A NASA CAPABILITIES EVALUATION DOCUMENT PRELIMINARY DRAFT

• Document Type: CREST
• Collection: General CIA Records
• Document Number (FOIA) /ESDN (CREST): CIA-RDP92B00181R001901730063-1
• Release Decision: RIFPUB
• Original Classification: K
• Document Page Count: 33
• Document Creation Date: December 23, 2016
• Document Release Date: March 14, 2012
• Sequence Number: 63
• Publication Date: June 16, 1983
• Content Type: REPORT

-1 1
Declassified and Approved For Release 2012/03/14: CIA-RDP92B00181 R001901730063-1
A NASA CAPABILITIES EVALUATION DOCUMENT
Preliminary Draft
June 16, 1983
,,, Declassified and Approved For Release 2012/03/14: CIA-RDP92B00181 R001901730063-1
 Declassified and Approved For Release 2012/03/14: CIA-RDP92B00181 R001901730063-1
Table of Contents
Page
1.0 INTRODUCTION
2.0 METHODOLOGY
2.1 Mission Model
1-1
2-1
2.1.1 Mission Model Development
2.1.2 Mission Categories
2.1.2.1 Astrophysics
2.1.2.2 Earth Science And
Applications
2.1.2.3 Solar System Exploration
2.1.2.4 Life Sciences
2.1.2.5 Communication Satellites
2.1.2.6 Materials Processing
2.1.2.7 Satellite Servicing
2.1.2.8 Technology Development
2-1
2-2
2-2
2-2
2-2
2-2
2-2
2-2
2-2
2-2
2.2 Cost Estimating
2.2.1
DDT&E Costs
3.0 SCENARIOS
3.1
Scenario I
3.1.1
Description
3-1
3.1.2
Capabilities
3-1
3.1.3
Cost
3-3
3.2.1
Description
3-4
3.2.2
Capabilities
3-4
3.2.3
Cost
3-4
3.3
Scenario II
3.3.1
Description
3-5
3.3.2
Capabilities
3-5
3.3.3
Cost
3-6
3.4
Scenario IIa
3.4.1 Description
3-7
3.4.2 Capabilities
3-7
3.4.3 Cost
3-7
Declassified and Approved For Release 2012/03/14: CIA-RDP92B00181 R001901730063-1
 Declassified and Approved For Release 2012/03/14: CIA-RDP92B00181 R001901730063-1
3.5
Scenario IIb
3-8
3.5.1
Description
3-8
3.5.2
Capabilities
3-8
3.5.3
Cost
3-8
3.6
Scenario IIIa
3-9
3.6.1
Description
3-9
3.6.2
Capabilities
3-9
3.6.3
Cost
3-10
3.7
Scenario IIIb
3-11
3.7.1
Description
3-11
3.7.2
Capabilities
3-11
3.7.3
Cost
3-11
3.8
Scenario IIIc
3-12
3.8.1
Description
3-12
3.8.2
Capabilities
3-12
3.8.3
Cost
3-13
3.9
Scenario IV
3-14
3.9.1
Description
3-14
3.9.2
Capabilities
3-14
3.9.3
Cost
3-14
4.0 SUMMARY
APPENDIX A: MISSION MODEL
APPENDIX B: CAPABILITIES OF SUPPORTING ELEMENTS
,,, Declassified and Approved For Release 2012/03/14: CIA-RDP92B00181 R001901730063-1
 Declassified and Approved For Release 2012/03/14: CIA-RDP92B00181 R001901730063-1
1.0 INTRODUCTION
This document has been prepared by NASA to provide a set of scenarios that
bound the options available to fulfill the nations civil space goals for the
time period 1991-2000. The document is a result of one year of developing
mission requirements, two months of evaluating architectural options to
fulfill those mission requirements, and one month of developing the cost data
for a Space Station concept and its operations.
This assessment process required a set of missions which represent the civil
space requirements, a group of scenarios of capabilities to fulfill those
options, and the developmental cost of each of the scenarios.
The approach used is to increase capabilities incrementally from one scenario
to the next. The scenarios begin with the "baseline" of today's STS capabil-
ity augmented by a Teleoperated Maneuvering System (TMS) and progresses
through options of varying capability to a manned Space Station scenario.
The scenarios are shown in Table 3.1 and a description of each element of the
scenarios is presented in Appendix B.
It is necessary to point out that the scenarios' capabilities and/or their
limitations do not lend themselves to a classical capture analysis where a
value, or figure of merit, can be placed on the increased capabilities. In a
classical capture analysis the added capabilities, their development costs
and their life cycle cost would be used to determine the benefit of the added
capability. To determine the value or benefit of each capability, a normaliz-
ation of the scenarios to these scenarios of long duration missions (years)
would require an exorbitant number STS launches. The cost of these addi-
tional launches (at $122 M average for ETR or WTR launch) causes the life
cycle costs of the scenarios without long duration mission capability to be
very unrealistic.
Therefore, a qualitative evaluation of the capability of each scenario is
presented in Section 3.0 and the conclusion drawn from this evaluation is
presented in the Sumiary Section 4.0.
As mentioned earlier, the mission sets are the result of a one year that
represent the agency's plans for the period of 1991-2000 and are within the
Agency's forecast budget. The study was conducted within the frame work of
exploiting the capabilities of a long term on-orbit facility with the added
capability of manned interaction. The coupling of these two unique aspects,
the long duration in space, and the permanent presence of man is the key
element of these missions sets. However, upon examination, many mission
requirements can be partially net with the existing capability (e.g., free
flyer for long duration), but the benefits of the permanent presence of man
are not attained even with frequent servicing by the Shuttle.
Following the mission analysis study and the architectural options survey,
the costs data for the Design Development Test and Evaluation (DDT&E) were
developed for the scenario elements that were incrementally added to the
present STS baseline. Although the establishment of a figure of merit was
not possible the DDT&E cost offers additional understanding to evaluate the
added capabilities.
q Declassified and Approved For Release 2012/03/14: CIA-RDP92B00181 R001901730063-1
 i
Declassified and Approved For Release 2012/03/14: CIA-RDP92B00181 R001901730063-1
Finally, Section 3.0 develops an evaluation of each scenario to determine if
the scenario accommodates the mission set and provides the cost for added
capability.
