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19850009763 

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Impact of Lunar 

and Planetary 

Missions on the 

Space Station 

a:: ff:1 ~I : • 111111111111111111111111111111111111111111111 

NF01848 

ENGINEERING, INC. 

CONTRACT NO. N AS 9 -17176 

i/45'/l cR - \. \ g31 

elL 

LIBRARY COpy 

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LANGLEY RESEARCH CENTER 

LIBRARY, NASA 

HAMPTOI'1. VIRGII'i!A 

SEPTEM&:R 21, 1984 / " ,. 

REPO~ NO. 84-8sa 

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BEST 

AVAILABLE 

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PRELIMINARY STS LOGISTICS REPORT 

IMPACT OF LUNAR AND PLANETARY MISSIONS 

ON THE SPACE STATION 

PREPARED FOR 

PLANETARY EXPLORATION DIVISION , 

JOHNSON SPACE CENTER 

BY EAGLE ENGINEERING 

REPORT NUMBER 84-85B 

CONTRACT NUMBER NAS9-17176 

SEPTEMBER 21, 1984 

N'P-;../907L ~ 
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· DRAFT 30 MINUTE PRESENTATION 

1. TITLE 

2. TASK DEFINTION 

3. LUNAR OPERATIONS IMPACTS 

4. LUNAR OPERATIONS IMPACTS 

5. PLANETARY MISSIONS IMPACTS 

6. IMPACT VERSUS NO IMPACT SPACE STATION 

7. STUDY GROUNDRULES AND ASSUMPTIONS 

8. STUDY GROUNDRULES AND ASSUMPTIONS 

9. STUDY GROUNDRULES AND ASSUMPTIONS 

10. LUNAR BASE DESCRIPTION 

11. UNLOADING MODULE ON LUNAR SURFACE 

12. LUNAR BASE BUILDUP SCHEME 

13. LUNAR SCENARIO, EXPENDABLE LANDER 

14. LUNAR SCENARIO, MANNED MISSION 

15. COMMON MODULE AND TRAILER 

16. LUNAR CRANE 

17. VEHICLE DESCRIPTIONS 

18. VEHICLE DESCRIPTIONS 

19. AOTV STACK DEPARTING SPACE STATION WITH COMMON MODULE 

20. AOTV 

21. OTV SCHEDULED MAINTENANCE OPERATIONS 
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22. OTV SCHEDULED MANITENANCE OPERATIONS 

23. OTV MANNED MODULE 

24. E-LANDER, R-LEM, LARGE H2 TANK, AND LUNAR LANDER MANNED 

MODULE 

25. LUNAR BASE LAUNCH REQUIREMENTS 

26. DETAILED LAUNCH MANIFEST AND LUNAR MISSION SCHEDULE 

27. DETAILED LAUNCH MANIFEST AND LUNAR MISSION SCHEDULE 

28. DETAILED LAUNCH MANIFEST AND LUNAR MISSION SCHEDULE 

29. DETAILED LAUNCH MANIFEST AND LUNAR MISSION SCHEDULE 

30. COMMENTS AND CONCLUSIONS - LUNAR BASE BUILD-UP AND OPERATIONS 

31. MARS SAMPLE RETURN SCENARIO 

32. MARS SAMPLE RETURN SPACE STATION CHECKOUT 

33. CERES OR KOPFF SAMPLE RETURN SCENARIO 

34. CERES OR KOPFF STACK 

35. OMV RETURNS SAMPLE TO QUARANTINE MODULE 

36. GLOVE BOX INSIDE QUARANTINE MODULE 

37. MERCURY ORBITER SCENARIO 

38. TITAN PROBES/SATURN ORBITER SCENARIO 

39. PLANETARY MISSIONS PERFORMANCE SUMMARY 

40. SHUTTLE LOADS REQUIRED FOR PLANETARY MISSIONS 

41. COMMENTS AND CONCLUSIONS - PLANETARY MISSIONS 
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IMPACT OF LUNAR AND PLANETARY MISSIONS 

ON THE SPACE STATION 

PREPARED FOR 

PLANETARY EXPLORATION DIVISION, 

JOHNSON SPACE CENTER 

BY EAGLE ENGINEERING 
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TASK DEFINITION 

LUNAR BASE MISSIONS 

o LUNAR BASE CONCEPTUAL DEFINITION 

o LUNAR ACTIVITIES LOGISTICS 

o DEFINE LUNAR SCENARIOS 

o SPACE STATION ELEMENTS REQUIRED 

o SPACE STATION FUNCTION 

o PRELIMINARY PROGRAM DEFINITION 

o UNCERTAINTIES IMPACT 

PLANETARY MISSIONS 

o BASELINE EXPLORATION PLAN 

o UNMANNED MISSION DEFINITION 

o PLANETARY MISSION SCENARIOS 

o SPACE STATION ELEMENTS REQUIRED 

o SPACE STATION FUNCTION 

o PHASED PLAN 

o UNCERTAINTIES IMPACT 
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LUNAR OPERATIONS IMPACTS 

o THE IMPACT OF THE LIJNAR BASE ON THE SPACE STATION IS ONE OF SCALE - FLIGHT 

OPERATIONS MUST BE DONE f10RE FREQUENTLY J WITH LARGER VEHICLES 

PRIOR TO LUNAR OXYGEN PRODUCTION: EVERY TWO MONTHS FLIGHT OPERATIONS ARE: 

0' ONE UNMANNED LAUNCH VEHICLE (ULV) TANKER LAUNCH OF LOX/LH2 TO SS (100 M. 

