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CONTRACT NAS9-12068DRL LINE ITEM 7
MSC 04482SD 72-SA-0007
ORBITAL OPERATIONS STUDY
APPENDIX C
DATA SOURCES AND VEHICLE DESCRIPTIONS
FINAL REPORT
MAY 1972
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APPROVED BY:
L. R. HoganStudy Manager
ORBITAL OPERATIONS STUDY
9|r Space DivisionODwt North American Rockwell
https://ntrs.nasa.gov/search.jsp?R=19720025153 2020-03-14T08:06:05+00:00Z
CONTRACT NAS9-12068DRL LINE ITEM 7
MSC 04482SD 72-SA-0007
ORBITAL OPERATIONS STUDY
APPENDIX C
DATA SOURCES AND VEHICLE DESCRIPTIONS
FINAL REPORT
MAY 1972
APPROVED BY:
L. R. HoganStudy Manager
ORBITAL OPERATIONS STUDY
9|r Space Division0D• North American Rockwell
I
TECHNICAL REPORT INDEX/ABSTRACT
DOCUMENT SECURITY CLASSIFICATION
I. I UNCLASSIFIED I ITITLE OF DOCUMENT LIBRARY USE ONLY
ORBITAL OPERATIONS STUDY, FINAL REPORT
APPENDIX C - DATA SOURCES AND VEHICLE DESCRIPTIONS
AUL lHOR( "'.
*W. L. STEINWACHSCODE
ORIGINATING AGENCY AND OTHER SOURCES DOCUMENT NUMBER
QN085282 SPACE DIVISION OF NORTH AMERICAN ROCKWELL SD 72-SA-0007
CORPORATION, DOWNEY, CALIFORNIA APPENDIX C
PUBLI CATION DATE CONTRACT NUMBER
May 1972 NAS9-12068
DESCRIPTIVE TERMS
*DATA SOURCES, *BIBLIOGRAPHY, *VEHICLE INVENTORY,*PROGRAM ELEMENTS
. . ,: . I~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~
_ \ - , , r ,~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~IABSTRACT
THIS DOCUMENT IS APPENDIX C OF THE FINAL REPORT OF THE ORBITALOPERATIONS STUDY. THE BIBLIOGRAPHY OF PUBLISHED DOCUMENTS REFERREDTO THROUGHOUT THE STUDY IS INCLUDED. A BRIEF DESCRIPTION OF ALL OFTHE SPACE PROGRAM ELEMENTS INCLUDED IN THE STUDY VEHICLE INVENTORYIS PRESENTED.
I,
ACCESSION NUMBERI .II . . l l I
II
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F. II I I
Space Divisionp•% North Arerican Rocl<well
,%G?gs B FILt
FOREWORD
This report contains the results of the analyses conducted by the SpaceDivision of North American Rockwell during the Orbital Operations Study,Contract NAS9-12068, and is submitted in accordance with line item 7,of theData Requirements List (DRL 7).
The data are presented in three volumes and three appendixes for easeof presentation, handling, and readability. The report format is primarilystudy product oriented. This study product format was selected to providemaximum accessibility of the study results to the potential users. Severalof the designated study tasks resulted in analysis data across elements andinterfacing activities (summary level); and also analysis data for onespecific element and/or interfacing activity (detailed level). Therefore,the final report was structured to present the study task analysis resultsat a consistent level of detail within each separate volume.
The accompanying figure illustrates the product buildup of the study andthe report breakdown. The documents that comprise the reports are describedbelow:
Volume I - MISSION ANALYSES, contains the following data:
o Generic mission models that identify the potential earth orbitmission events of all the elements considered in the study
o Potential element pair interactions during on-orbit operations
o Categorized element pair interactions into unique interfacingactivities
Volume II - INTERFACING ACTIVITIES ANALYSIS, contains the following data:
o Cross reference to the mission models presented in Volume I
o Alternate approaches for the interfacing activities
o Design concept models that are adequate to implement the approaches
o Operational procedures to accomplish the approaches
o Functional requirements to accomplish the approaches
o Design influences and preferred approach selection by element pairs.
