NOT K.:LEASED DESTROY NO LATER THAN 

LOCKHEED DORIAN RESUPPLY STUDY 

NVH.LI31V1 ON A081S30 03SVD12,8 ION 

gammEr vemilmimmosami■Et 

NROAPPROVEDF.eR 

RELEASE 1 JULY45 
NRO APPROVED FOR 

RELEASE 1 JUL 15 

11. 

Oe 

LOCKHEED HAS CONDUCTED A PRELIMINARY STUDY SHOWING THE FEASI=ILTIY 

f" 

OF CONDUCTING UNMANNED RESUPPLY IN SUPPORT OF THE DORIAN 'MISSION. sr-7m 

Rya 

THE STUDY R4PHASnED THE USE OF THE RESUPPLY IN CONJUNCTION WITH 

Kis 

UNMANNED DORIAN OPERATION (DESIGNATED AS P-66 BY LOCKHEED). 

a 

THE RESUPPLY CONCEPT CAN ALSO BE APPLIED TO THE MANNED DORIANt= 

L'D 

a SYSTEM. THE STUDY REPORTS ON BOTH TECHNICAL AND COST FACTORS. 

1=0 

/15,17 

SM' '24 

RAM42 

dim 

PROPRIETARY DATA: The information and design disclosed herein were originated by and are the 

a-ros property of Lockheed Aircraft Corporation. Lockheed reserves all patent, proprietary, design, 

Za% manufacturing, reproduction, use, and sales rights hereto, and to any article disclosed herein, 

."4 except to the extent rights are expressly granted to others. 

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RETURN VMICLE, AND PAYLOAD 

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ATTITUDE . CONTROL, ORBIT ADJUST 

SYSTEMS AND EXPENDABLES (FOR 

MOL/DORIAN ) 

"MOL/DORIAN SYSTR4 
NRO APPROVED FOR 

RELEASE 1 JULY 2015 NOT R

ELEASED DESTROYNOLATf-:R THAN 

UNMAIRTD AUTOMATIC 3 L/EORIAN SYSTE:-1 CONCEPT' 13- ALSO 

PRESENTED TO ESTABLISH A POI 1i OF'REEEREME FOR 'hE DO IA 

RESUPPLY STUDY. THE COCEPT IS A DIRECT COPY OE FROM 

THE FUNDED Urr.,!&-IED DORIAN SYSIal STUDY (P-66) •AirD DORIAN • "' V 

MISSION TARGETING SOFTWARE PROPOSAL RFP. 

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11.111.1.17 • NRO APPROVED F 

RELEASE 1 JULY 

PRESSURIZED LAT3ORATCrY NODULE V/h SENscr, 

/-• AUTO cA:7,?A BAcK. 

FILM 1"9.1v:sp(r7 --1 

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FUNDED Tri.lAUNE,D IX),RIA13 STUDY ( 17 JUNE 1966). TELE P-66 `CO.OEPT 

I.11,PILASIZES SU8SYSTI-7 OflUIARJTYI Ti-T. CONTROL ATID P.ISSION • 

SUPPORT moDurs.s. TF1E, APPIJCATION OF THIS 1.:ODULARITY COI1(3.FPT 

IS CONTIITUTI.D OM THE DORTAN .P...E,SUTE'PI.Y TO FACILITATE SIMPI.,IF1ED 

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777;4/1/ _ND-5 SEGNENT 8005TE2 - 97° /4/C///147707/, 70- /70 
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AS NOL/DORTAr. -Fri:SUPPLY AIM Y.AN—Aq'STSTED :7?.F.SUPPLY HAVE BEEN 

COILPF.I.'.;) Irer _.:S OF DETE-':MiiiG Rg•', COSTS . HO';:iTIER 

MANY OF,' THE FAC TORS DEV'ELOY-FD SYSTE-: 

NOT R

ELEASED DESTROY 

NOLATER T

HAN 
romm...1 

RELEASE 1 JULY 2 

NOT R

ELEASEDDESTROYNOLATER TH

AN 

GROUND RULES AND APPROACHES 

o MAINTAIN TOTAL SYSTEM OPERATION AS LONG AS PAYLOAD SYSTEM IS OPERABTE 

o RESUPPLY EXPENDABLES AND/OR EQUIPMENT TO EXTEND LIFE 

o P-66 ORBIT (70 NM/170 NM, 97° INCL.) 