TONS) 

o ONE SHUTTLE AFT CARGO CARRIER (ACC) LAUNCH WITH PAYLOADS J LUNAR LANDERS J CREWS J ETC 

o AT THE SPACE STATION - TWO OTV'S J THE LANDER AND PAYLOAD(S) ARE CHECKED OUT 

& MATED INTO A STACK· THE OTV'S & LANDER ARE FUELED WITH LOX/LH2 

o THE LUNAR MISSION IS FLOWN AND THE OTV'S (PLIIS MANNED MODULE ON MANNED SORTIES) RETURN TO SPACE STATION FOR DOCKING AND RECOVERY 

AFTER LUNAR 02 PRODUCTION STARTS J FLIGHT OPERATIONS INCLUDE: 

o TWO TANKER LAUNCHES 

PLUS 

o TWO STS LAUNCHES 

FOR EVERY 

o THREE LUNAR MISSIONS 
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LUNAR OPERATIONS IMPACTS 

SPACE STATION HARDWARE 

o HANGERING AND STORAGE FOR 4 OPERATIONAL OTV'S 

o GANTRY'S FOR PREPARING TWO STACKS SIMULTANEOUSLY OF 2 OTV'S PLUS LUNAR LANDER~ PLUS CARGOS (UP TO 3 ELEMENTS). STACKS WILL BE 30 TO 40 M (100 TO 135 FT) IN LENGTH & UP TO 15 M WIDE 

o PROPELLANT DEPOT WITH CAPACITY OF AT LEAST 2 TANKER LOAD UNITS OF 100 M TONS EACH 

o EQUIPMENT TG FUEL FROM DEPOT - 2 OTVS PLUS LANDER WHILE MATED IN STACK FOR 

DEPARTURE. 98 M TONS LOX/LH2 TOTAL PER MISSION 

o ADDITIONAL HABITABILITY flODULE FOR HOUSING 2 TO 4 EXTRA SPACE STATION CREW 

AND TEMPORARY BILLETING FOR 4 TO 6 TRANSIENT LUNAR BASE PERSONNEL 

o 2 OMVS FOR FLIGHT SUPPORT 

SPACE STATION MANPOWER: EACH SIXTY DAYS THE SPACE STATION flUST PROVIDE FACILI- TIES AND MANPOWER FOR: 

o TRAFFIC CONTROL 

- RENDEZVOUS/DOCKING ACTIVITIES - 1 TANKER~ 1 SHUTTLE~ 1 AFT CARGO CARRIER PAYLOAD~ 2 OTV'S - 1 LUNAR DEPARTURE 

- 1 DEPOT ELEMENT REMOVAL FOR DEORBIT 

o VEHICLE CHECKOUT~ MAINTENANCE AND REPAIR 

- 2 OTV SORTIES 

- 6 OMV SORTIES (4 DOCKING~ 1 STACK DEPARTURE~ 1 EMPTY DEPOT DEPARTURE FOR DEORBIT INITIATION) - 1 SET OF LUNAR VEHICLES & PAYLOADS (E-LANDER~ OMM~ E-LLMM/ASCENT~ COMMON MODULE) 

o STACK ASSEMBLY AND FUELING SEQUENCE 
PLANETARY MISSIONS IMPACTS ON THE SPACE STATION 

REQU I REMENTS MARS KOPFF CERES MERCURY TITAN 

SAMPLE SAMPLE SAMPLE ORBITER PROBESI 

RETURN RETURN RETURN SATURN 

ORBITER 

o SPACE STATION HARDWARE REQUIRED 

No. OF OTVs EXPENDED 

(NOT RETURNED) 0 1 1 0 1 

I No. OF OTV REFURB. KITS 1 2 2 1 1 

GANTRY TO STACK TWO STAGES YES YES 

1 CHECKOUT EQUIP. FOR TWO STAGE 

STACK YES YES 

1 QUARANTINE MODULE YES YES YES 

ADDITIONAL POWER, ~ 5 5 5 

I ADDITIONAL THERMAL CONTROL, 

NO. OF STANDARD MODULES 1 1 1 

] o SPACE STATION MANHOURS REQUIRED 

OTV REFURBISHMENT 52 103 103 52 52 

AEROBRAKE REMOVAL 21 21 21 

OTV/PAYLOAD INTEGRATION & CIO 11 21 21 11 11 

FUEL, RELEASE, AND LAUNCH 24 36 36 24 24 

RENDEZ/RETRIEVE OTV USING OMV 12 12 12 12 

SHUTTLE RENDEZ/PAYLOAD REMOVAL 2 2 11 2 2 

ULV PROPELLANT DELIVERY 7 17 18 7 10 

SAMPLE RETRIEVAL USING OMV 8 8 8 

SAMPLE ANALYSIS & SHIPMENT 24 16 16 

TOTAL MISSION MANHOURS 138 235 246 105 118 
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LUNAR & PLANETARY STUDY 

GROUNDRULES & ASSUMPTIONS 

1· THE SPACE STATION CAN STORE AND TRANSFER LOX AND LH2 TO THE ORBITAL TRANSFER VEHICLE (OTV) IN ORBIT. 