Preceding page blank
S-Siii -
SD72-SA-0007
9|r Space DivisionNorth American Rockwell
This volume is subdivided into four books or parts which are:
Part 1. INTRODUCTION AND SUMMARY - Condensed presentation of thesignificant results of the analyses for all interfacing activities
Part 2. STRUCTURAL AND MECHANICAL ACTIVITY GROUP
o Matingo Orbital Assemblyo Separationo EOS Payload Deploymento EOS Payload Retraction and Stowage
Part 3. DATA MANAGEMENT ACTIVITY GROUP
o Communicationso Rendezvouso Stationkeepingo Detached Element Operations
Part 4. SUPPORT OPERATIONS ACTIVITY GROUP
o Crew Transfero Cargo Transfero Propellant Transfero Attached Element Operationso Attached Element Transport
Volume III - BASIC VEHICLE SUMMARIES, contains a condensed summary of thestudy data pertaining to the following elements:
o Earth Orbital Shuttleo Space Tugo Research and Applications Moduleso Modular Space Station
Appendix A - INTERACTIVITY ANALYSES, contains many of the major tradesand analyses conducted in support of the conclusions andrecommendations of the study.
Appendix B - OPERATIONAL PROCEDURES, contains the detailed step-by-stepsequence of events of each procedure developed during theanalysis of an interfacing activity.
Appendix C - VEHICLE DESCRIPTIONS AND DATA SOURCES, presents a synopsisof the characteristics of the program elements that wereincluded in the study (primarily an extraction of the datain Appendix I of the contract statement of work), and abibliography of the published documentation used asreference material during the course of this study.
- iv -
SD72-SA-0007
Space Division' North American Rockwell
SD 72-SA-0007
�___·�___
Space Division9N% North American Rockwell
CON'ITNT S
Page
INTRODUCTION . 1-1
DATA SOURCES . 2-1
VEHICLE DESCRIPTIONS 3-1
3.1 THE BASIC PROGRAM ELEMENTS .3.1.1 Earth-to-Orbit Shuttle3.1.2 Research and Applications3.1.3 Earth Orbit Space Station3.1.4 Space Tug .3.1.5 Automated Payloads
3.2 ADD-ON3.2.13.2.23.2.33.2.43.2.53.2.6
PROGRAM ELEMENTSChemical Propulsion Stage .Nuclear Stage .Orbiting Lunar StationGeosynchronous Space StationLunar Surface Logistics Vehicle.Lunar Surface Base
PRECEDING PAGE BLANK NOT FILMED
Preceding page blank
- vii -
SD 72-SA-0007
Section
1.0
2.0
3.0
Module
3-33-53-83-103-153-28
3-343-363-403-433-473-473-47
Space DivisionON - NNorttlAferi:;,rl Roockwfell
ILLUSTRATIONS
Page
Phasing for the Basic Program .Earth-to-Orbit Shuttle Configuration - Delta WingTypical Configurations for RAM ElementsEOS-Launched Space Station Configuration - Initial6-Man Station . . . .
Shuttle-Launched Space Station Configuration -12-Man Growth Station . .
GT Centaur Configuration . .GT Centaur Characteristics ..Large Tank Agena Configuration .Large Tank Agena CharacteristicsTitan Transtage ConfigurationTitan Transtage Characteristics.Burner II Configuration . . . .
Burner II Characteristics .European Space Tug Configuration .European Space Tug Characteristics . .Space Tug Configuration . ..
Space Tug Characteristics . .
Time Phasing of Add-On Options .Chemical Propulsion Stage - Orbit InsertionStage Application . . .
Chemical Propulsion Stage ConfigurationChemical Propulsion Stage Characteristics.Reusable Nuclear Stage ConfigurationReusable Nuclear Stage CharacteristicsBaseline Orbiting Lunar StationEarth Orbit Space Station Derivative OrbitingLunar Station . . . .
Lunar Surface Logistics Vehicle ConfigurationLunar Surface Base . . . . .
3-43-63-9
3-11
3-133-163-173-183-193-203-213-223-23:3-243-253-263-273-35
3-373-383-393-413-423-44
3-453-483-50
pRECEDING PAGE BLANK NOT FILMED
Preceding page blank
- ix _
SD 72-SA-0007
Figure
3.1-13.1-23.1-33.1-4
3.1-5
3.1-63.1-73.1-83.1-93.1-103.1-113.1-123.1-133.1-143.1w153.1-163.1-173.2-13.2-2
3.2-33.2-43.2-53.2-63.2-73.2-8
3.2-93.2-10
Space Division'D NorthArneric;n Rockwell
TABLES
Table
Data Source Documentation List Numbering SystemData Source Documentation List..Time Table for Initial Operational Capability ofSpace Systems . . . .