o LONG TERM MATERIAL USAGE RATE 65-70 LB/2 WEEKS 

• TITAN CLASS BOOSTERS FOR INITIAL LAUNCH 

• MINIMUM COST BOOSTER FOR SUPPORT LAUNCHES 

9 UNMANNED MISSION AND RESUPPLY OPERATIONS 
FC)Ft T.E. PLEPOST OF 'PITS A CI.5.•;.?41-,T, MISSION OFE?_:,710.;L• FI 

WAS. CONCEIVFD TfEl BASIC PF.1.2-:1 Sr. IS A 30 DAY LOH,TA I MIS 0:: 2:2, 70 1.33 F11.1; 

USAGI7, PPR ‘.TF.F. ON 60 DA Y ( 7:-4.7TS PRP3.:1SF USED FOR. FIT.:1LED 

DORTAN STUDY) , AS SUCH, T::13." R.: - -.:SUPPLY SYSTLi.: PROVIres SUFFICII.NT FIL41 LOAD *

FOR. A 50'7, MISSI 01.1 DUTY CYOL".-1- , . F 70 LT :,S UR:7.FL' , - F.010IER , STJ77 "L": 

EXPFKIABLES -6-FYF PP-0 "VTDE: TO HI CL7. 11117. • .7;0 1:1'../170 'HP3T 

colITINuous A;';"17...,F.'a . THIS PE3OVIDES • . FLEX I >31.1.: TO. • 

• •p110TOGPtAP - OF • OPPORTIIIIII77 AT • . • CAPSUL-t:" .P2 CO:1.,'"E•HY SOH:: r_1TJLF.;D 

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D F 

RELEASE 1 JULY 15 

01/E24ZZ OPEP,47704/ 

//1//77,4L P(SSI/PPZY EXTE/VGD 

OPER:47/04/ OPE-P.4776W OPERAT/ON 

11

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iNIROAPPROVED FOR 

RELEASE 1 JULY 2015 

THE RENDFTIOUS AND DOCKING OPERATION UTILIZES APPROACHES DEVELOPED 

IN THE GEMINI PROGRAM, TT IS CONSIDERARLY sii.:71-Fa TS. THE, UMINED 

INSPECTION I-aSSION FOR LDSC HAS BEEN DEVELOPING EXPE'RDIENTAL 

HARDWARE AND SOFT FOR 70 YEARS . 

THE ACQUISITION AND TRACKING RADAR AND DOCKING ADAPTER. CAN BE 

SIMILAR TO THOSE USED ON THE Ga:INT PROGRAM. BOTH COMPLETELY 

AUTOMATIC AND SEMI -AUTO'NATIC RENDEZVOUS AND DOCKING (DAN IN THE 

GROUND LOOP) ARE CONSIDERED AS FEASIBLE 1,MTHODS 

; - 3 
11.1111111.11" 

NRO APPROVED FOR 

RELEASE 1 JULY' 1 

0 RELEASED DESTROY NO LATER THAN 

RENDEZVOUS AND DOCKING OPERATION 2 

0 ro TARGET EPHEMERIS KNOWN 

m 

C3 

EITHER DIRECT ASCENT OR PARKING ORBIT RENDEZVOUS 

MAY BE USED ri 

o COOPERATIVE TARGET -c• 

0 ADJUST ORBIT FOR RENDEZVOUS AS REQUIRED 

STABLE -4 

trt 

BEACON TO AID ACQUISITION AND CLOSING 

o DOCKING SYSTEM 

LARGE INTERFACE AREA FOR ELECTRICAL MATING AND 

MECHANICAL ALIGNMENT DEVICES 

ACQUISITION AND TRACKING RADAR 

ACQUISITION OPTICS 

COMPUTER 

BEACON ON PARENT VENIOLt 
DRIATE OPERATION 

o MISSION MODULE SEGMENT RETAINS HOUSEKEEPING CAPABILITY AFTER SEPARATION 

o ATTITUDE CONTROL 

o POWER 

o RENDEZVOUS AIDS 

o TT&C 

o EXPENDED SEGMENT TRANSFERRED TO LOW ORBIT AFTER SEPARATION TO AVOID 

COLLISION AND IMPROVE DE-ORBIT, 

NRO APPROVED FOR 

RELEASE 1 JULY 20 
NRO APPROVED FO 

RELEASE 1 JULY 

0 

m 

r- in 

in 0 

0 

1711 

CO 

2 0 

0 

in 

REPIACEMENTCANDIDATES 

o ATTITUDE CONTROL GAS 

• EXPENDABLES 

o FILM 

o RE-ENTRY VEHICLE 

o ORBIT ADJUST PROPELLANT 

o FUEL CELL REACTANT 

• VEHICLE EQUIPMENT (RELIABILITY CONSIDERATION) 