This document is based on a first iteration of a set of space missions and a
Space Station concept that will continue to be refined in the next few
months.
Declassified and Approved For Release 2012/03/14: CIA-RDP92B00181 R001901730063-1
 i
Declassified and Approved For Release 2012/03/14: CIA-RDP92B00181 R001901730063-1
2.1.1 Mission Model Development
The mission model was developed by merging the "STS Mission Model 1983-2000
-- Nominal Version" (Advanced Planning Division, NASA Headquarters, December
20, 1982) and the results of the Space Station Mission Requirements Workshop
which was the culmination of one year of NASA and private industry study of
missions for the Space Station era. The study and the Workshop were neces-
sary because previous mission planning had generally considered only STS,
Spacelab, and Free Flyers and did not include the availability of a Space
Station System. The Mission Requirements Workshop utilized advocacy groups
in four major areas: Science and Applications, Carmercial, and Tech-
nology as a means to merge the results of the industry Mission Analysis Study
results of the past year with NASA's space mission plans. This activity can
be perceived as one of refocusing NASA mission plans to include a capability
in excess of the present STS in terms of orbit stay time. This need has been
recognized for many years, but mission planning has been constrained by the
lack of long-term, manned on-orbit capability.
The term "mission" is used very broadly in this model. In sane cases, the
term refers to (1) a single instrument (e.g., a telescope), or (2) a single
launch of a spacecraft, or (3) a series of experiments
,,, Declassified and Approved For Release 2012/03/14: CIA-RDP92B00181 R001901730063-1
 Declassified and Approved For Release 2012/03/14: CIA-RDP92B00181 R001901730063-1
2.1.2 Mission Categories
The model includes missions in the following categories:
2.1.2.1 Astrophysics. The astrophysics missions use telescopes or other
detectors that are flown as missions requiring one to ten years on-orbit to
complete their mission objectives. In addition, several missions desire
ready manned intervention for adjustment and servicing of instruments.
2.1.2.2 Earth Science And Applications. Earth Science and Applications
missions are generally flown in high inclination orbits. Long duration
missions are essential for the observations of the slowly varying changes on
the earth's surface.
2.1.2.3 Solar System Exploration. The Solar System Exploration missions
utilize either expendable upper stages or Orbital Transfer Vehicles (OTV's)
for insertion into the proper trajectory.
2.1.2.4 Life Sciences. The life sciences missions require extended,- unin-
terrupted time on-orbit with extensive crew involvement. The major objective
of these missions is to understand, and develop countermeasures for, the
effects of lack of gravity on humans.
2.1.2.5 Communication Satellites. The communications satellites require
launch capability to geosynchronous orbit.
2.1.2.6 Materials Processing. Effective development of Materials Processing
in Space (MPS) requires a research and development facility that affords long
duration, uninterrupted tine on orbit with extensive manned interaction.
This facility would allow realization of the potential of MPS research to
yield new commercial enterprises and technology advances.
2.1.2.7 Satellite Servicing. On-orbit satellite servicing in low earth
orbit is expected to become a -routine procedure in the 1990s. Satellite
servicing includes routine and contingency maintenance of free flyers and
platforms, resupply of propellants, adjustment or change-out of scientific
instruments, and, in some cases, on-orbit assembly and deployment of satel-
lites. Servicing satellites at geosynchronous orbit is also anticipated.
2.1.2.8 Technology Development. The Technology Development missions that
are listed in this model were designed specifically to take advantage of long
duration in space with interaction by man. Most of these missions are
designed to provide verification of Space STation technology for the enhance-
ment of Space Station evolution. Some of the missions provide significant
technology development for areas such as large antenna development for
commercial cannunication.
Declassified and Approved For Release 2012/03/14: CIA-RDP92B00181 R001901730063-1
 i
Declassified and Approved For Release 2012/03/14: CIA-RDP92B00181 R001901730063-1
The cost estimates used for the Space Station System were derived fran a cost
model developed by NASA. This model is based on a historical manned space-
craft (Gemini, Apollo, Skylab, Spacelab, STS orbiter) and unmanned spacecraft
(Landsat, HEAO,.ATS, and others) data base. This model uses cost estimating
relationships (CER's) to determine the subsystem and system level costs. The
CER's in the cost model were developed fran a normalized historical data base
by parametric costing and similarity between present and past programs.
The cost estimates are for Design Development Test and Evaluation (DDT&E) and
are based on 1984 dollars.
2.2.1 DDT&E Costs
When elements in addition to the STS, are required to support a scenario, a
DDT&E cost for that element is included in the total cost. The cost included
such items as structures, thermal control, electrical power, corrunications,
data handling, attitude control, and environmental control and life support
subsystems. System test hardware, integration, assembly and checkout, ground
support equipment, and program management costs are also estimated and
included in the DDT&E cost estimates. The costs include the first flight
unit cost and if identical units are required, they are produced at a signif-
icantly lower cost.
The cost for instruments or mission/payload equipment are not included in any
scenario cost.
Operations/Life Cycle Costs
An operations/life cycle cost was developed for the element within each
scenario fran 1991 through 2000. The life cycle cost utilized for the STS
was based on STS historical data which includes the ground processing and
flight operations costs for each flight. However, as stated in the introduc-
tion, this operational life cycle cost was not used.
Declassified and Approved For Release 2012/03/14: CIA-RDP92B00181 R001901730063-1
 i
Declassified and Approved For Release 2012/03/14: CIA-RDP92B00181 R001901730063-1
The elements of each scenario are outlined in Table 3.1. The further detail
description of the elements is contained in Appendix B.
An extended orbitor capability, in the form of a power extension package, has
been added to some of the scenarios to evaluate its ability to fulfill the
mission model requirements -
3.1.1 Description
Scenario I utilizes the present STS system augmented with an STS-based
Teleoperator Maneuvering System (TMS) to enhance capabilities for deployment,
retravial, service, and on-orbit maintenance of free flying satellites.
Other elements in the scenario are free flying satellites, and expendable
upper stages (PAM A, PAM-D, IUS, and Centaur) that are used to lift payloads
from the shuttle orbit to geosynchronous and other high energy orbits.'