2· AEROBRAKING WILL BE A MATURE TECHNOLOGY AND IS INCORPORATED IN THE OTV 

DESIGN· 

3· THE OTV WILL USE LOX/LH2 PROPELLANT· 

4· Isp = 460 SEC WITH 1% START/STOP LOSSES YIELDING EFFECTIVE Isp = 455·4 SEC· 

5· ALL STAGES~ LUNAR LANDERS~ ETC.~ WILL BE LOX/LH2 UNLESS STRONGLY CONTRAINDICATED· 

EXCEPTION - EXPENDABLE ASCENT STAGE WILL USE STORABLES. 

6. BOIL OFF RATE FOR CRYOGENIC STAGES IS 55 KG/DAY OF LH2 PER STAGE· 

7· CARGO UNITS FOR THE LUNAR BASE WEIGH A MAXIMUM OF 1R METRIC TONS. 

8. THE LUNAR ORBIT SERVICE STATION WT = 35 M TONS· IT CAN STORE AND TRANSFER 

LH2 AND LOX IN ORBIT· ON-ORBIT RE-REFRIGERATION CAPABILITY FOR CRYOGENICS 

IS ASSUMED· 

9· OTV ELEMENTS CAN BE "STACKED" I·E· USED AS TWO IDENTICAL STAGES~ ONE 

STAGING BEFORE THE OTHER IGNITES· 

10· LUNAR SURFACE STORAGE~ TRANSFER (INTO LANDERS)~ AND RE-REFRIGERATION OF 

CRYOGENICS BOTH LOX AND LH2 IS ASSUMED AFTER 02 PRODUCTION COMMENCES. 
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LUNAR & PLANETARY STUDY 

GROUNDRULES & ASSUMPTIONS 

(CONTINUED) 

11· MAJOR MAINTENANCE OF THE LANDER IS AVAILABLE EITHER AT THE LUNAR BASE OR AT 

THE LUNAR ORBIT SERVICE STATION· 

12· FOR THE PURPOSE 

DELIVERY OF THE 

IN THE REUSABLE 

NOT BE EXAMINED 

OF THIS STUDY: LUNAR 02 WILL BECOME AVAILABLE AFTER 

PRODUCTION PLANT TO LUNAR SURFACE· THIS 02 WILL BE USED 

LUNAR LANDER, BUT DELIVERY OF LUNAR 02 TO EARTH ORBIT WILL 

IN THIS STUDY· 

13· THE OTV WILL BE SIZED TO PERFORM ANY OF THREE REFERENCE MISSIONS: 

A· DELIVER 9 M TONS TO GEOSYNCHRONOUS ORBIT, RETURNING EMPTY USING A 

SINGLE STAGE· 

B· DELIVER 6 M TONS ROUND TRIP TO GEOSYNCHRONOUS ORBIT, USING A SINGLE 

STAGE· 

C· DELIVER 18 M TONS PAYLOAD PLIJS A LUNAR LANDER (SIZED TO LAND THE 

PAYLOAD) TO LUNAR ORBIT, USING TWO OTV STAGES IN TANDE~1· BOTH OTV 

STAGES ARE RETURNED TO THE SPACE STATION. 

14· THE SAME OTV's (WITH A KICK STAGE WHERE APPROPRIATE) CAN BE USED FOR THE 

PLANETARY MISSION· ALTERNATE EXPENDABLE STAGES (SUCH AS CENTAUR) CAN ALSO 

BE CONSIDERED· WHERE FEASIBLE, OTV STAGES ARE RECOVERED· 

15· THE SPACE STATION ALTITUDE = 500 KM (270 N MI)· 

16· LUNAR OPERATIONS WILL NOMINALLY HAVE A LAUNCH WINDOW EVERY NINE DAYS. 
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LUNAR & PLANETARY STUDY 

GROUNDRULES & ASSUMPTIONS 

(CONTINUED) 

17· LUNAR ORBIT OPERATIONS WILL BE AT 200 KM LUNAR ALTITUDE (109 NAUT. MI.). 

18· LUNAR BASE WILL BE NEAR EQUATORIAL (+ 4°). 

19· AFTER STAGE 1 BURNOUT OF OTV~ SECOND STAGE COASTS AROUND (NEARLY) TO 

PERIGEE BEFORE IGNITION TO MINIMIZE G-LOSSES (2 BURN OPTION). 