Earth-to-Orbit Shuttle CharacteristicsLOS-Launched Space Station Characteristics -Initial 6-Man Station . .
EOS-Launched Space Station Characteristics -12-Man Growth Station .Automated Payloads, Earth Orbit Program -Equatorial Synchronous .Automated Payloads, Earth Orbit Program -Other Synchronous . . .
Automated Payloads - Other Nonplanetary PayloadsAutomated Payloads - Planetary FlightsAutomated Payloads - Additional Payloads CurrentlyUnder Consideration . .Orbiting Lunar Station - CharacteristicsLunar Surface Logistics Vehicle - Characteristics
. 12-22-3
3-2· . 3-7
3-12
3-14
3-29
3-30· . 3-31
3-32
3-33· . 3-46
· . 3-49
PRECEDING PAGE BLANK NOT FLMEW
Preceding page blank
xi -SD 72-SA-0007
2.0-i2.0-23.0-1
3.1-13.1-2
3.1-3
3.1-4
3.1-5
3.1-63.1-73.1-8
3.2-13.2-2
Page
Space Divisioni• North Ame!rcan Rockwell
1.0 INTRODUCTION
This appendix provides supplemental data to the main body of the OrbitalOperations Study final report. it is divided into two main sections: 2.0,Data Sources, and 3.0, Vehicle I)cscriptLons.
Section 2.0 serves a dual purpose. It provides a list of all documentsthat are referenced in the various volumes and appendixes of this final report.In addition, this section lists all of the formal documentation that has beenreviewed in the conduct of this study, but not necessarily referenced in thetext.
Section 3.0 presents a description, in terms of configuration and perform-ance, of the space elements considered in the Orbital Operations Study. Thematerial included in this section was extracted from Appendix II of the studycontract and was prepared originally by the NASA. The vehicles describedherein have been used in this study, where appropriate, as representativemodels. However, the analyses conducted and the results obtained in this study,in most cases, are not sensitive to exact configuration or performance data.
1-1
SD 72-SA-0007
Space Divisionto NorthArnerlcanRo(kwell
2.0 DATA SOURCES
This section lists, by major categories (i.e., program elements), alldocumentation (except NR informal letters) that have been reviewed in theOrbital Operations Study. The reference numbering system was set up early inTask 1.0 and was designed to accommodate subsequent growth. Blocks of numbers(50 to a block) were set aside for each major program element (Table 2.0-1).The large number of earth orbital shuttle (EOS) reports reviewed requiredassignment of an additional block of numbers to the EOS, resulting in a largenumber gap between the two blocks. This numbering system results in gaps ofunassigned numbers occurring in the latter part of each block of numbers.Also, additional gaps occur where numbers were assigned to informal NR letters,which are not included herein. The data source documentation list is presentedon Table 2.0-2.
Z-12_1
SD 72-SA-0007
9|, Space DivisionNortlhAr sria:;In Rockwell
Table 2.0-1
Data Source Documentation List Numbering System
Block ofAssigned Numbers
Earth Orbital Shuttle (EOS) 100 - 149550 - 599
Research and Applications Module (RAM) i50 - 199
Modular Space Station (MSS) 200 - 249
Tug 250- 299
Chemical Propulsion Stage (CPS) 300 - 324
Reusable Nuclear Shuttle (RNS) 325 - 349.
Orbiting Lunar Station (OLS) 350 - 399
Lunar Surface Base (LSB) 350 - 399
Shuttle Orbital Applications 400 - 449and Requirements (SOAR)
Orbital Propellant Depot (OPD) 450 - 499
General 500 - 549
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3.0 VEHICLE DESCRIPTIONS
Presented in this section are text, sketches, and performance datadescribing the space program elements which comprise the vehicle inventoryof the Orbital Operations Study.: Most of the information 'in this section. wasextracted from Appendix II of the study contract. With few exceptions, thedata developed in this study are not sensitive to exact weights, dimensions,or performance of the elements considered. However, for convenience, andwhere appropriate, the vehicle physical and performance data included hereinhave been used in the analyses as representative model data.
Section 3.1 presents currently planned basic advanced space programsand associated space elements. Section 3.2 describes several potentialadd-on programs and elements that are under consideration for the mid-1980's.Table 3.0-1 presents an approximate timetable for the availability of theelements of the basic program and of the potential add-ons.