3.1.2 Capabilities
The Materials Processing missions preferred mode of accarnodation is the
Space Station. These missions require extensive, uninterrupted man-tended
experiment time on-orbit. Theses missions cannot be accommodated by the
capabilities of this scenario. However, a limited amount of research can be
accomplished by STS sortie flights. These limited R&D missions could provide
early precurser equipment development leading to the eventual product ca-
pability.
The astrophysics missions require long time on-orbit (one to ten years) and
many of these missions also desire manned involvement for servicing and
adjustment of instruments. The total mission set cannot be accommodated
within the capabilities of Scenario I. Some of the missions will be flown as
free-flying satellites. The remaining missions will be placed on STS sortie
flights, where they do receive the benefit of manned involvement; but in this
case, the attainment of mission objectives is severely limited because of the
short duration of the STS flights. For example, experiments such as Starlab
and Solar Optical Telescope that need three to four years of on-orbit obser-
vation time are limited to one or more STS missions of approximately seven
days each. Since several days of outgassing time are required before good
observations can be performed with these instruments, the amount of good
quality data obtained is questionable.
Life science missions require extended, uninterrupted tine on-orbit with
extensive crew involvement. These missions cannot be fulfilled in this
scenario. Only precursor experiments can be accarnplished in this scenario
(flying these experiments as sortie missions on the STS). The long term
objectives of these missions can only be accomplished with a permanent manned
orbiting faciilty.
The earth science and application missions in general require high in-
clination orbits and a few missions require man involvement. The high
inclination missions will be flown on free flyers in this scenario. Those
,,, Declassified and Approved For Release 2012/03/14: CIA-RDP92B00181 R001901730063-1
 Declassified and Approved For Release 2012/03/14: CIA-RDP92B00181 R001901730063-1
I
Ia.
II
IIa
IIb
IIIa
IIIb
IIIc
IV
STS
STS
STS
STS
STS
STS
STS
STS
STS
S/L
S/L
S/L
S/L
S/L
S/L
S/L
S/L
S/L
U/S
U/S
U/S
U/S
U/S
U/S
U/S
U/S
U/S
F/F
F/F
F/F
F/F
F/F
F/F
F/F
F/F
F/F
TMS
TMS
TMS
TMS
TMS
TMS
TMS
TMS
TMS
PEP
SP28.5?
PEP
SP90?
SS28.5?
SS28.5?
SS28.5?
SS28.5?
PEP
OTV/SS
SBOTV
OTV @SS
SP 28.5?
OTV/SS
SP 28.5?
SS90?
OTV @ SS
LEGEND :
STS - SPACE TRANSPORTATION TMS - TEIEOPERATOR MANEUVERING SYSTEM SBOVr - SPACE BASED ORBITER TRANSFER VEHICLE
SYSTE4 PEP - POWER EXTENSION PACKAGE (PEP) MPS - MATERIALS PROCESSING IN SPACE
S/L - SPACELAB - SORTIES SP - UNMANNED SPACE PLATFORM L/S - LIFE SCIENCE
U/S - UPPER STAGES OTV/SS - OTV SPACE STATION OIV @ SS - OTV CAPABILITY ADDED TO EXISTING
FF - FREE FLYERS SS - SPACE STATION SPACE STATION
Declassified and Approved For Release 2012/03/14: CIA-RDP92B00181 R001901730063-1
 Declassified and Approved For Release 2012/03/14: CIA-RDP92B00181 R001901730063-1
missions requiring man intervention because of the complexity of the experi-
ments, will be flown as STS sortie missions, but again the short duration on
orbit severely limits the attainment of mission goals.
Satellite servicing missions preferred acccnrudation modes are, satellite
return to the on-orbit servicing facility, or remote servicing at the satel-
lite location. These missions can be accomplished with the STS, TMS, and
expendable launch vehicles. However, the servicing equipment must be brought
to orbit on planned STS flights for each mission.
Coen unications satellites which require geosynchronous orbit will be launched
via the STS with an expendable upper stage (PAM A, PAM-D, IUS, or Centaur).
The technology development missions preferred accommodation mode is a long
duration orbit facility with extensive man interaction capability. Most of
the missions are designed to provide for the enhancement of the evolutionary
capability of the Space Station and its objectives. These missions cannot be
fulfilled by this scenario.
The STS can be utilized for the development of some techniques and equipment
for eventual use by the Space Station in fulfilling some of its mission
objectives (e.g., satellite servicing).
In Scenario I, the solar system exploration missions will be accomplished
with expendable upper stages (IUS or Centaur) launched from the STS.
3.1.3 Cost
The following are the cost associated with Scenario I:
DDT&E Cost
Cost
STS
(Developed)
0
Spacelab
(Developed)-
0
Upper Stages
(Developed)
0
TMS
$ 132 MIL
*Free Flyers
(26 FF x $200)
$5200 MIL
Total Cost $ 5332 MIL
* The Free Flyers cost is for the bus only, not instruments.
II Declassified and Approved For Release 2012/03/14: CIA-RDP92B00181 R001901730063-1
 Declassified and Approved For Release 2012/03/14: CIA-RDP92B00181 R001901730063-1
3.2.1 Description
This scenario utilizes the present STS system augmented with (1) a power
extension package (PEP) which extends the shuttle on-orbit stay time from a
maximum of 7 to 20 days and (2) a STS-based teleoperator maneuvering system
(CIS) to enhance capabilities for deployment, retrieval, service, and
on-orbit maintenance of free flying satellites. Other elements in the
scenario are free flying satellites and expendable upper stages (PAM A,
PAM-D, IUS, and Centaur) that are used to lift payloads fran the shuttle
orbit to geosynchronous and other high energy orbits.
3.2.2 Capabilities
The major change in capabilities to this scenario from Scenario I, is the
addition of the PEP (Power Extension Package). This addition has a small
impact on the fulfilling of the mission model. The significant impact is in
the increased orbitor stay time for the Spacelab/sortie missions., Most
sortie missions benefit is an increase in the on-orbit staytime, but still
fail to accomplish a significant fraction of the mission objectives.