20. PROPELLANT TRANSFER TO R-LEM TAKES PLACE ON LUNAR SURFACE-H2 TANK IS 

LANDED INTACT AND STORED ON THE SURFACE FOR REFRIGERATION AND PUMPING· 

21· No LUNAR ORBIT SERVICE STATION IS ASSUMED· 

22· LOX/LH2 MIXTURE RATIOS OF 7:1 ARE USED FOR ALL LUNAR LANDERS. 

23· AFT CARGO CARRIER ON SHUTTLE EXTERNAL TANK IS ASSUMED AND USED· 

24· SHUTTLE DERIVED-UNMANNED LAUNCH VEHICLES (ULV) NEEDED AND ASSUMED FOR 

PROPELLANT TANKERS· LAUNCH 100 METRIC TON LOX/LH2 TO SPACE STATION PER 

FLIGHT· 

25· LAUNCH COST ESTIMATES (1984 DOLLARS) ULV -$133 MILLION/LAUNCH 

STS -$100 MILLION/LAUNCH 
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LUNAR BASE DESCRIPTION 

THE FINISHED LUNAR BASE CONSISTS OF: 

o 5 HABITABILITY MODULES 

o 5 RESEARCH UNITS 

- GEO-CHEMICAL LABORATORY 

- CHEMICAL/BIOLOGY LABORATORY 

- GEO-CHEMICAL/PETROLOGY LABORATORY 

- PARTICLE ACCELERATOR 

- RADIO TELESCOPE 

o 3 PRODUCTION PLANTS (PRECEEDED BY PILOT PLANTS) 

- OXYGEN PLANT 

- CERAMICS PLANT 

- METALLURGY PLANT 

o 2 SHOPS 

o 3 POWER UNITS 

o 1 EARTHMOVER/CRANE 

o 3 MOBILITY UNITS W/ TRAILERS 

o 18 PERMANENT PERSONNEL 

ALL ASSEMBLED OVER A 10 YEAR BUILD-UP PERIOD 
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LUNAR BASE BUILD-UP SCHEME 

o FIRST 8 YEARS - UNMANNED EXPLORATION & MAPPING 

o BASE BUILD-UP STARTS IN 2005 

- 1ST YEAR - HABITAT POWER UNIT, CRANE, & 1 LABORATORY DELIVERED-UNMANNED 

- 2 MANNED SORTIES FLOWN TO PREPARE BASE-ALL RETURN 

- 2ND YEAR - MOBILITY UNIT & 02 PILOT PLANT DELIVERED-2 MORE MANNED SORTIES SMALL PERMANENT CREW STAYS 

- 3RD YEAR - 1 MORE LAB & MISC. EQUIPMENT DELIVERED-UNMANNED 

- 3 MANNED SORTIES, ENTIRE CREW OF ONE MISSION STAYS SO THAT 

PERMANENT CREW HAS A LAUNCH VEHICLE ON SURFACE 

- 4TH YEAR - OPERATIONAL OXYGEN PRODUCTION PLANT DELIVERED, REUSABLE LANDER/ 

LAUNCHER (R-LEM) DELIVERED & BECOMES OPERATIONAL . 

- 5TH YEAR - HEAVY FLIGHT SCHEDULE TO DELIVER REMAINDER OF BASE ELEMENTS, THROUGH SLACKING OFF AS TO 6 t1ANNED CREW ROTATION SORTIES PER YEAR AS 10TH YEAR BASE APPROACHES FULL GROWTH - f1ATURE BASE BY 10TH YEAR. 
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LUNAR SCENARIO, EXPENDABLE LANDER 

1. Stack departs SS 

2. First stage burn 

3. Second stage burn 

4. 

5. 

6. 

7. 

8. 

9. 

10. 

First stage returns to SS 

Circularized in lunar orbit 

Expendable lander places Common 

Module on lunar surface 

Second stage returns to Earth 

Aerobraking 

Circularized above SS orbit 

Second stage returns to SS 

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LUNAR SCENARIO, MANNED MISSION 

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3. 

4. 

5. 

6. 

7. 

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10. 

11. 

Stack departs SS 

Trans-lunar injection burn 

First stage returns to SS 

Second stage, lander, and manned 

module insert into lunar orbit 

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Lander descends 

Ascent module departs 

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Ascent module rendezvous with second 

stage 

Second stage returns to-earth with 

ascent module discarded 

Aerobraking 

Circularization above the SS orbit 

Rendezvous with SS 

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STS ELEfVENTS 

LUNAR SPACE TRANSPORTATION SYSTEM 

ELEMENT DESCRIPTION ELEMENT FUNCT ION 

AND DES I GN GOf-\lS 

=====================================================================================================: 

BASE ELEMENT COMMON MODULE 

E-LANDER 

LUNAR LANDING MANNED MODULE (LLMM) . 

E-LAUNCHER 

OTV MANNED MODULE (OMM) 

AERCBRAK I NG ORB IT f-\l TRANSFER VEHIQE (AOTV) 

LENGTH = 11 M. ; DIAMETER = 4.6 M. 