V 

o FUEL CELL o T,T& C 

o ATTITUDE REFERECE o COMPUTER 

o ATTITUDE ELECTRONIC 

• MISSION SUPPORT EQUIPMENT (RELIABILITY CONSIDERATION) 

6 CAMERA MECHANICS 

ATTITUDE DETERMINATION EQUIPMENT (STAR TRACKER, Gya)) 

V/h SENSOR 

TRACKING .MIRROR 'SERVO AND IOGIC 
NRO APPROVED FOR 

RELEASE 1 JULY 2015 

RESUPPLY OF EXPENDARLE ITE S IS STVPLIFIED FY REPLAC ING, 

COMPLETELY OP IN PART, THE SYSTEMS IN 

Ti:HICH Ti[ EKPEZIDABI,ES 

ARE USED, THE COST AND V,T,IGHT PEI" ALT IES ASSOCIATED WI TR TH:S 

APPROACH ARE MI ::,OR CO.!PAP. ED '41TH RELIABILTTY GAINS FRO:: 

SIMPLIFIED DOCK ING INTERFACES . IN GENERAL , EXPEIDAPIE 

liFOPPI. IN PEESAC;=L, HAVE 217;EN RIDUCED TO LECHA!:i P 

AND. ALT Gre:P7 T AND ELECTRICAL CONNECTORS 

0 r0 

rn 0. 

0 

TTA'..711= 

NOT RELEASED DESTROYNO LATER THAN 

al, Iva 

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a 
•:, 

D F 

RELEASE 1 JULY 2 

EXPENDAKE RESUPPLY CONSIDERATIONS 

EXPENDABLE 

RESUPPLY 

ITEM 

HA.REO■ RE ITS 

RESUPPLIED TO 

SIMPLIFY INTERFACES RETAINING INTERFACES REQUIRED T7CRNCLOGY 

REASONS FOR. 

RESUPPLY 

ORBIT 

ADJUST 

PROPELLANT 

TANKS, PIUMRI no , 

MOTOR 

ALI GNEEN T VITH V Ell CLE 

POWER 

C OMAND 

STATUS DATA 

SELF ALIGNMENT DEVICES 

ELEC TR IC AL C 0?INEC TORS 

P ROPELLAI; T 

DEPLETION 

REACTION 

CONTROL 

PROPELLANT 

TANKS, PLUMING , 

THRUSTERS 

SAME AS ABOVE SAME AS ABOVE PROPELLANT 

DEPLETION 

FUEL CELL 

REACTANTS 

TANKS, PLTJNBING, 

FUEL CELLS 

POWER 

COMMAND 

STATUS DATA 

SAME AS ABOVE REACTANT 

DEPLETION 

FILM, RV 1 s FILM TRANSPORT 

....--- 

ALIGNMENT WITH CAMERA 

POWER 

COMMAND 

STATUS DATA 

FILM FEED THRU CAMERA 

SAME AS ABOVE, ALSO 

CUT AND SPLICE OR 

! SEPARABLE CAMERA BACK 

FILM SUPPLY & 

RV DEPLETION 

DAMAGED::- FILM 

SUPPLY ' 

rim T4ANsp OR T., 

CAMERA PikHANIam " 

, ALIGNMENT WITH ROSS TUBE* 

; Polo. 

COMHAND - f ,: 

STATUSpitA ' • -; 

FRAME DATA 

SELF ALIGNMENT DEVICES 

LARGE CAPACITY 

SIGNAL INTEKFACE 

(40(N1600 LEADS) 

NOT RELEASEDDESTROYNOLATER THAN 

ViLI3NIAt4T4tiY-tIE-0J170i1ATI 

FILTTRM SPORT' 

r 

t- 
NRO APPROVED FOR 

RELEASE 1 JULY 2015 

NOT R

ELEASED DEST

ROY NO LATER 

T

HAN 

RESUPPLY OF EQUIMENT. IS ,SASEI 

EXPECTED LIFE 

COMPLEXITY OF INTERFACES 

TO SIMPLIFY INTERFACES.IT IS DESTRAPLE TO GROUP THOSE UNITS OF 

EQUIPMENTS WHICH HAVE A HIGH NUMBER OF ELEOTRICAL 

INTO A SINGLE REPLACEME'NT ASSF2-3LY AND TO REDUCE 

a-EROONNE:,C,T10113 

INTERFACE 

REQUI R ERLI IT TO 1'.`2C HAN IC AL ALI GIF.!..ENT . 