3.2.3 Cost
STS
(Developed)
0
Spacelab
(Developed)
0
Upper Stages
(Developed)
0
TMS
$232 MIL
*Free Flyers
(27 x $200 To Support
The Scenario)
5400 MIL
PEP
150 NIL
RMS
$ 25 MIL
Total Cost
$ 5807 NIL
* The free flyers cost is for the bus only, not instruments.
0.1 Declassified and Approved For Release 2012/03/14: CIA-RDP92B00181 R001901730063-1
 i
Declassified and Approved For Release 2012/03/14: CIA-RDP92B00181 R001901730063-1
The following are costs associated with this scenario:
DDT&E
Cost
STS
(Developed)
0
Spacelab
(Developed)
0
Upper Stages
(Developed)
0
TM
$ 232 MIL
*Free Flyers
(20 x $$200)
4000 NIL
Platforms
28.50
650 MIL
900
305 NIL
PEP
150 NIL
RMS
25 MIL
$5362 MIL
* The Free Flyers cost is for the bus only, not instnments.
Declassified and Approved For Release 2012/03/14: CIA-RDP92B00181 R001901730063-1
 Declassified and Approved For Release 2012/03/14: CIA-RDP92B00181 R001901730063-1
3.4.1 Description
Scenario Ha utilizes the present space transportation system (STS) augmented
with a per extension package (PEP) which extends the Shuttle on-orbit stay
time. Other elements required in the scenario are (1) free flying satel-
lites for 1991, (2) expendable upper stages for 1991, and (3) an STS-based
Teleoperator Maneuvering System (TMS).
This scenario contains a space-based OTV capability in 1992. The OTV is
launched from a manned 0TV servicing station. The ThS will also be space-
based at that time.
3.4.2 Capabilities
Scenarios Ha adds to the capabilities of scenario Ia the capability to
service and launch space-based OTV's and to mate payloads to OTV's on-orbit.
The on-orbit 0TV payload mating capability allows greater flexibility in STS
payload manifesting, thus potentially increasing the STS load factor.
Greater flexibility in satellite design is also allowed because the payload
can be assembled on-orbit prior to mating to the OTV. The number of STS
flights will also be reduced because flights to bring the expendable launch
vehicles to orbit are no longer required. Geosynchronous satellite servicing
is included in this scenario because the space-based OTV provides round-trip
transportation to geosynchronous orbit for the TMS or other servicing equip-
ment.
No attempt has been made to further enhance this servicing facility to
provide for attached payloads or laboratory modules.
The advantages of the PEP in this scenario are the same as in Scenario Ia.
Cost
STS (Developed)
0
.Spacelab (Developed)
0
Upper Stages (Developed)
0
TMS
$ 232 MIL
*Free Flyers (27 FF x $200 To
5400 MIL
Support this Scenario)
RMS
25 MIL
PEP
150 MIL
OTV Servicing Station
8608 NIL
OTV
1600 MIL
Total Cost
$16015 NIL
* The Free Flyers cost is for the bus only, not instruments.
Declassified and Approved For Release 2012/03/14: CIA-RDP92B00181 R001901730063-1
 i
Declassified and Approved For Release 2012/03/14: CIA-RDP92B00181 R001901730063-1
3.5.1 Description
Scenario IIb utilizes the present space transportation system (STS). Other
elements required in the scenario are (1) free flying satellites, (2) expend-
able upper stages (phased out in 1992), and (3) an shuttle-based Teleoperator
Maneuvering System (TMS).
This scenario adds two unmanned space platform with operational capability
beginning in 1991 and a space-based 0TV capability in 1992. The OTV is
launched fran a manned OTV servicing station. The TMS will also be
space-based at that time.
3.5.2 Capabilities
The capabilities of Scenario IIB are the sum of the capabilities of Scenarios
II and IIa. As in Scenario II the long duration missions are accanrodated on
platforms. As in Scenario IIa the OTV servicing station provides capability
for servicing and launching of OTV's, on-orbit mating of payloads to OTV's,
assembly of payloads on-orbit, and servicing of satellites at geosynchronous
orbit.
DDT&E
Cost
STS
(Developed)
0
Spacelab
(Developed)
0
Upper Stages
(Developed)
0
TMS
$ 232 MIL
*Free Flyers
(22 FF x $200)
4400 MIL
Manned OTV
Servicing Station
8698 MIL
OTV
-
1600 NIL
Platforms
28.5?
650 MIL
90?
305 MIL
Total Cost
$15795 MIL
* The free flyers cost is for the bus only, not instruments.
Declassified and Approved For Release 2012/03/14: CIA-RDP92B00181 R001901730063-1
 Declassified and Approved For Release 2012/03/14: CIA-RDP92B00181 R001901730063-1
3.6.1 Description
Scenario IIIa utilizes the space transportation system (STS). Other elements
in the scenario-are (1) free flying satellites, and (2) expendable upper
stages (PAM A, PAM-D, IUS, and Centaur) that are used to launch payloads from
the STS orbit to geosynchronous and other high energy orbits.
This scenario adds a manned Space Station that is operational in 1991 and
grows to support mission requirements. When the station is activated the TMS
will be moved from shuttle-based to space based.
3.6.2 Capabilities
In Scenario IIIa most astrophysics missions are accommodated on the Space
Station at 28.5?; in this mode they receive the benefits of both long
on-orbit stay-time and ready manned intervention. The missions that are
free-flyers in this scenario are those that were on-orbit before the' Space
Station became operational or those that have unique requirements such as
orbits that are not compatible with the Space Station.
Most of the earth science and applications missions must be acccmnodated on
high inclination orbiting free-flyers in this scenario.
The Space Station defined in this scenario has no reusable OTV capability,
therefore, the geosynchronous satellites and planetary missions will utilize
expendable upper stages as in Scenarios I, Ia, and II.
This scenario acccamrodates life sciences research. It provides laboratory
research facilities and meets the requirements for extended time on orbit with
manned interaction.
This scenario also fully enables. Materials Processing in Space (MPS) research
and development. A man-tended laboratory on the Station will be utilized to
develop these MPS capabilities which have the potential to produce both
cammercial enterprises and technology advances.
Free flying near 28.50 inclination will be serviced from the Space Station.
In this scenario the servicing facility is an integral part of the Space
Station, therefore, additional STS launches to bring up servicing equipment
are not required for servicing of satellites near the station's orbit.