WEIGHT =17.5 M. TON 

DIAMETER = 8.2 M. ; HEIGHT = 7 M. 

WEIGHTS: 

BURN OUT = 3.8 M.TON 

USABLE PROPELLANT = 13.6 M. TON LOX/LHZ PROPELLANT 

COMMON LUNAR HClJS ING AND/OR 

LftBORATORY UN IT 

EXPENDABLE LUNAR LANDER 

DESIGNED TO DELIVER 17.5 M. TON TO LUNAR SURFACE 

LENGTH = 3.6 M. ; DIAMETER = 2.6 M MODULE TO CARRY CRBW OF 4 TO 

WEIGHT = 3.25 M.TON (WITH 4 CREW) LUNAR SURFACE, AND RETURN--

DIAMETER = 3.6 TO 5 M. 

HEI GHT = 2 M. 

WEIGHTS: 

BURN OUT = 2.6 M. TON 

USABLE PROPELLANT = 5 M.TON 

PUMP FED,STORftBLE PROPELLANT 

LENGTH = 2.6 M. ; DIAMETER = 3 M. 

WEIGHT = 5.5 M. TON (WITH 4 CREW) 

DIAMETER = 12.2 M. (AERO SHIELD) LENGTH = 5 M. 

WEIGHTS: 

BURN OUT = 7.0 M.TON 

USABLE PROPELLANT = 42 M.TON LOX/LHZ PROPELLANT 

LIMITED LIFE SUPPORT 

--NOT REUSED--

EXPENDAB LE LAU NCH ER TO CARRY LLMI 

PLUS .5 TON PAYLOAD FROM LUNAR SURFACE TO LUNAR ORB IT 

CRBW MODULE FOR OTV, TO CARRY 

PERSONNEL FROM ORBIT TO ORBIT 

-SH I RT SLEEVE EV IRONMENT . ---REUSftBLE---

OTV SIZED TO DELIVER 35 M.TON TO 

LUNAR ORBIT AND RETURN EMPTY 

US ING lWO OTVs BOTH RETURNED 

BY AEROBRAKING -- REUSftBLE--
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STS ELErv£NTS 

LUNAR SPACE TRANSPORTATION SYSTEM 

ELEMENT DESCRIPTION ELEMENT FUNCTION AND DES IGN GOALS 

===================================================================================================== 

REUSABLE LUNAR LANDER/LAUNCHER (R - LEM) 

REUSABLE LUNAR LANDING MANNED ~DDULE (R - LLMM) 

LARGE OMM 

H2 TRANSFER TANK 

SHUTTLE ( STS ) 

SHUTTLE/AFT CARGO CARRIER ( STS-ACe) 

SHUTTLE DERIVED UNMANNED LAUNCH VEHICLE (SD-ULV) 

DIAMETER = 10 M. ; HEIGHT = 7 M. WEIGHTS: BURN OUT = 5.2 M.TON USABLE PROPELLANT = 30 M.TON LOX/LHZ PROPELLANT 

LENGTH = 5 M. ; DIAMETER = 2.6 M. WEIGHT = 5 M.TON (WITH 6 CREW) 

LENGTH = 4 M. ; DIAMETER = 3 M. WEIGHT = 8 M. TON (WITH 6 CREW) 

VOLUME = 57 CU.M. WEIGHTS: 

EMPTY WT.=1 M.TON 

FULL WT.= 5 M.TON 

---- LAUNCH VEHICLES ---

PL TO SPACE STATION = 25 M.TON 

PL TO SPACE STATION = 22 M.TON 

USABLE LOX/LHZ TO SPACE 

STATION = 100 M. TON 

LUNAR BASED VEHICLE FOR TRANSPOR FROM LUNAR SURFACE TO LUNAR ORBIT AND BACK - USING LUNAR PRODUCED OXYGEN. DESIGNED FOR 17.5 TON PL DOWN, 0 UP -- OR -- 14 TON PL DOWN, 7 TON UP. - A 5 TON TANK OF LHZ IS PlSO· CARRIED DOWN ON EACH LANDING' 

LUNAR BASED MANNED,MODULE FOR U~ 

WITH R-LEM; NORMAL CRBN 6,MAX 1 

LARGER OMM REPLACErvENT; FOR ORBITAL TRANSPORT OF CRBNS IN 

MATURE LUNAR BASE OPERATIONS' NORMAL CREW 6, MAX. 10 

TANK OF LIQUID HYDROGEN FUEL FOF R-LEM (WITH LUNAR 02) - ONE 

DELIVERED TO LUNAR SURFACE STORAGE EACH FLIGHT 

REUSABLE LAUNCH VEHICLE FOR VPlUABLE CARGOS AND PERSONNEL 

SHUTTLE WITH A CARGO COMPARTMENl ON AFT END OF EXTERNAL TANK -FOR OVERSIZE CARGOSUNMANNED LAUNCHER DESIGNED USINC 

SHUTTLE ELEMENTS,--USED FOR LAUNCHING LOX/LHZ PROPELLANT T( ORBITAL STORAGE DEPOT 
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DURATION 1 DAY 