A SECOND CRITERION IS ,TO GROUP EQUIE:ENT OF ADOUT EQUAL -E.41PECTED 

LIFE TOGETHER SO THAT MA,XII;::UM UTILIZATION IS AO3-IIEVED 66 

RELIABILITY REQUIREMENTS INCLUDED THE STIPULATION THAT NO SIIFT,I_E 

EQUIPMENT FAD-AIRE liOULD RESULT IN LOSS OF A PROMOTIVE MISSION. 

AS 11; RESULT, ' STANDBY REDUND;Ncy. 1.:As : REQUIRED IN Ti' H. SGLS ATTI'EUDE 

CONTROL :ELEOTFtONICS COMPUTER, DATA ADAPTERS, AND SIMILAR UNITS . 
REQUIRED 

TECHOLCG7 

ITEMS RESUPPLIED 

TO SMPLIFT 

INTERFACES 

REASON 

FOR 

RESUPPLY 

RESUPPLY 

I TE-I 

C 

(IL 

RI 

A Y,7:-,C HAN I SM 

D NG Pr:i.E S SU - 

A:PION ) 

:4. TRANSPORT LIGHT TIGHT MECt-

- CUT AND sPun 

MENT TECHNIQUES 

FAILURE, INTERFACE 

SIMPLICITY 

MECHANICAL LINKAGE 

ENVIRONMENT 

CAMFRA, RV, a5 FILM 

SUPPLY, PRESSURIZATION 

4111111111111111P

NRO APPROVED F R 

P11111011111111.11111111111111111111111.11111111111111111. 

RELEASE 1 JULY - 15 

EQUIP RESUPPLY CONSIDERATIOL5 

MION COMPUTERS,, 

BULK STORAGE UNIT 

AND DAU's 

SGL 

rAT74PDE CONTROL 

ELECTRONICS 

1.0 

STKPACQUISITION AND 

TRZAING 

FAILURE OR LIFE 

EXPECTANCY 

INTERFACE SIMPLICITY 

FAILURE OR LIFE 

EXPECTANCY 

FAILURE OR LIFE 

EXPECTANCY 

FAILURE OR LIFE 

EXPECTANCY 

FAILURE OR LIFE 

EXPECTANCY 

C U..71.1AN D/DA TA N - 

FACE UNITS 1 

USABLE FILM rn 

USE GEMINI MULTI 

PLEXING , SINGLE 

DUAL WIRE PLUG 

TIVC OTT-TANDS 

0 

rPRECISE ALIGNMENii 

DOCKING 

ALIGNMENT WITH 

TRACKING MIRROR 

ASSLY 

FILM SUPPLY 

FILM TR PI:SPORT 

SIGNALS, POWER, 

MECHANICAL ALI '37..71.--1; , 

ENVIRCINENT RADIATE ON 

SGLS, ATTITUDE CONTROL 

MODULE, V/h SENSOR, 

STAR ACQ, & TRACKING 

SIGNALS, POWER 

MISSION COMPINERS, ATTI- SIGNALS, POWM 

TUDE CONTROL MODULE, DATA 

ADAPTER UNIT 

MISSION COMPUTERS, DATA 

ADAPTER UNITS, SGLS, 

SIGNALS, POWER, 

ALIGNMENT 

MISSION COMPUTERS, SGLS, PRECISE ALIGNMENT TO 

DATA ADAPTER, V/h SENSOR OPTICS POINTING 

REFERENCE POWER, 

SIGNALS 

DOCKTNO AD1.17.a ANL1, 2 

TECHNIQUES SHIEL.- Ci) 

SAME AS ABOVE 

:rt 75, 

VW. 

TRICKING. MIRROR 

51 AND LOGIC: EXPECTANCY 

FAILURE OR LIFE COMPUTER :AND DAU 

SGLS , 

TRACKING MIRROR INTERFACE WITH 

TRACKING MIRROR 

A§Sg'IL 

RiPJNTNG 

INTERFACES 
15.0 

29.3 

NRO APPROVED FOR 

RELEASE 1 JULY 2015 

0 

In 

rIn 

C)

0 

0 

z

0 

C- 

-4 m 

z 

2: 

THE COST Ca.TAT.-',HONS PHSFT fl A7f." BASED ON THE FOII0Th5 ASSUYF -- 

NOI, P-66 

P-66 'zi.P. 