The Space Station will be used to develop technology that will enhance capa-
bilities for Space Station growth, science mission execution, caminunications,
and other areas. One of the major areas to be developed, is the capability
to construct large structures on orbit. This technology is required for large
antennas, telescopes, and communications satellites. Technology will also be
developed for science missions including optics assembly techniques and earth
observation instrument development.
The high energy missions are accomplished by a space-based OTV as described in
Scenario Ha.
Declassified and Approved For Release 2012/03/14: CIA-RDP92B00181 R001901730063-1
 Declassified and Approved For Release 2012/03/14: CIA-RDP92B00181 R001901730063-1
The addition of PEP to the STS in this scenario does not increase the mission
capability since the long duration missions are accarnbdated by the Space
Station and space based TIC.
DDT&E
Cost
STS (Developed)
0
Spacelab (Developed)
0
Upper Stages (Developed)
0
TM
$ 232 MIL
*Free Flyers (27 FF x $200)
5400 MIL
Manned Space Station at 28.5? Initial
7520 NIL
Growth
4745 MIL
PEP
150 NIL
RMS
$ 25 MIL
Total Cost
$18072 MIL
* The free flyers cost is for the bus only, not instruments.
?i Declassified and Approved For Release 2012/03/14: CIA-RDP92B00181 R001901730063-1
 i
Declassified and Approved For Release 2012/03/14: CIA-RDP92B00181 R001901730063-1
3.7.1 Description
Scenario IIIb utilizes the present Space Transportation System (STS). Other
elements in the. scenario are (1) free-flying satellites and (2) expendable
upper stages (PAM A, PAM D, IUS, and Centaur) that are used to lift payloads
from shuttle orbit to geosynchronous and other high energy orbits.
This scenario adds a manned space station beginning in 1991 with growth to
support mission requirements, and a space platform at 90?. When the station
is activated the TMS will be moved from orbiter based to space-based.
3.7.2 Capabilities
With the capability of the Space Station at 28.50 and the space platform at
90? the mission requirements of astrophysics, material processing, and life
sciences are all fulfilled.
With the basic capabilities of the STS and the expendable launch vehicles for
satellite servicing, the mission requirements for solar system exploration,
and commercial ccun unication are accomplished.
DDT&E
Cost
STS
(Developed)
0
Spacelab
(Developed)
0
Upper Stages
(Developed)
0
TMS
$ 232 MIL
*Free Flyers
(22 FF x $200 To
5400 NIL
Manned Space Station at 28.5?
Initial
7520 MIL
Growth
4745 MIL
Platform
90?
550 MIL
Total Cost
$18447 MIL
* The free flyers cost is for the bus only, not instructions.
?i Declassified and Approved For Release 2012/03/14: CIA-RDP92B00181 R001901730063-1
 Declassified and Approved For Release 2012/03/14: CIA-RDP92B00181 R001901730063-1
3.8.1 Description
Scenario Ilic uses the present Space Transportation System (STS). Other
elements in the -scenario are (1) free flying satellites and (2) expendable
upper stages (PAM A, PAM D, IUS, and Centaur) until 1995.
This scenario contains a manned Space Station beginning in 1991 with growth
to support mission requirements. When the station is activated, the ZMS will
be moved from shuttle-based to space based. OTV space-based operations will
commence in 1994.
In addition, two space platforms, one at 28.5? and one at 90?, are added to
this scenario.
3.8.2 Capabilities
Scenario IIIc adds a 28.5? platform and space-based OTV to the capabilities
of Scenarios IIIa and IIIb. The OTV capability of this scenario is function-
ally the same as that of scenarios Ha and IIb, but physically it is differ-
ent because this facility is attached to an existing station rather than
being a unique facility.
The astrophysics instruments that are on-orbit at 28.5? will be the same as
those in Scenario IIIa, but telescopes and other instruments that do not
require frequent manned interaction will be placed on the Space Platform at
25.8 ? . The orbit of the Platform will be carpatible with that of the Space
Station.
In this scenario the 01V capability is fully operational in 1995. Prior to
this time the geosynchronous satellites and planetary exploration missions
will be launched with expendable upper stages. After 1995, these missions
will be accarplished with the OTV, and include satellite servicing at both
low earth and geosynchronous orbit.
The life sciences and Materials Processing in Space accarrrodations in for
this Scenario are the same as described in Scenarios IIIa and IIIb.
The technology development missions accamrodate in this scenario will be the
same as those of IIIa and IIIb.
?l Declassified and Approved For Release 2012/03/14: CIA-RDP92B00181 R001901730063-1
 Declassified and Approved For Release 2012/03/14: CIA-RDP92B00181 R001901730063-1
DDT&E
Cost
STS
(Developed)
0
Spacelab
(Developed)
0
Upper Stages
(Developed)
0
TMS
$232 MIL
*Free Flyers
(22 FF x $200 MIL)
4400 MIL
Manned Space Station at 28.5?
Initial
7520
Growth
4745
OTV Ser.
1400
OTV
1590
Platforms 28.5?
550
90?
260
$20,697 MIL
The free flyers cost is for bus only, not instructions.
Declassified and Approved For Release 2012/03/14: CIA-RDP92B00181 R001901730063-1
 Declassified and Approved For Release 2012/03/14: CIA-RDP92B00181 R001901730063-1
3.9.1 Description
Scenario IV utilizes the present Space Transportation System (STS). Other
elements in the. scenario are (1) free flying satellites and (2) expendable
upper stages (PAM A, PAM D, IUS, and Centaur) until 1995.
This scenario contains a manned Space Station beginning in 1991 with growth
to support mission requirements. When the station is activated, the TMS will
nave from orbiter-based to space-based. OTV space-based operations will
commence in 1994 and phase out the use of expendable upper stages. There
will be two platforms (one at 28.5? and one at 90?.
In addition a manned polar station has been included beginning in 1998.
3.9.2 Capabilities
Scenario IV adds a manned Space Station at polar orbit to the capabilities of
Scenario Ilic. The mission model used in support this exercise does not
presently include any missions that require a manned station at polar orbit.
3.9.3 Cost
Cost
STS (Developed)
0
Spacelab (Developed)
0
Upper Stages (Developed)
0
TMS
$232 NIL
*Free Flyers (22 FF x $200)
4400 MIL
Manned Space Station at 28.5?