3-1SD 72-SA-0007
Space DivisionNorth American Rockwell
Table 3.0-1. Timetable for Initial Operational Capability of Space Systems
CYBasic Operational Capabilities
Skylab 1973
Earth-to-Orbit Shuttle 1979(First Manned Orbital Flight - 1978)
Sortie Mission Module 1979
Interim Tug 1979
Permanent Space Station 1981
Space Tug 1985*
Potential Add-On Components
Chemical Propulsion Stage 1983
And one or more of the following:
High Energy Automated Landers andIntelligence Modules 1983
Geosynchronous Space Station 1983
Lunar Surface Logistics Vehicle 1983(Tug Derivative)
Orbiting Lunar Station 1983
Lunar Surface Base 1983
*European Space Tug (limited capability) as early as 1981/1982
3-2
SD 72-SA-0007
'|r Space DivisionNorthAmyican Rockwell .
3.1 TIIE BASIC PROGRAM ELEMENTS
In recent months, the advanced planning organizations within the OMSFhave generated several potential programs for the late 1970's and the decadeof the 1980's. The material'provided in this section represents a basicearth orbital program, keyed to the use of the earth-to-orbit shuttle (EOS).Operational dates have been adjusted to reflect the current forecasts fromNASA Central Planning. Project descriptions, flight rates, and inventoryrequirements are detailed. Figure 3.1-1 provides a pictorial representationof the types of activities contained in the basic program.
The EOS is planned to become operational in 1979. For the subsequenttwo years, the manned space program will be conducted using the EOS withshuttle-carried sortie modules.
In 1981, the six-man space station will be launched by the EOS. This isassumed to be an earth observation station. The EOS provides crew rotationand-resupply. In 1982, a second six-man space station will be added forastronomy applications. In 1983, one of the existing six-man space stationswill be expanded to a 12-man capability. The 12-man space station providesmuch greater long-term space operations capability through its increasedredundancy and maintenance facilities.
During this same time period, the EOS will be used to support the unmannedautomated research and applications program. An interim space tug (Agena,Centaur, or similar derivatives) will be used with the EOS to deliver, revisit,or return unmanned automated space vehicles.
In 1985, the space tug will become operational. The greater payloadcapability and versatility of the space tug will greatly enhance the capa-bility for satellite delivery and servicing.
The following sections, 3.1.1 through 3.1.5, describe in more detail thecomponent projects of the basic program. These sections discuss the specifichardware elements and missions which comprise the basic program. Each elementis briefly described, a summary of the performance parameters is discussed, andthe interrelationships of the elements to the total program are given.
3-3SD 72-SA-0007
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3.1.1 EARTH-TO-ORBIT SHUTTLE
The earth-to-orbit shuttle is a two-stage reusable vehicle that willbegin operations before the end of this decade to serve a broad range offunctions. The design of the EOS will emphasize versatility and economy tomaximize the extent of the EOS capability.
Among thile items presently .c.ltljded in this capability are:
I. Salfe, ecolnollicall, allnd eflficieLlt transport of men andequ(llltpmelL to alhd froti sY);Lce
2. Economical transport of spacecraft to low earth orbit inpreparation for their subsequent transfer by a space tuginto the desired orbit or escape trajectory
3. Return spacecraft from low earth orbit to the earth forrepair, refurbishment and replacement
4. Emplace large telescope or observatory modules in orbit andrevisit them periodically to change experiments, retrievedata, and service the modules
5. House, within its cargo compartment, a variety of experimentmodules that provide a laboratory environment and livingaccommodations where specialistfs can conduct scientific andtechnological observations and experiments in earth orbit onbrief "sorties" for:periods extending from several days toa week or more
6. Transport space station modular elements and bulk.cargo intoorbit, thus facilitating assembly of an orbiting space sta-tion and subsequent logistic support
Utilization of the EOS for such operations will permit an entirely newapproach to the design and development of spacecraft and experiments. Adva~n-tage can be taken of the opportunity for on-orbit checkout and activation,repair and refurbishment, relaxation of weight and volume constraints, andsimplified manned on-orbit operations.
This new capability and approach to system development will allow theintroduction of a new and more productive era of space activities withoutconcomitant increases in investment.
Figure 3.1-2 and Table 3.l1-1 present salient features and characteristicsof a current EOS design conce t.