Ini ti al 

BOOSTER SM 17.0 15.0 15.0 

MISSION NODULE 35.0 35.0 35.0 

MISSION SUPPCaT ft 

CONTROL NODULES 50.0 12.0 12.0 

TOTAL 1.02.0 62.0 62.0 

FOR YOL ANT) F-66, SIX LAUNCHES PER YEAR OF 30-DAY LIFE VEHICLE WEE 

ASSUNED. FOR P-66 WITH RESUPPLY, AN INITIAL LAUNCH FOLLg:TED PY TEPEE 

130-140 DAY RESUPPLY VEHICLES WAS USED. THE REST OF THE STUDY PHSENIS 

THIS DETAILS OF TNT P-66 RESUPPLY CONCEPT. 

r7rm 

t 

eta

,`• • 

t • 

0,- -; 

d. '3 

ray 

:1 1 

T.J 

GNa4 
NRO APPROVED F 

RELEASE 1 JULY 2 

r 

ROM ANNUAL RECURRING HARDWARE COST 

SYSTEM ANNUAL COST SAVINGS VS. MOL 

M

p 

$612,000,000 

$378,000,000 $23/4,000,000 

$1119,000,000 $463,000,000 

MOL 

P-66 

P-66 RESUPPLY 
NRO APPROVED FOR 

RELEASE 1 JULY 2015 

z C) 

r0 

0 rl 

En 

0 

(1.1 

I —A 

• ›. 

27: 

THE DEPLETION, EQUIPMENT FAILURE, MID RESUPPLY IN CONSIDERATIONS 

PRESENTED IN THE PREVIOUS CHARTS LEAD TO THE RESUPPLY NODES SHOW N HERE. 

FROM EZPENDABLES, FILM AND RV's, THE RESUPPLY' LIST CAN•BE EXPANDED TO 

INCLUDE ALL EQUIPMENT SUBJECT TO FAILURE IN OPERATION. IN A MAXI= 

RESUPPLY NODE, MISSION SUPPORT.MODULE AND CONTROL MODULE MIGHT BE 

REPLACED COMPLETELY, AND THE ELECTRO—NECHANICAL ELEMENTS OF THE MISSION 

MODULE AS WELL, A, B AND C AT THE LEFT IDENTIFY RESUPPLY NODES FOR WHICH 

VEHIOU CONFIGURATIONS ARE DEVELOPED. IN THE FOLLOWING PAGES. 

THE GUIDANCE AND rre.-O EQUIPMENT OF THE RESUPPLY VEHICLE CAN BE USED ON 

ORBIT AF, MISSION EQUIPMEN I' AND THEREFORE OFFERS ADDITIONAL BACKUP IN 

THESE FUNCTIONS. 

NV

HI 2:131

V1 ON

t•as 

•••• 

rryw 

op.v. 

caws 
NRO APPROVED FO 

RELEASE 1 JULY 2 

RESUPPLY %0D1-,S 

MISSION SUPPCET AND 

COI\TAND MODULE RECOVERY MODULE 

EXPENDABLES 

o OAS PROPELLANT, ENGINE 

TANKS 

*USED loda ASCENT, RENDEZVOUS DOCKING, 

AVAII BLE 4S OH-ORBIT: BAcimp 

SION COMPUTER OF THE PARENT VEHICLE CAN ALSO BE B ED FOR Ezv9 

o RCS GAS, VALVES, TANKS FILM & RV's ON 

o FUEL CELL REACTANTS, FIRST LAUNCH 

CELLS, TANKS 

ATTITUDE REFERENCE 

A/C ELECTRONICS 

COMPUTER is' ,

o CAMERA MECHANICS 

o POWER DISTRIBUTION 

o ATTITUDE REFERENCE 

o A/C ELECTRONICS 

o T, T & C 

o COMPUTERS 

MISSION MODULE 

o TRACKING MIRROR 

SERVO AND LOGIC 

• ATTITUDE DETERMINATION 

o V/11 SENSOR E5 

16- 

0 

0 

0 

o RV's 

o FILM 

o FILM TRANSPORT 

o f 

▪ Ci2 

EXPENDABLES -‹ am 

FILM & CAMERA 

• 4 TOTAL > 

ESUPPLY M ;47.1 

7s.1 r" 

O ROSS TUBE 

o TRACKING 141EtROR 

I o PRIMARY AND AaLDnNG 

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LIFETIMES LOITO E7701iGE1-.TO. .13E.'opERAi.io UALLY OR ECO1011ICALLY -ATTP2.:CTI7E 

REFLECT IfEAVY LAG EJLtO-T 

BOOSTER:.'. CtppBTLITY .-TFLAY. 