Initial
7520 NIL
Growth-
4745 MIL
OTV Ser.
1400 MIL
Oil
1590 MIL
Platforms 28.5?
550 NIL
90?
260 MIL
.Manned Space Station at 90?
$5000 MIL
Total Cost
$25697 MIL
*The free flyers cost is for bus only, not instruments.
,,, Declassified and Approved For Release 2012/03/14: CIA-RDP92B00181 R001901730063-1
 Declassified and Approved For Release 2012/03/14: CIA-RDP92B00181 R001901730063-1
The ability to accomplish the nation's civil space goals have been evaluated
by comparing the capabilities of a number of scenarios beginning with the
present STS capability and progressing to a manned Space Station. A qualita-
tive survey of the scenario yields several conclusions:
1) A manned Space Station offers the unique coupling of long mission
duration in space with continuous manned interaction.
2) This coupling of long duration and manned interaction is required
for materials processing in space research and development, as well
as life sciences research and many missions in other areas.
3) The extended orbiter capability provided by the Per Extension
Package offers longer on-orbit stay time that benefits satellite
servicing missions and sortie science and applications missions;
however, it cannot provide the mission duration required to meet
the objectives of materials processing, life sciences, and the
majority of astrophysics missions.
4) The Space Platform scenarios meet the long duration requirements,
but extensive manned interaction is not provided.
5) Both the Space Station and Space Platform offer an attractive cost
avoidance through the grouping of payloads on a common buss.
6) Both the Space Station and Space Platform provide a unique capabil-
ity for ready access to multiple payloads for servicing and/or
payload change-out.
7) The Space Station as a transportation mode offers an attractive
cost avoidance because the space based OTV allows an increase in
the STS load factor and an efficient manifesting of payloads for
geosynchronous, high energy, and planetary launches.
8) The Space Station as a satellite servicing facility offers ef-
ficient, readily available service to satellites and platforms near
the Space Station orbital inclination.
9) The Space Station program provides a unique capability for tech-
nology advancement due to the developmrent of technology for the
initial and evolutionary stations as well as the technology result-
ing from the use of the station as a space oriented technology
development laboratory.
The STS was designed as a transportation vehicle to law earth orbit. Devel-
opment of a Space Station completes the system allowing each element to be
used most efficiently: the STS primarily for transportation of instruments
and supplies to law earth orbit and the Space Station as the base for long
duration mission and the permanent presence of man.
Declassified and Approved For Release 2012/03/14: CIA-RDP92B00181 R001901730063-1
 1
Declassified and Approved For Release 2012/03/14: CIA-RDP92B00181 R001901730063-1
APPENDIX A
MISSION MODEL
Table A-1 is a listing of the various missions and the flight duration.
Declassified and Approved For Release 2012/03/14: CIA-RDP92B00181 R001901730063-1
 Declassified and Approved For Release 2012/03/14: CIA-RDP92B00181 R001901730063-1
TABLE A-1 MISSION MODEL
Mission Name
Mission Duration
Missions Fran Langley Model
o Astrophysics
Spectra of Cosmic Ray Nuclei
('91-1 Yr)
Starlab
('92-'95)
Solar Optical Telescope
('91-195)
Pinhole Occulter Facility
('97-'98)
Advanced Solar Observatory
('99-2000)
Shuttle IR Telescope Facility
('93-1 Yr)
Transition Radiation & Ion Calorimeter
('94-'95)
High Throughput Mission
('96-'99)
High Energy Isotope
('97-2000)
Space Telescope
('91-2000)
Ganma Ray Observatory
('91-'93)
X-Ray Timing Experiment
('91-'92)
Far UV Spectroscopy Exp.
('93-'94)
Solar Corona Diagnostic Exp.
('99-2000)
Solar Max Mission
('91-'93)
Adv. X-Ray Astrophysics Facility
('93-2000)
Very Long Baseline Interferaneter
('95-'97)
Large Deployable Reflector
('98-'2000)
Shuttle IR Telescope Facility/Sunsynch
('98-2000)
Solar Dynamics Observatory
('91 Launch)
o Earth Science & Applications
LIDAR Facility
Earth Science Research _
(Includes SAR, IS, LTM R other)
Ocean Topography Experiment
Geopotential Research Mission
Space Plasma Physics
Origin of Plasma in Earth's Neighborhood
o Solar System Exploration
Mars Geochem/Climatol Orbiter
Lunar Geochem Orbiter
Comet Rendezvous
Venus Atmosphere Probe
Titan Probe
('92-1 Yr)
('91-2000)
('91-'94)
(191-1 Yr)
('92-'93)
(92'-95)
('91 Launch)
('91 Launch)
('91 Launch)
('94 LAUNCH)
(193 Launch)
?i Declassified and Approved For Release 2012/03/14: CIA-RDP92B00181 R001901730063-1
 i
Declassified and Approved For Release 2012/03/14: CIA-RDP92B00181 R001901730063-1
Table A-i (Continued)
o Coirmunications*
Experimental Geo. Platform
Carrminications Test Lab
PAM -D Class Satellite Deployment
Mission Name Flight Dates
Saturn Probe ('94 Launch)
Main Belt Asteroid Rendezvous (2-'97 Launches)
Saturn Orbiter ('93 Launch)
Near Earth Asteroid Rendezvous ('97 Launch)
Mars Sample Return ('99 Launch)
o Life Sciences
Health Maintenance Clinical Research ('91-2000)
Animal/Plant Vivarium and Lba ('91-2000)
Human Research Lab ('91-2000)
Closed Environmental Life Support Exp. Sys. ('92-2000)
Closed Environmental Life Support Exp. Pallet ('93-'98)
Dedicated Closed Env. Life Support Module ('99-2000)
o Pilot MPS Processes
Pilot Biological Processes ('93-'95)
Pilot Containerless Processing ('94-'96)
Pilot Furnace Processes ('94-'96)
PAM -A Class Satellite Deployment
IUS Class Satellite Deployment.
