battery is 

provided to s\;.pply power for the inverter, 

comrnand receiver, the destruct systeln, and 

the recovery systen; arter engine shut -down 

and pri.or to package se[;aration. 

The battery is connected to the remainder of 

the direct current system via a blocking diode 

which allow s the battery to receive po\ver, hut 

preven.ts the bat-tel'Y fron, di.s chargbg into any 

other than the above svedfied loads. A suitable 

heater i.s also provi.ded for this battery. 

t'acka'''e 

----~ 

A 28V, 7 ampere hour nickel-cadmLlm battery is 

provided to sup:)ly power for the o[Jeration of 

the Teien-;etry System during the recovery phase. 

A separate battery is provided for the recovery 

system beacon and is i.n.s called ins ide the beaC01} 

pad:age. 

Recel)tacies Un,bilical receptacles are located on the top 

a'1d hottom ce:,terline of the vehicle and mate \\ ith the ir 

counter ?arts in:n.alled in the pylon of the B -52H and the 

boostel' rc)cket. V, iring com'.ected to these rece;otacles i.s 

used for control ai:d check-out of the vehicle during the 

grol:nd test and nated flight phases as v.ell as to sl<pply pO\ver 

durh~ the ground test, mated and boosted flight phases of 

the ...-ehi.cle mission. 

Approved for Release: 2018/11/16 COS11480S 
3. 1'4 

3.13.4 

3.13.5 

3. 13.6 

3.13.7 

3.13,8 

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Page 25 

Equi.pment Installa:ion - AU equi:Jr::1e11.t, except those itenlS 

required for the flier-system, engine c011.trol. and the auto~ 

pilot gyros, are located i:1 the equ iprcent compartment, or 

are an integral part of the recovery t)ackage. 

"'~N iri.n.g .. The electrical wiring installation is in accordance 

with aeplicable :::-equirements of specification MF .. -\V -8160 as 

intertJl'eted by approved Lockheed Proces s Spec iiicat ion. 

MIL-VI -16878C type wire (329 0 F ambient) is bs tailed i.n the 

equipment compartment. VI ire installed in uncoated areas is 

MIL-C-Z5038 nickeL clad c'JPFer wire suitable for 650 0 F 

ambient temperatures. MIL-\V-16878C, Type E teilonwire 

(32So F ambient) is installed in the fuel tanks. Spec LAC 1-140 

v.il"c i.s installed in the payload package. 

Bondinz - Bondi.'i1g is accompt ished in accordance with the 

requirements of specification MIL-B-5087. 

Controls - (Refer to 3.2.13.7) 

Li.ghth~z - Not applicable. 

3.I3.() IgnitionSystem - (See3.11.9) 

3.13.10 Indicators - Not applicable. 

3.13.11 ElectricDri';es3.l3.lt.l One lbear actuator, driven by a 28V DC motor, 

conio:n:ning to lvUL-M-8C'J9 and eqllilJped with a 

radio noise .filter per MIL-I-6181 is installed 

i.n the aft section of the booster' rocket, 

The actuator is used to extend and retract a 

foldable ventral fin on the booster. 

3. 13. 22 Relays - The utilization and installat ion of reLays is based 

u~)on the :t'equiren,ents of the aircraft systen:. Relays conform 

to MIL-R-6106 or their at)plicable detail specifications and 

MS drav, ing s . 

3. 13. 13 Booster Coil - Not apl)l icable. 

3.13.14 Filters - Radio i.nterference filters are installed as required 

in conforn,ance with the reqdrements of MIL-I-6051. 

Hydl'aulic System 

3. 14. 1 DcscritJtion and Components - Two hydraulic povv'er systems 

are provided, the RAT and MaLl systems, both of 'l,vhich feed 

into the main control and distribution system 'which actuates the 

flight control surfaces only. 

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3. l4. 

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Descripti.on a-:d Components (Contd) 

SP-IZ14 

Page 26 

The RAT system, ddven by the ram air turbine i.n the nose 

cone of the booster provides hydraul ic power for the carry 

out and boost phases of the mission. 

The Main system is driven by the APU and provides hydraulic 

rower for the free £1 ight cruise phase of the mis sion. 

The Mai.n hydraul ic system cons ists of a variable del i.very 

pltmp, two reservoirs; a nitrogen gas IJressurized reservoir 

and a riston (seU pressurizing) reservoir, fUters, valves, 

and related H:.tings and tubing. 

Components of the Main system generaLLy conform to MIL-H-877~ 

except where devi.ations are necessary to provide satisfactory 

operati;)n throGghout the unusllal flight enveiope. 

The nOl'lnal operating pressure of the Main Hydraulic System 

is 3300 psi at zero £lovi and 3200 psi at full flow. 

To prevent structurai damage in the event of a hard over 

elevon faiLure du:dng n,ated flight, the hydraulic system 

pressure is reduced to eyOo psi. Pressure control is 

effected by selenoi.d operation of a pressure reducing valve 

via a s\vitch at the LCO station. 

The hydraulic fLLlid used in the system is SP-302 (MIL-H-2760) 

a high temperature de-waxed mineraL oil. An oil-to-{u·el heat 

exchanger i.s provided to grcvent fl;.,id temperature at the 

pump hom exceeding 500 F. The hydraulic system is designed 

to conform to the intent of MIL-H~25475, eXCcilt where 

devi.ations arC neces sary to provide sat isfactory oi,1eration 

throughout the intended ground and flight envelope. 

The RA T system cons ists of a variable del ivery [Jump driven 

by the ram air turbine, a heat sink reservoi.r, shut-off 

valve, filters and related £i~.tings and tubing. Self sealing 

breakaway fittbgs are provided to seal the two systems at 

booster separat ion. 