3-5
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3.1.2 PESEARCII ANI) APPLICATIONS MOI)ULEi
The research and applications module (RAM) program consists of manypotential elements, all designed to provide and enhance the capability toconduct experiments in earth orbit. To satisfy user, program and designoriented requirements, modular elements are being considered. To
accommodate the primary requirements of habitability and access to experi-mental equipment, pressurized elements are being assessed. Modular buildupof subsystems to permit flexibility in operational capability and to meetvarious program funding constraints are being considered. The unpressurizedRAM element is being considered as a low-cost, flexible payload carrier thatprovides unobstructed viewing when access to the payload is not required.To satisfy requirements for high pointing accuracy, low contamination, andlong-duration observations, free-flying unmanned RAM's are necessary. Inaddition, these RAM's will be designed to be man-tended from the shuttle.A version of the pressurized RAM element is to be capable of operating as aservice element when attached to the free-flying RAM.
Missions and operations analyses have identified potential RAM elementswhich are candidates for inclusion in an earth-orbital research program.These elements are pressurized RAM's, unpressurized RAM's (pallet), andfree-flying RAM's. Within these broad generic classifications there arespecific characteristics which further define these RAM elements.
Sortie Mission - Three sets of desirable characteristics for pressurizedRAM's are identified. The first is a minimum-volume, minimum-weight withminimum subsystems for support of austere payloads. It is a minimum-weightconfiguration which can be carried to polar orbits. The second has a fullcomplement of subsystems for supporting large payloads and provides crewhabitability for experiment crews greater than two. The third is a largepressurized volume for housing advanced payloads. An unpressurized RAM(pallet) is also identified for use with payloads which require added mountingsurfaces.
Free-Flying Mission - Two RAM configurations are identified for thismode. A free-flying RAM which provides subsystems for payload supportalong with an extremely stable platform, low contamination, and a pressuriz-able volume for manned servicing of the payload. The second is a pressurizedRAM which provides storage volume and subsystem support for free-flying RAM'sduring manned servicing periods.
Station-Attached Mission - A single RAM configuration has been identified.It is characterized by a large pressurized volume; it receives subsystem supportfrom the Space Station (except thermal control).
Figure 3.1-3, illustrates typical configurations being considered. Thelarger of the two payload modules is a candidate for an MSS attached RAM.
3-8SD 72-SA-0007
Space Division
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3.1.3 EARTH 01LI' SPACE STATION
The assembly of a space station in earth orbit is planned to begin in theearly 1980's. The space station will extend the capability of the sortie mod-ule to operate continuously and autonomously in space for long periods of time.The size and capability of the space station will be flexible in that it canbe placed in operation, then extended or modified to satisfy changing require-ments. Its modules will be launched into earth orbit and provided periodiclogistics support by the EOS.
Since it will be a relatively permanent as well as flexible laboratory,the space station will make it possible to conduct diverse experiments inspace. These experiments further broaden the scope of science and applica-tions information available, observe the physical and psychological behaviorof varied groups of individuals and the performance of their support equipmentover extended periods of time, and develop experience in the operation ofsystems requiring long operating lifetimes in space. The space station willthus complement the short duration sortie missions through its capability toextend almost indefinitely the periods of observation in space.
The EOS-launched space station configuration described in Figure 3.1-4and Table 3.1-2 can be readily adapted to other applications. For example,with minor modifications, the modules can be applied to a geosynchronousspace station or an orbiting lunar station. With more extensive modifications,the modules could be assembled into a lunar surface base. By adding modulesof similar design, the initial six-man station can be extended to a 12-mancapability.
The 12-man space station described in Figure 3.1-5 and Table 3.1-3 isassembled from modules identical to those of the six-man station. Additionalelements required include experiments and maintenance modules and a medicaland exercise unit. The increased redundancy in the 12-man station greatlyimproves its long-term space operations capability.
The basic modular station design is derived from the EOS-sortie module;each module is compatible with the EOS payload bay, and only the EOS isrequired for launch into earth orbit. The design provides for periodicreplacement of the environmental control life support system. A two-yearreplacement cycle has been assumed.