Centaur Class Satellites
PAM-D Class Satellite Servicing at GED
PAM--A Class Satellite Servicing at GED
IUS Class Satellite Servicing at GEO
Centaur Class Satellite Serv. at GED
Exchange Reconfigured Satellite
Spares On-orbit
('94 Launch)
('93-2000)
('96(3), '97(5),
198(4), '99(4), 2000(4))
('96(3), '97(3),
'98(3), '99(2), 2000(2))
(' 96 (6) , '97 (6) ,
'98(6), '99(7), '2000(7))
(196(l), '97(l),
'98(2), 199(2), 2000(2))
(199(1))
(198(l), 199(j)
2000(2))
('96(1), '97(1),
-98(l), '99(2), 2000(3))
('95(1), '96(1), '97(1),
'98(l), '99(l), 2000(2))
('95(2), '96(2), '97(3),
'98(3), '99(3), 2000(3))
* Geosynchronous launches fran 1991-1995 are listed in the STS model section.
"I Declassified and Approved For Release 2012/03/14: CIA-RDP92B00181 R001901730063-1
 Declassified and Approved For Release 2012/03/14: CIA-RDP92B00181 R001901730063-1
Table A-1 (Continued)
Mission Name
o Materials Processing (Commercial Development)
Flight Dates
Materials Processing in Space Lab #1
('91-2000)
Materials Processing in Space Lab #2
('94-2000)
Electrophoretic Separation Production
('91-2000)
Galium Arsenide Production Unit
('91-2000)
Isoelectric Focusing Production
('94-2000)
HgCdTe Crystal Production
('96-2000)
Optical Fiber Production
('93-2000)
Solution Crystal Growth Production
('97-2000)
Iridium Crucible Production
('93-2000)
Biological Processes
('94-2000)
Merged Technology/Catalyst Prod.
('93-2000)
o Earth and Ocean Observations (Cann ercial)
Remote Sensing Test/Develop. Facility
('97-6mo.)
Stereo Multi-Linear Array
('91-2000)
Stereo SAR/MIA/CZCS Instruments
('99-2000)
o Technology Development Missions
Materials Performance Technology
('91-2000)
Materials Processing Technology
('91-'94)
Deployment/Assembly/Construction
('92'94)
Structural Dynamics
('92-'94)
Design Verification Technology
('92-18no.)
Waste Heat Rejection Technology
('95-'96)
Large Solar Concentrator Technology
('96-'97)
Laser Power Transmission/Conversion
('97-'98)
Attitude Control Technology
('92-'93)
Figure Control Technology
('92-'93)
Telepresence and EVA Technology
('93-'94)
Interactive Human Factors
('93-'94)
Advanced Control Device Technology
('94-lyr & '99-lyr)
Satellite Servicing Technology
('91-'92)
OTV Servicing Technology
('91-'93)
Habitation Technology
('91-'94)
Environmental Effects Technology
('91-18mo, '96-18mo)
Medical Technology
('91-'94)
Power System Technology Experiments
('96-lyr)
On-Board Operations Technology
('92-'97)
,,, Declassified and Approved For Release 2012/03/14: CIA-RDP92B00181 R001901730063-1
 Declassified and Approved For Release 2012/03/14: CIA-RDP92B00181 R001901730063-1
Table A-1 (Continued)
Mission Name Flight Dates
Planetary Automated Orbit Cps. ('98-'99)
Large Space Antenna Technology ('93-'94)
Earth Observation Instrument Tech. ('92-'96)
Telecanrnxnications System Tech. ('96-lyr)
Space Interferaneter System Tech. ('95-lyr)
Fluid Management Technology ('91-'92)
Low Thrust Propulsion ('94-lyr, '97-lyr)
Fluid Dynamics Experiments ('94-'95)
Cryogenic Physics Experiments ('95-'96)
Space Polymer Chemistry Experiments ('95-'96)
General Relativity Experiments ('99-lyr)
Missions fran STS Model
Materials Experiment Assembly (Sortie missions in
'91, '92, '93, '94, '95,
'96, '97 & '2000)
EURECA (European free flyer) ('91, '93, '96, 199)
Materials Processing in Space Processes (Sortie missions in
'92, '94, '95, '96, '97,
'98, '99, '2000)
Tethered Satellite System (Sortie missions in
'92, '94, '95, '97,
'98, 2000)
OSTA Materials Experiments (Sortie missions in
91, '92, '93, '95)
Radar Research Mission (Sortie in '91)
Intelsat ('910), '94(3),
194(3), '95(2) Launches)
Telesat (Canadian - '91 Launch)
Satcol (Columbian - '91 Launch)
Tropical Earth Resources Satellite (Indonesia - '91,
'93 Launches)
Geosynchronous Earth Obs. Sys. ('92, '95 Launches)
NOAA TIROS ('92, '93, '94, '96,
'98, '99 Launches)
Advanced Earth Resources Satellite ('92, '94, '96, '98,
'99, Launches)
Satcan (RCA - '92(2), '93(2),
'94(3) Launches)
Galaxy Satellite (Hughes - '92, '93, '95
Launches)
Direct Broadcast Satellite ('92(2), '93(3),
'95(3) Launches)
Declassified and Approved For Release 2012/03/14: CIA-RDP92B00181 R001901730063-1
 -1- 1
Declassified and Approved For Release 2012/03/14: CIA-RDP92B00181 R001901730063-1
Table A-1 (Continued
Mission Name Flight Dates
Data Transfer
Banking
Palapa
Mexsat
Aussat
NATO
Telstar
Westar
MSAT
CXGT
IRI
TDRS
GSTAR
Syncam
('92, 94 Launches)
('92, '94 Launches)
(Indonesian '92, 94
Launches)
(Mexican '92 Launch)
(Australian 92, 93(3)
Launches)
('92, '95 Launches)
(AT&T '93, '94, '95
Launches)
(Satellite Television Corp
'93(2), '94(4) Launches)
(93(2), 94(2) Launches)
(Canadian '93, 95
Launches)
(Japanese '93 Launch)
(Italian 193 Launch)
(Tracking and Data Relay
93, 94(2), 95 Launches)
(British ' 94, '95(2)
Launches)
(GM '94(2) Launches)
(Hughes 194 (2) , 195 (2)
Launches
(Satellite Business Sys.