The basic oI.erating pressure of the RAT system is 3100 psi 

at zero flow and 3000 psi at full flo'.¥ \\hich is normally lower 

than that of the Main system. This enables the Mab system 

to lock out the RAT system at sw itchover during acceleration 

in the boost phase and as suriJe the full fi ight load. 

Both the Main and RAT hydraulic systems are serviced on the 

ground through disconnects provided in the lower surface of 

the fuselage and in the booster nose cone respectively. 

\<\;hen mated, the ground servicing for the complete sya tem is 

through the disconnects in the booster nose cone. 

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3.15 

3.16 

3. 17 

3. 14.2 

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Emerge:lcy Hydr,?-ulic System -

SP-1214 

Page 27 

Emergency hydraulic power is supplied by a cold gas blo'hdown accumulator which directs reserve flqid through 

!l1echanl.cal servo valves into the primary actuators to 

positi.on the control surfaces for jettison. 

Pneul1,atic System 

3. 15. 1 

3.15.2 

3. 15.3 

Adequate cooling for the electronic equ irment and payload 

hstalled in the equipment con1partment is provided by the 

auxilia ry pOVia I' ;.m.it (See Paragraph 3. 12. 1). Cool air is 

ducted directly to electronic units to provide suitable air 

drcdatl.on '\vithin the units as specified by the manufacturer, 

and air is also supplied for externaUy cooling the payload 

ar ... d other equipment not internaLly couled. vi ater is removed 

from the air by a water trapping device incorporated in the 

air syster:n in the B-52 which provides cooling air during 

carry out. 

Ground Cooli~ - For cooling when either one or two D-21Bs 

are mated to the B -52, a ground connection for each D-21B 

is provided in the B-52 fOI'\vard wheel well. The ground 

connections are not intended for ground operation of the 

APU. They are structurally able, but inlet air temper" 

ature must be held at 1800 - 18 OF. 

Anti-Icing ~jrovisions - A heated pitot tube is provided to 

precLtde icing of the pitot ports. 

Uti! itie sand Equiprnent Subsystems 

3. 16. 1 InstnlHlents - None 

3. 16.2 Furnishin~? - None 

3. 16.3 Oxygen System - None 

3.16.4 Emergency Rescue .. None 

Communications, Navigation and Guidance 

The follow ing equ i~)ment is installed, placed in normal operating 

condition, and tested in accordance y., ith the intent of MIL-E-25336. 

The equipment conforms to MIL-E -8189 '\,vhe1'e poss ible. 

Inertial Guidance System 

Autopilot with Stability Augmentation System 

Command Receiver 

Recovery Beacons 

Teler:netry Transm itttng System 

This equipment is located in a cooled compartment. 

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3. 17 

3. 18 

3.20 

3.21 

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Page 23 

Communications. Navigati.on and Guidance (Contd) 

3. 17. 1 

3.17.2 

3.17.3 

3. 17.4 

3.17.5 

Communication tpment - A nine channel command 

receiver is prov r rernote control of recovery 

beacons, telemetry transmitter, fuel shut-off, package 

eject, destruct arm, destruct disable, engine ignition, 

booster separate, a,1d n1anual destruct. 

ion E I..:ipment - A HoneY'v/eU H-3!)O (D) Inertial 

iga lOn ystem ts installed to provide steering 

i.nformation to the autopilot and present position for 

programming operating commands. 

Autopilot - (Sec 3.9.1) 

Telemetry - A Telemetering Sys tern is installed to provide 

tranSIT, is sian 01 vehi.cle pc rformance characteristic 8 for 

monitoring at rer:note locations. 

Antenna Installations - Flush mounted antennas are 

provided for command recei.ver, recovery beacons, and 

telerr;etry transr.r,i.tter as required to provide adequate 

space coverage~ 

These antenna instal.lations will conform to MIL-A-7772 

where pos sible. 

Reconnais sance SysterrJ 

Provis ions for installation of a GF AE canlera (Hycon HR- 335) and 

accessories, are n1ade. 

Fire Control System - None , 

~rmament System - None 

Ground Handling and Servicing Provisi.ons 

3.21. 1 

3.21.2 

3.21.3 

3.21.4 

3.21.5 

.!ow in.~ Provis ions - None 

Jacking Provis ions - None 

Mooring Provis ions - None 

~~~~~'2£l.1~~l18~10~1~1~S - Hoisting fittings are provided at 

ap?ropr1.ate points or raising and lowering the vehicle 

off a:ld on the towable transport cart, and the B-52H 

aircraft. 

MeagLlrin~ and Levelin Provis tons - Are installed at 

Stations 2 2.5 and 4 4. 

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Approved for Release: 2018/11/16 COS11480S 

3.22 Aerial Refueling Sxstem None 

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Page 29 

4.0 QUALITY ASSURANCE PROVISIONS 

The method of inspecti.on and tests are in accordance Vi ith Lockheed 

Aircraft Corporation, Advanced Development Projects Divisi.on 

standard F,rocedure. 

5,0 PREPARATION FOR DELIVERY 

Vehicle w'lli be prepared and delivered in accordance with the terms 

of the contract. 

6.0 NOTES 

6. 1 htended Use 

This Sl)eciiication is intended to descrtue the vehi.cle configuration 

at time of deli\'ery as cOli,ple;;e, assembled and flyable unit produced 

by Lockheed A ll'cra£t Corporation under ternlS of the contract. 

6.2 Revis ions 

The Contractor v .. i.11 ta~,-e suitable action to maintai.n this specification 

current by issuance of revised pages as necessary and appropriate, 

through delivery of the last vehicle described by this speci.fication. 

Approved for Release: 2018/11/16 COS11480S