3-10
SD 72-SA-0007
Space Division-% NN(xIh'IqIvArKrl.'nlI Fkxkw4lI
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EOS-Launched Space Station Configuration -Initial Six-Man Station
3-11SD 72-SA-0007
Space Division9L• Noh FRockwell
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EOS-Launched Space Station Characteristics -Initial Six-Man Station
* WEIGHT STATEMENT
ITEM WEIGHT (LBS)
CORE MODULE #1 (C1) 28,220POWER MODULE #1 (PM) 15,420
CREW QUARTERS MODULE #1 (CQM 1) 12,950
CARGO MODULE (CM) 20,000
CONTROL CENTER #1 (CCM1) 17,280
RESEARCH &APPLICATIONS MODULE (AM) 20,000
CONTROL CENTER #2 (CCM2) 19,270
CREW QUARTERS MODULE #2 (CQM2) 14,060
RESEARCH & APPLICATIONS MODULE (AM) 20,000
GROSS (LESS CREW) 167,200
· CAPABILITY6 MAN16.5 KW
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3-12
SD 72-SA-0007
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Figure 3.1-5. Shuttle-Launched Space Station Configuration -Twelve-Man Growth Station
3-13
SD 72-SA-0007 '
Space Division9• North American Rockwell
't'able 3.1-3. EOS-Launclicdl Space StatLon Cliaracteristics -Twelve-Man (Growth Station
* WEIGHT STATEMENTITEM
CORE MODULE #2 (C2)CREW QUARTERS MODULE #3 (CQM3)POWER MODULE #2 (PM)
RESEARCH &:APPLICATIONS MODULE (RAM)
MEDICAL/EXERCISE MODULE (MEM)
CREW QUARTERS MODULE #4 (CQM4)ANTENNA POD (ON CQM3)ANTENNA POD (ON CQM4)
12 MAN GROSS (LESS C
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20,00013,5509,980
1,950
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3-14SD 72-SA-0007
Space Division'North Ar rlericlar Rockwell
3.1.4 SPACE 'TUG
The space tug is a propulsive stage capable of being carried into orbitin the EOS cargo bay. Once in orbit, it will be capable of performing missionsranging from placing spacecraft into orbits different from that of the EOS tothe insertion of spacecraft into geosynchronous orbit, or injection into escapetrajectories. Although the ultimate performance objectives for this propulsivestage include manned applications, spacecraft retrieval, and reusability of thepropulsive stage itself, the early capability may be somewhat more restricted.Studies are currently underway both in the United States and in Europe to definethe performance and operating requirements of the space tug and-to identify andevaluate alternate design approaches. It is envisioned that a space tug withlimited capability could be available by the early 1980's (European tug) andthat a system embodying the full performance objectives could be in operationby the mid-1980's.
In the interim before the space tug becomes operational, it is plannedthat a derivative of an existing stage, such as Centaur, Agena, Titan Transtageor Burner II, will be adapted to fulfill the functions of inserting spacecraftinto orbits different from that of the shuttle, into geosynchronous orbit, andinjection into escape trajectories. This vehicle is identified as an interimtug and could become operational concurrently with the EOS.
It is conceived that the interim tug could initially be operated in anexpendable mode and later be operated in a reusable mode with ground-basedreplenishment of expendables. The exception is the Burner II stage which usesa solid propellant and is always expended. From the standpoint of operationalcomplexity, particularly for initial EOS/tug operations, it is desirable tolaunch the interim tug mated with its payload, i.e., in one EOS flight. Thus,for this case, the gross weight (tug plus payload) is limited to the EOS pay-load capabilityat the required orbital inclination. Orbital inclinationrequirements for identifiable tug payloads tend to be grouped at or near equa-torial, 30-degree, 55-degree, or polar orbits. When launched from either theEastern or Western Test Range, the EOS is limited to an operational orbit of28.5 degrees or greater inclination. Gross weight limits of 65,000, .55,000,and 40,000 pounds are representative of the EOS payload capabilities to a 100nautical mile circular orbit at inclinations of 28.5, 55, and 90 degrees,respectively (payload capability decreases as orbital inclination increases).These limits were used in illustrating the performance capabilities of thevarious tug candidates. Gross weight-limited performance is representativeof totally ground-based operations in which no orbital assembly or orbitalpropellant loading is required. Tug propellants are off-loaded as payload isincreased in order to stay within the gross weight limits.
Figures 3.1-6 through 3.1-13 illustrate the characteristics and configur-ations of the Agena and Centaur derivatives, the Titan Transtage, and Burner II,which represent vehicles that could be used as interim space tugs. Interimtugs could also comprise slightly modified current operational versions of theAgena or Centaur. Figures 3.1-14 and 3.1-15 illustrate a possible configura-tion for the European space tug. Figures 3.1-16 and 3.1-17 describe thecharacteristics of a full capability new development space tug.
3-15
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3.1.5 AUTOMATED PAYLOADS
The combination of eartli-to-orblit slluttle and space tug will providethe capabi. lity to deliver, service, and return to earth virtually all auto-mactd scLelntLlec payloads within the current inventory or planning stages.