DURATION 2 DAYS 

DURATION 1 DAY 

DURATION 1 DAY 

DURATION 2 DAYS 

OTV SCHEDULED MAINTENANCE OPERATIONS 

REMOVE AND REP~A~~O~~~L CELL/BATTERY 

REMOVE AND REPLACE ENGINE 

4 PEOPLE 

OTV UNSCHEDULED MAINTENANCE OPERATIONS 

REMOVE AND REPLACE AVIONICS MODULE 2 PEOPLE 

REPAIR AEROBRAKE 4 PEOPLE 

REMOVE AND REPLACE TANK MODULE 4 PEOPLE 

5: 40 MANHOURS 

65:30 MANHOURS 

5:30 MANHOURS 

26:20 MANHOURS 

58: 15 MANHOURS 
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OTV TURNAROJND OPERAT IONS 

NORMAL OTV TURNAROUND DURATION 4 DAYS 2 PEOPLE 

o RETRIEVAL AND CAPTURE 

o SAFING 

o BERTHING 

o INSPECTION 

o REMOVE AND REPLACE ACS MODULES 

o SYSTEMS TEST 

o PAYLOAD INTEGRATION 

o TRANSFER PROPELLANT 

o PRELAUNCH 

o LAUNCH 

69: 40 MANHOURS 
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LUNAR B/~SE LAUNCH REQUIREMENTS 

900 .-----------------~----------------------------------------~ 

800 

700 

600 

500 

400 

300 

200 

100 

O rr rr r/ // r// r/.c r.c/ r.c.c r.c/ r/.cl i I Iii I I Iii 

2005 2006 2007 2008 2009 2010 2011 2012 2013 2014 

YEAR 

IZZJ LOX/LH2 PROPELLANT lSSI CARGOS 
1 DETAILED LAUNCH MANIFEST AND LUNAR MISSION SCHEDULE 

MONTH LAUNCH TYPE CARGO MANIFEST CARGO LUNAR FL IGHT NO. WT. FL IGHT TYPE 

M. TON NO. 

====================================================================================================== 

------------- YEAR 2005 --------------

JAN 5-1 SD-ULV LOX/LHZ PROPELLANT SUPPLY UNIT 100 

FEB 5-2 STS-Ace E-LANDER,+BASE ELEMENT #1 21 LS-1 UNMANNED 

DELIVERY MARCH 5-3 SD-ULV LOX/LHZ PROPELLANT SUPPLY UNIT 100 

APRIL 5-4 STS-ACC E-LANDER,+BASE ELEMENT #2 21 LS-2 UNMANNED 

DELIVERY 

MAY 5-5 SD-ULV LOX/LHZ PROPELLANT SUPPLY UNIT 100 

JUNE 5-6 STS-ACC E-LANDER,+BASE ELEMENT #3 21 LS-3 UNMANNED 

DELIVERY JULY 5-7 SD-ULV LOX/LHZ PROPELLANT SUPPLY UN IT 100 

AUG 5-8 STS-ACC E-LANDER,+BASE ELEMENT #4 21 LS-4 UNMANNED 

DELIVERY SEPT 5-9 SD-ULV LOX/LHZ PROPELLANT SUPPLY UN I T 100 

OCT 5-10 STS-ACC E-LANDER,+E-LLMM/ASCENT,+OMM,+4 CREW 20 LS-5 MANNED , SORTIE NOV 5-11 SD-ULV LOX/LHZ PROPELLANT SUPPLY UN I T 100 

DEC 5-12 STS-ACC E-LANDER,+E-LLMM/ASCENT,+OMM,+4 CREW 20 LS-6 MANNED 
1 

1 

J 

J 

.I 

MJNTH LAUNCH NO. TYPE 

DETAILED LAUNCH MANIFEST AND LUNAR MISSION SCHEDULE 

CARGO MANIFEST CARGO 

WT. 

M. TON 

LUNAR 

FL IGHT 

NO. 

FL IGHT TYPE 

===================================================================================================== 

JAN 

FEB 

MARCH 

APRIL 

MAY 

JUNE 

JULY 

AUG 

SEPT 

OCT 

NOV 

DEC 

6-1 

6-2 

6-3 

6-4 

6-5 

6-6 

6-7 

6-8 

SD-ULV 

STS-ACC 

SD-ULV 

STS-ACC 

SD-ULV 

STS-ACC 

SD-ULV 

STS-ACC 

------------- YEAR 2006 --------------

LOX/LHZ PROPELLANT SUPPLY UNIT 

E-LANDER,+BASE ELEMENT #5 

LOX/LHZ PROPELLANT SUPPLY UNIT 

E-LANDER,+E-LLMM/ASCENT,+4 CREW,+2 TON 

P.L.,+ 4 TON OF AOTV ELEMENTS 

LOX/LHZ PROPELLANT SUPPLY UNIT 

E-LANDER,+BASE ELEMENT #6 

LOX/LHZ PROPELLANT SUPPLY UNIT 

E-LANDER,+E-LLMM/ASCENT,+4 CREW,+2 TON 

P.L.,+ 4 TON OF AOTV ELEMENTS 

100 

21 

100 

20 

100 

21 

100 

20 

L6-1 UNMANNED 

DELIVERY 

L6-2 MANNED SORTIE 

L6-3 UNMANNED 

DELIVERY 

L6-4 MANNED 

SORTIE 
fIONTH LAUNCH NO. 