Till D 

8 

52o LB 

10,00 

1170 

SOLAR 

ARRAY 

2 

1L0.L3 

2270, 

200 

560 F C 

REACT-T 

8 MK S 

560 LB 

10850 

TITID IB/ACEPI A 

RV 8 MK 5 2 MK5 

, , 560 LB :1140 LB, 

ORBIT ADJUST PROP 11200 • .2870 

INITIAL RV $ s Lt MK 5 

FILM .:280TH 

ORBIT ADJUST PROP 2650 

REACTION COUT PROP 590 

ELECT POWER 560 

NRO APPROVED FOR 

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140 DAYS 4o DAYS 

PROPULSION SYSTEM AND 

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SGLS, COMPUTE 

280 LB 

4 MK 5 

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TIIID I TIIIB/AGENA 

13 DAYS 38 DAYS 

PROPULSION SYSTEM AND 

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MISSION MODULE 

TIIID TIIIB/AGENA 

130 DAYS - 1: 32 DAYS 

PROPULSION SYSTEM AND 

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THIS CONFIGURATION IS DESIGNED FOR EXPENDABIE RESUPPLY. THE 

SATELLITE VEHICLE IS LAUNCHED ON A TITAN IIID BOOSTER AND PROVIDES 

EXPENDABLES FOR 35 DAYS IN ORBIT.-AT THE END OF THAT TINE THE 

EXPENDABLE NODULES (SHADED) ARE SEPARATED FRON THE MISSION NODULE ON 

THE LEFT, TO BE REPLACED BY A RESUPPLY VEHICLE. A SEC-MINTED CYLTNDRICAT, 

SECTION. ATTACHED AFT OF THE MISSION MODULE CONTAINS MISSION EQUIPMENT 

AND. A DOCKING ADAPTER AS NELL AS A BATTERY AND REACTION CONTROL 

EXPENDABLES FOR MAINTENANCE IN ORBIT BETVTEN SEPARATIOND RESUPPLY. 

CONFIGURATION A VEHICLES ARE NOT RESUPPLIED WITH CAMERAS BUT ONLY 

WITH FILM AND THE TRANSPORTSYSTM. THEREFORE, CUT AND SPLICE 

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CONTAINS AN ACQUISITION AND TRACKING SYSTEM CONSISTING OF RADAR AND 

OPTICS UTILIZED DURING THE RENDEZVOUS AND DOCKING SEQUENCE. BECAUSE 

OF THE LONG ORBIT LIFETIME, A SINGLE-AXIS. PROGRAMMABLE SOLAR ARRAY MODULE 

REPLACES THE FUEL CELL MODULE. FOR PRIMARY POWER. THIS MAINTAINS 

THE MAXIMUM NUMBER OF MISSION SUPPORT FUNCTIONS IN ORBIT AT ALL•IrMES 

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SHADED PORTION OF THE SATELLITE, IS IATINCHED BY THE TIM 

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IN ADDITION TO THE EXPENDABLES, THIS COP ALSO RESUPFITES 

THE CA-7.-7.RA MECHANICS. THE VEHICLE IS LAUNCHED. ON THE TITAN IIID 

BOOSTER AND PROVIDES EXPENDABLES FOR 35 DAYS IN ORBIT. AT THE END 

OF THAT TE!".

.E THE EXPENDABLE MODULES (REPRESENTED BY THE SHADED AREA) 

ARE SEPARATED FROM THE MISSION. MODULE TO BE REPLACED BY A RESUPPLY 

VEHICLE. A SEGMENTED CYLINDRICAL SECTION ATTACHED AFT OF THE MISSION 

MODULE CONTAINS.MISSION•EQUIPNTAT AND. A DOCKING ADAPTER AS WELL AaA-.. 

BATTERY AND REACTION CONTROL EXPENDABLES FOR MAINTENANCE Ill PERIODS 

BETWEEN SE?ARATION AND SUBSEQUENT RESUPPLY. CONFIGURATION B VEHICLES 

ARE RESUPPLIED WIT} 1 CAMERAS AS WELL AS FILM AND A .TRANSPORT SYSTEM. 