Tables 3.1-4 through 3.1-8 deL;ail tilhe weight, dimensions, and orbitalparameters associated with candidate shuttle/tug automated payloads underconsideration for the 1978-1990 time period. It should be understood thatseveral of these missions may be replaced by sortie or space station exper-iments. Also, these dimensions are based on current expendable launch vehicleconfigurations. Configurations may vary considerably if payloads are redesignedfor launch in the EOS for maintainability and reuse.
Items denoted by an asterisk have been identified in current planningactivities as prime candidates for EOS launch.
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3.2 ADD-ON PROGRAM ELEMENTS
This section describes several potential program additions for the 1980's.Depending on priorities and budget restrictions, any one or a combination ofseveral of these 1980 programs might be added.
A space transportation vehicle having greater payload capability than theEOS alone or the EOS/space tug combination would be required in order to imple-ment most of the potential program additions. A chemical propulsion stage(CPS) could be mated with the EOS booster (in place of the EOS orbiter) andused as an orbit insertion stage to place large payloads into earth orbit.After placement into earth orbit the CPS could be refueled and used as a highenergy translunar shuttle. Another contender for the translunar shuttle roleis the reusable nuclear stage.
Four potential add-on program options consist of:
1. A multi-space stage program. This add-on option builds fromthe 18-man space population of the basic program to 54 menthrough the addition of three 12-man modular earth orbitalspace stations. These additional stations are launch in 1983,1984, and 1985.
2. A six-man geosynchronous space station. This station is placedin orbit in 1983 and supplied through the use of the EOS inconjunction with the chemical propulsion stage.
3. An independent lunar surface program. Along with the EOS andchemical propulsion stage, a new lunar landing vehicle isrequired (space tug derivative). This program, beginning in1983, is an Apollo-type mission with no orbiting lunar spacestation. Two landings are performed each year.
4. Full lunar program. This program includes an eight-man lunarorbit space station in 1983, followed by a permanent 12-manlunar surface base in 1987. The program requires the EOS, theCPS, a lunar landing vehicle, as well as a modular orbitinglunar station and a station-derived lunar surface base. Sig-nificantly higher funding levels are required for this add-onoption than the preceding four options.
Figure 3.2-1 pictorially represents the potential add-on options. Keyelements of the basic program are shown for reference.
3-34
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MULTISTATION PROGRAM OPTION
GEOSYNCHRONOUS STATION
INDEPENDENT LUNAR SURFACEPROGRAM OPTION
FULL LUNAR PROGRAM OPTION
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3-35
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This section shows the characteristics of potential new hardware to beadded to the NASA inventory if the four add-on programs are flown. Theyinclude:
L. 'rI'l clteil[cal_ propulsion stage - required For add-on options,' ., and /.
2. ''lhe reusable nuclear stage - an alternate to the CPS foradd-on options 2, 3, and 4.
3. The orbiting lunar or geosynchronous space station - requiredfor add-on options 2 or 4.
4. The lunar surface logistics vehicle (tug derivative) -required for add-on options 3 or 4.
5. The lunar surface base - required for add-on option 4.
3.2.1 CHEMICAL PROPULSION STAGE
The CPS, mated with the earth-to-orbit shuttle booster, serves as alaunch vehicle capable of inserting heavy payloads into low earth orbit(150,000 to 200,000).
Once in orbit, the CPS can be refueled (using EOS tankers) and employedfor a variety of orbit-to-orbit functions. This stage is assumed to bereusable for approximately 20 missions.
Options shown in this guide assume use of the CPS for deep space, high-energy automated missions, as an orbit-to-orbit shuttle for future manned orautomated lunar missions, and as a delivery and resupply vehicle for mannedgeosynchronous missions.
The vehicle may be used as a single stage vehicle or in tandem operations.Typical configurations and data are shown in Figures 3.2-2, 3.2-3 and 3.2-4.Figure 3.2-2 depicts a possible configuration showing the orbit insertion stagecapability. Figure 3.2-3 illustrates the orbit-to-orbit stage configuration.The design characteristics of the stage are listed in Figure 3.2-4.
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3.2.2 NU(GI'AR SA(;E
'rle nuclear stage is an alternate to the CPS for all applications exceptthat of payload delivery to low earth orbit.
The nuclear stage is conceptually made up of a propulsion module, pro-pellant module(s), and a command and control module. The propulsion moduleconsists of a NERVA engine and a small propellant (run) tank, and is sizedfor launch in the EOS orbiter bay. The propellant module(s), along with therun tank, provide a propellant capacity of about 300,000 pounds of liquidhydrogen (LH2 ).