TYPE 

DETAILED LAUNCH MANIFEST AND LUNAR MISSION SCHEDULE 

CARGO MANIFEST CARGO 

WT. 

M.TON 

LUNAR 

FLIGHT 

NO. 

FL IGHT 

TYPE 

----------------------------------------------------------------------------------------------------- -----------------------------------------------------------------------------------------------------

7-1 

7-2 

7-3 

7-4 

7-5 

7-6 

7-7 

7-8 

7-9 

7-10 

SD-ULV 

STS-ACC 

SD-ULV 

STS-ACC 

SD-ULV 

STS-ACC 

SD-ULV 

STS-ACC 

STS-ACC 

SD-ULV 

------------- YEAR 2007 --------------

LOX/LHZ PROPELLANT SUPPLY UNIT 

E-LANDER,+BASE ELEMENT #7 

LOX/LHZ PROPELLftNT SUPPLY UN IT 

E-LANDER,+E-LL~/ASCENT,+4 CREW,+2 TON P.L.,+ 4 TON OF AOTV ELEMENTS 

LOX/LHZ PROPELLftNT SUPPLY UN IT 

E-LANDER,+E-LL~/ASCENT,+4 CREW,+2 TON 

P. L.,+ 4 TON OF AOTV ELErtENTS 

LOX/LHZ PROPELLftNT SUPPLY UN I T 

E-LftNDER,+E-LLMM/ASCENT,+4 CREW,+2 TON P. L.,+ R-LL~ 

R-LEM ELErtENTS,+SECOND R-LLMM,+HZ TANK LOX/LHZ PROPELLftNT SUPPLY UN IT" 

100 

21 

100 

20 

100 

20 

100 

21 

10 

100 

L7-1 UNMANNED 

DELIVERY 

L7-2 MANNED· SORTIE 

L7-3 MANNED SORTIE 

L7-4 MANNED SORTIE 
J 

1 

rvtlNTH LAUNCH 

NO. 

TYPE 

DETAILED LAUNCH MANIFEST AND LUNAR MISSION SCHEDULE 

CARGO MANIFEST CARGO 

WT. 

M.TON 

LUNAR 

FL IGHT 

NO. 

FLIGHT 

TYPE 

"----------------------------------------------------------------------------------------------------

-----------------------------------------------------------------------------------------~---------­

JAN 

FEB 

MARCH 

APRIL 

MAY 

JUNE 

JULY 

AUG 

SEPT 

OCT 

NOV 

DEC 

------------- YEAR 2008 --------------

8-1 STS-ACC E-LANDER,+BASE ELEMENT #8 21 L8-1 

8-2 SD-ULV LOX/LHZ PROPELLANT SUPPLY UNIT 100 

8-3 STS-ACC E-LANDER,+BASE ELEMENT #9 21 L8-2 

8-4 SD-ULV LOX/LHZ PROPELLANT SUPPLY UNIT 100 

NOTE---- LUNAR CREW DELIVERED TO SPACE STATION ON SCHEDULED-RESUPPLY STS LAUNCH 

L8-3 

8-5 SD-ULV LOX/LHZ PROPELLANT SUPPLY UN IT 100 

UNMANNED 

DELIVERY 

UNMANNED 

DELIVERY 

MANNED SORTIE 

8-6 STS 2 HZ TANKS,+ 18 TONS OF LUNAR CARGO, 21 L8-4 MANNED 

+ 4 CREW SORTIE 8-7 SD-ULV LOX/LHZ PROPELLANT SUPPLY UNIT 100 

NOTE--- LUNAR CREW DELIVERED TO SPACE STATION ON SCHEDULED RESUPPLY STS LAUNCH 

8-8 STS 2 HZ TANKS,+ 18 TONS OF LUNAR CARGO, 

+ 4 CREW 

21 

L8-5 MANNED SORTIE 

L8-6 MANNED 

SORTIE 
1 

J 

1 

] 