THE DOCKING. - INTERFACE TFEREFORE REQUIRES ONLY A LOCATING AND LOOKING 

MECHANIST F.R THE :CAMERA SYSTEM 'ID- L ASSURE ACCURATE • ALIGIE..1. 73.IT. • 

NOTRELEASED DESTROY NO LATER THAN 

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IT CONTAINS - AN ACQUISITION AND TRACKING SYS'S: CONSISTING OF 

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TRACKING SOLAR ARRAY MODULE REPLACES THE. FUEL CELL MODULE IN 

THE INITIAL - VEHICLE BECAUSE OF THE LONG ORBIT LIFETIME. THIS 

CONCEPT MAINTAINS THE MAY1=•IIUMBER OF MISSION SUPPORT FUNCTIONS 

IN.ORBITAT ALL TIMES AND RESUPPLIES ONLY.NECESSARY 'EXPENDABLESAND THE MINIMUM MISSION EQUIPMENT. 
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THE .4.L'ERNATE RESUPPLY VEHICLE, REPRESENTED BY THE RIGHT—H1 - ,2D 

SHADED PORTION OF THE SATELLITE, IS LAUNCHED BY THE TITAN IILB 

WITH TEE, AGENA UPPER STAGE. AFTER MATING WITH T;-1E :MISSION NODULE 

THE PROPELLANTS REMAINING IN THE AGENA TANK ARE UTILIZED FOR ORBIT -. 

ADJUST BY USE OF THE ISPS ENGINES. A FUEL CELL MODULE AND OHLY TWO 

RVs ARE PROVIDED-WITH THIS REST:PPLY VEHICLE BECAUSE OF THE, LIMITED 

(36 DAYS) ORBITAL LIFETIME AND BOOSTER SYSTEl WEIGHT CAPABILITY 

LIMITATIONS. OTHERWISE THE ELECTRICAL., AND ELECTRONIC COMPONENTS 

ARE THE. SAME AS THOSE INCORPORATED IN THE TIIID—LAUNCIED RESUPPLY 

VEHICLE. 
NRO APPROVED FOR 

RELEASE 1 JULY1P15 

MISSI0: COT 

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SUBSEQUENTLY 'REPLACED BY A RESUPPLY VEHICLE. THE SEGMENTED 

CYLINDRICAL SECTION AFT OF THE NISSIOU NODULE CONTAINS ONLY 

EQIUIPMENT AND EXPENDABLES NECESSARY FOR MAINTEI.L.CE (HOUSEKIIBING). 

FUNCTIONS AND A DOCKING ADAPTER. CONFIGURATION C RESUPPLY VEHICLES 

REPLACE THE COMPLETE CANERAIFIL?:,/TRANSPORT SYSTF.,:, THE STAR TRA,73KER 

AND RATE GYRO PREVIOUSLY CONTAINED IN THE. MISSION NODULE, AND ALL 

THE NECESSARY EXPENDABLES. THE DOCKING INTERFACE REQUIRES A LOCATING 

AND LOCKING MECHANISM FOR ACCURATE•ALIGNMENT OF THE CA2.aRA•SYSIT2.1.WITH 

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AND EXPENDABLES FOR UP TO 130 DAYS, IS LAUNCHED BY THE TIM) VEHICLE. A 

SINGLE—AXIS TRACKING SOLAR ARRAY MODULE REPLACES THE FUEL CELL MODULE IN 

THE INITIPT,VEHICLE BECAUSE OF THE. LONG ORBIT LIFETIME. THIS VEHICLE ALSO 

CONTAINS AN ACQUISITION AND TRACKING' SYSTE,I, CONSISTING OF RADAR AND OPTICS, 

UTILIZED DURING THE RENDEZVOUS- AND DOCKING -.SEQUENCE, THIS • CONVIGURATION• 

MAINTAINS ONLY THE MI1-n1,111I-1 1`1111-isER 0.7.‘'. HOUSEKEEPING FUNCTIONS IN ORBIT, 

ATTACHED TO THE MISSIONMODULE - .97,7•7EE-21 SEPARATION AND RESUPPLY. MOST OF 

THE MISSION EQUIPMENT, THE COMTPLI-OTE CA;M.ERA SYSTEM, AND. THE STAR TRACKER ,- 

AND RATE GYRO ARE RESUPPLIED WITH EACH SUBSEQUENT LAUNCH. 
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NRO APPROVED FOR 

RELEASE 1 JULY' 

HOUSE-KEEP PPOCRAY,Y_FR,.- 

A TT I TIT DE RFFERY'NCF & ELECTRONICS; 

REACTION CONTROL, AND BATTERY 

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(8)• I,E5 itv MISSION TT&O, COMPUTERS, ATTITUDE 

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AGENA UPPER STAGE. PROPELLANTS REMAINING IN THE AGENA TANK PROVIDE 

THE IMPULSE, FOR ORBIT ADJUS7•11.711T AFTER EATING WITH THE MISSION MODULE. 