Two propellant module configurations are possible; a singular versions.ized for launch on the EOS/CPS launch vehicle, and a modular version sizedfor launch in the EOS orbiter bay. These alternative configurations areillustrated in Figure 3.2-5.
The command and control module fulfills all RCS, intelligence, and pay-load docking functions. It is sized for launch in the EOS orbiter bay andconceptually can either be replenished in earth orbit after each mission orthe entire unit can be recycled to the ground with each payload.
Additional vehicle and performance data for the nuclear stage are pro-vided in Figure 3.2-6.
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3.2.3 ORBITING LUNAR STA-TION
Among the alternatives for add-on options, use of space station technologyto extend manned exploration of the solar systems appears to be attractive.One of the locations to be considered is lunar orbit. The immediate apparentscientific return from an orbiting lunar station is relatively low, but thestation serves a valuable purpose in the transportation chain for lunar surfaceexploration, whether by small expeditions or by operations from a fixed lunarsur lace base.
Iwo clad lltlg space staLioll colif i guratlions that are adaptable to lunarorbl.t are depicted in Ifigures 3.2-7 ;nld 3.2-8. Figure 3.2-7 shows the baselinestation, derived from thle basic earth orbiting configuration and the transporta-tion capability of the OIS/CPS. Figure 3.2-8 shows a modular counterpart,derived from the EOS-launched (modular) space station which was an element ofthe basic program.
It is likely that the configuration of an orbiting lunar station will bebased upon other elements of the overall program. For example, if the modularconfiguration is selected for the earth observation stations, development costconsiderations may dictate selection of a modular approach for all otherstation-type programs. On the other hand, an integral station, similar to thebaseline design, may prove to be a valuable precursor to other long-durationspacecraft missions.
The configurations shown here are designed to accommodate a crew of eightmen. Early studies have shown that six crewmen will be occupied with the sci-entific experiments and observations. Two additional crewmen are provided toassist the with deployment and operation of landing parties.
A comparison of some of the basic characteristics of the- two designs ismade in Table 3.2-1.
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3.2.4 GEOSYNCIIRONOUS SPACE STATION
l'reliminary studies have shown thiat a geosyllchronous space station couldle :upporLed withl ;pproxlmnaLtey the same resources reqluired for the orbitinglunar :;LatLion. An cartlhl-fIxed orl[L;tl. locaLtion may prove useful for earthsurveil;I.t:llce or coiiiniini ca Lions supl)port activi.ties.
h'le configurations and characteristics for the modular earth orbit spacestation (previously described) and for the orbiting lunar station appear well-suited to the geosynchronous station. A six-man crew presumably can handlethe work load, since no landing missions are supported from the station.
3.2.5 LUNAR SURFACE LOGISTICS VEHICLE
The lunar surface logistics vehicle is a derivative of the reusable spacetug. The crew module and cargo module are located aft near the surface atlunar landing as shown in Figure 3.2-9. This provides better visibility,better surface access, a low center of gravity, and lower design structuralloadings. The engines are extended outboard to accommodate the aft crew mod-ule location. The engines are retracted for launch by the EOS. Deployment ofthe engines and assembly of the crew module, cargo modules, and landing gearto the propulsion module is performed in earth orbit. More detailed character-istics of the lunar surface logistics vehicle are provided in Table 3.2-2.
3.2.6 LUNAR SURFACE BASE
The lunar surface base (LSB) will probably be an adaptation of the spacestations employed earlier in the program. If the space stations previously inuse are modular, the lunar surface base may be modular. An integral designfor the space stations may dictate similar design constraints for the LSB.
Establishing a lunar surface base will require commitment of substantiallygreater resources.to the space program. It requires the longest and most com-plex logistics lines of any of the programs being considered.
Radiation and meteorite protection as well as thermal stability questionspose difficult problems for the lunar surface base designer. One concept,illustrated in Figure 3.2-10, provides this protection by banking lunar soilover the modules of the LSB.
The postulated purposes of the LSB concept shown here are to support alunar observatory, deep drilling operations, and remote surface explorationsorties., For this concept, four men each are required to support the observa-tory and exploration functions, and two men are required for the deep-drillingoperation. The base is sized to support 12 men and includes two drive-ingarage/warehouse modules. The surface vehicles are required to support amaximum surface sortie duration of 90 days.
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