J 

J 

J 

J 

COMMENTS AND CONCLUSIONS 

LUNAR BASE BUILD-UP AND OPERATIONS 

o THE LUNAR INITIATIVE REQUIRES HEAVY UTILIZATION OF THE SPACE STATION AS AN 

OPERATIONS CENTER AND TRANSPORTATION DEPOT 

o STORAGE, MAINTENANCE, AND OPERATIONS OF PERMANENT AND TRANSIENT TRANSPORTA- TION SYSTEM ELEMENTS REQUIRE EXTENSIVE HANGERS, GANTRYS, AND SHOP AREAS, PLUS 2 TO 4 ADDITIONAL SPACE STATION CREW MEMBERS 

o ADDITIONAL PERSONNEL r10DULE(S) WILL BE NECESSARY FOR ENLARGED SS CREW PLUS 

4 TO 6 TRANSIENTS (25% OF TIME) 

o LARGE OTV'S WITH MULTI-STAGING CAPABILITY ARE REQUIRED 

o ULV TANKER LAUNCHES ARE REQUIRED TO ACHIEVE REASONABLE LAUNCH RATES - PROVIDES LAUNCH COST SAVINGS OF $1.5 BILLION/YEAR COMPARED TO NSTS ALONE. 

o LUNAR TRANSPORTATION OPERATIONS ARE FAIRLY INTENSE BUT ENTIRELY PRACTICABLE. REQUIRES ONE LAUNCH PER MONTH, ONE LUNAR FLIGHT EVERY 2 MONTHS 
"] 

1 

1 

J 

MARS SAMPLE RETURN SCENARIO 

1. Stack Leaves S.S. 

2. Trans-Mars Injection 

3. Trans-Mars Voyage 

4. Aerocapture/Mars Orbit Insertion 

5. Jettison orbiter Aeroshell 

6. Lander and Orbiter Separate 

7. Lander Enters Mars Atmosphere 

8. Landing on Mars 

9. Collect Samples 

10. Launch from Mars 

11. Rendezvous Maneuvers 

12. Rendezvous with Orbiter 

13. Trans-Earth Injection 

14. Trans-Earth Voyage 

15. Earth Orbit Insertion 

16. Rendezvous with OMV 

17. Return to s.s. 

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CERES OR KOPFF SAMPLE RETURN SCENARIO 

1. 2 OTVs, MMII, 2 Samplers, 

and EOC leave SS 

2. 

3. 

First stage separates 

and returns to SS 

Second stage and spacecraft 

enroute to comet/asteroid 

4. Spacecraft surveying 

asteroid/comet 

5. Landers on surface, Spacecraft 

orbiting 

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and departs for Earth 

7. MMII and EOC enroute to Earth 

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TITAN PROBES/SATURN ORBITER SCENARIO 

SKETCH TO BE SUPPLIED 
PLANETARY MISSIONS PERFORMANCE SUMMARY 

C3 TYPE OF PAYLOAD LEO TOTAL OlV PROPELLANT 

OlV* OUT OF DEPARTURE PROPELLANT + PAYLOAD 

LEO MAss LOAD (LIFT REQ. ) 

(KM/SEC)A2 METRIC METRIC METRIC METRIC 

TONS TONS TONS TONS 

MARS SAMPLE 1 STAGE 

RETURN 9.0 REUSABLE 8.89 43.53 27.41 36.31 

KOPFF SAMPLE 2 STAGE, 

RETURN 80.7 1ST STAGE 8.38 91.76 71.08 79.46 

RETURNS 

CERES SAMPLE 2 STAGE, 

RETURN 9.9 1ST STAGE 43.57 131.24 75.42 118.99 

RETURNS 

MERCURY 1 STAGE 

ORBITER 18.7 REUSABLE 5.63 41.02 28.46 34.08 

TITAN PROBES/ 1 STAGE 

SATURN ORBITER 50.5 EXPENDABLE 6.34 52.90 41.30 47.65 

J * Isp = 455.4 SEC., ALL STAGES HAVE A TOTAL PROPELLANT CAPACITY OF 40 METRIC TONS, A = 3,731 KGMS, B = .0785. STAGES THAT DO NOT RETURN HAVE THE AEROBRAKE REMOVED. 
SHUTTLE LOADS REQUIRED 

FOR PLANETARY MISSIONS 

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MSR Nom MSR Worst Kopff SR MO Best MO Worst Ceres SR TP ISO 

PLANETARY MISSION 

[ZZJ LOX/LH2 for OTV ~IS-SJ--' PAYLOAD 

J 
J 

) COMMENTS AND CONCLUSIONS 

J 

, ] 

: 1 

\ 

I 

PLANET MY MISS IONS 

o THE IMPACT OF THE PLANETMY MISSIONS STUDIED ON THE SPACE STATION IS NOT LARGE WHEN COMPMED TO THE LUNAR BASE 

o A QUMANTINE MODULE MAY BE DESIRABLE FOR SAMPLE RETURNS 

o THE KOPFF AND CERES MISSIONS REQUIRE THE CAPABILITY TO STACK AND CHECKOUT TWO STAGE 

orus 

o 2 TO 7 MANWEEKS OF ON-ORBIT WORK, DEPENDING ON THE MISSION COMPLEXITY, WILL BE REQUIRED OF THE CREW OF THE STATION TO LAUNCH A MISSION 

o WITH THE POSSIBLE EXCEPTION OF QUMANTINE MODULE WORK, DEDICATED CREW WILL NOT BE REQUIRED 
End of Document