A FUEL CELL MODULE ANT) ONLY TC.TO RVs ARE PROVIDED WITH THIS RESUPPLY 

VEHICLE BECAUSE OF THE LIMITED (32 DAYS) ORBITAL LIFF,TI:::?: AND BOOSTER 

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THIS CHART PRESENTS A POST-DORIAN CONCEPT REPRESENTED BY 

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THE RESUPPLY VEHICLE '..aLL BE LAUNCHED FR.011 THE TITAN HID BOOSTER 

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FOR P-66 AND MOL, SIX LAUNCHES PER YEAR OF 30: DAY LIFE VEHICLE WERE ASSUMED. FOR P-66 RESUPPLY , 

AN INITIAL LAUNCH FOLLOWED BY THREE 1,30-":1/10 DAY RESUPPLY VEKICLES VAS USED. 

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P-66 $378,000,000 $234,000,000 

P-66 RESUPPLY 

CONFIGURATION A $146,000,000 $466,000,000 

CONFIGURATION B $149,000,000 $463,000,000 

CONFIGURATION C $162,000,000 $450,000,000 

D F 

'R.EELASE 1 JULY 
NRO APPROVED FOR 

RELEASE 1 JULY 2015 NOTRELEASED DESTROYNO LATER THAN 

CD 

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AMSDO O9SV37?`! NVELL 431V 1 1 ON 

ROM ANNUAL RECUERI NO- HARDZARE COST 

(WITH EXPECTED KILIABI LIT./ ) 

THE EXPECTED LIFE OF SYS T1.3 INFLUENCES ANNUAL HARDWARE COST. BASET) 

ON THE Kt SS TON MODULE RELIABILITY ASSIGNMENT FURNISHED TO LOCKHEED IN 

CONNECTION WITH THE P66 STUDY, - IT APPEARS THAT TWO MISSION MODISTE 

LAUNCHES PER YEAR WOULD BE REQUI FED . THIS FACTOR INCREASES TFD COST 

OF RESUPPLY ABOUT .,30 , CO 0 „COO. PER YEAR. . 
D F 

RELEASE 1 JULY 2 

ROM ANNUAL RECUHRIG HARU;TARE COST 

(WITH EXPTIID RFLIABILITY) 

SYSTEM ANNUAL COST SAVINGS VS. MOL 

MOL $673,000,000 

P-66 $426,000,000 $247,000,000 

P-66 RESUPPLY $191,000,000 $482, 000 , 000 

(CONFIGURATION C) 

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$1o0 m p-66a DEy. (65 24 P-66) 

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DtCISION 

POINT, 
N 0 APPROVED FOR 

RELEASE JUL45 

SUNEARY 

o PRELIMINARY STUDIES HAVE SHOWN THREE TECHNICALLY FEASIBLE 

CONCEPTS FOR UNMANNED DORIAN RESUPPLY. 

o BOTH THE LMSC P-66/P-66 RESUPPLY CONCEPTS CAN PROVIDE DORIAN 

OPERATIONAL CAPABILITY EARLIER THAN MOL. 

o DEVELOPMENT SAVINGS WOULD EXCEED $1,000,000,000 AND ANNUAL 

OPERATIONAL SAVINGS WOULD RUN $200,000,000 - $500,000,000 LESS 

THAN MOL. 

NO NEW TITAN BOOSTERS ARE REQUIRED FOR THE UNMANgED APPR=HES. 

DEVELOPMENT OF P-66/P,66 RESUPPLY1r;OULD MAKE LARGE AMOUNT OF 

. . 

DEVELOPMENT FUNDS AVAILABLE .FOR POST DORIAN SYSTEMS. 

RESUPFLTDEV4OPME4T LAYS FONDATION F,OR POST-DORIAN 

tiEsio0/0,0zAToN 
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