('95 Launch
('96(2), 97 Launches)
,,, Declassified and Approved For Release 2012/03/14: CIA-RDP92B00181 R001901730063-1
 Declassified and Approved For Release 2012/03/14: CIA-RDP92B00181 R001901730063-1
APPENDIX B
CAPABILITIES OF SUPPORTING ELEMENTS
The SIG scenarios involve the incorporation of various specific hardware
elements to acclish mission goals. This appendix describes each of these
elements and presents general performance capabilities of the elements. The
supporting elements discussed herein are:
1.
Space Transportation Systems (STS)
2.
Power Extension Package (PEP)
3.
Teleoperator Maneuvering System
(TMS)
4.
Free-Flying Spacecraft
5.
Unmanned Space Platforms
6.
Spacelab
7.
Orbital Transfer Vehicles (Ground and Space-Based, Reusable and
Expendable).
8.
OTV Servicing Facility
9.
Space Station
1. SPACE TRANSPORTATION SYSTEM (STS)
STS is used as an integral part of each scenario and will be used to
place all elements in low-earth orbit (LEO).
The Orbiter on-orbit stay time is limited by the amount of consumables
and their rate of consumption. Pacer is one of several consumables that
limit the STS stay time. A nominal power level of 18-20 kW, limits the
on-orbit stay time to 7-10 days depending on the number of cryogenic tank
sets installed.
2. POWER EXTENSION PACKAGE (PEP)
The PEP is a 2000-pound solar array kit which provides most of the
required Orbiter/payload electrical per during light-side orbit periods.
This relieves the baseline Orbiter cryogenic oxygen and hydrogen storage
limitations on mission duration and increases per available to payloads.
Note that to increase the stay time of the STS, systems other than just the
per system must be modified.
The PEP solar array is held in the desired attitude and location by the
RMS with the PEP providing two-axis sun tracking. More than one RMS position
can be used for any Orbiter orientation. This flexibility allows minimal
interference with payload viewing.
PEP operates with the regulated solar power in parallel with the Orbiter
fuel cells. When in sunlight, the Orbiter fuel cells are off-loaded to
conserve fuel cell reactants (and may, indeed, actually be enhanced by
electrolysis).
,,, Declassified and Approved For Release 2012/03/14: CIA-RDP92B00181 R001901730063-1
 Declassified and Approved For Release 2012/03/14: CIA-RDP92B00181 R001901730063-1
3. TELEOPERA'IOR MANEUVERING SYSTEM ('IS)
There will be two distinctly different ThIS systems. TM-1 will be
available for-all scenarios and will be limited to the capability of deploy-
ing and/or retrieving free-flying spacecraft to/fran the proximity of the
Orbiter or to/fran the Space Station. TMSl will not have the capability of
performing payload servicing remotely from the Orbiter or Space Station.
TMS-2 will be available for all scenarios. TMS2 will be a general-pur-
pose, remotely-controlled, free-flying vehicle capable of performing a wide
range of payload service remotely from the STS or Space Station. The system
will provide spacecraft placement services, planned or contingency payload
retrieval functions, assembly/ servicing support for large space systems,
dextrous manipulator operation for planned or contingency satellite ser-
vicing, satellite viewing and science support as a free-flying subsatellite
operating in the vicinity of the STS or Space Station, resupply, change-out,
etc.
For Scenarios IIa, IIb, Ilic and IV, ThI.S can be space-based. The TMS
will receive routine service and repair in orbit. For major repairs or major
refurbishment the ThI.S will be retrieved and returned to earth by the Orbiter.
When the ZMS is Orbiter-based, it will be returned to earth in the Orbiter
payload bay at the completion of each servicing mission. The TMS for Scenar-
ios IIIa, IIIb, IIIc and IIId will be space-based at the Space Station where
it will be harbored, serviced, and maintained.
Free-flying spacecraft include all dedicated mission satellites that
cannot be accanrodated in Space Platforms or attached to a Space Station
because of unique orbit location or unique instrument environmental re-
quirements. For Scenarios I,_ IA, and IIA this class of satellites includes
all missions that are not accamndated in the Orbiter crew area or in the
Spacelab.
The unmanned space platform is a spacecraft bus that provides the key
resources of power, thermal control, data transmission, and attitude control.
Multiple payloads are attached to this bus and operated simultaneously. The
payloads may all be of the same discipline, e.g., astronomy, or a platform
may accommodate a set of multi-disciplinary payloads. The platform design
allows payloads to be reproved and replaced with new ones on-orbit when the
mission is complete or improved instruments are available.
Significant savings in the design and development costs for multiple
platforms will be realized by utilizing a cannon design for all platforms
(high or low inclination). The design will be modular to allow for appro-
priate scaling and on-orbit expansion of the electrical, thermal and other
capabilities of the platforms. Initially each platform will provide approxi-
Declassified and Approved For Release 2012/03/14: CIA-RDP92B00181 R001901730063-1
 Declassified and Approved For Release 2012/03/14: CIA-RDP92B00181 R001901730063-1
mately 12 kW of electrical power and heat rejection capability. The modular
design will allow on-orbit "growth" (e.g., by the addition of more solar
array panels) if additional resources are required in the future.
6. SPACELAB/SORTIE
Under international agreement, the European community has provided to
the U.S. Space Program a system of Orbiter cargo bay experiment mounting
facilities. The system includes two types of manned laboratories, i.e.,
short and long modules. Also included are several three meter length pallets
and environmentally controlled subsystems in an "igloo" unit. All integra-
tion and reconfiguration costs of the above hardware are the responsibility
of the U.S. Space Program. Sortie missions are those flying in the Spacelab
module or on a Spacelab pallet.
7. ORBITAL TRANSFER VEHICLES (OIV'S)
a. Ground-based Upper Stages (STS-Catpatible)
The initial STS will make use of a family of upper stages to transport
payloads beyond LEO. Included is a class of expendable solid rockets, the
largest being the IUS, capable of transporting 5,000 pounds from LBO to GEO.
Another ground-based OTV currently under development is the ground-based,
Shuttle-deployed, Centaur vehicle. The Centaur's performance permits trans-
fer to GED for payloads of up to 13,500 pounds. They are all expendable
vehicles, adaptable to mating either on the ground or in space, and not
optimized for space-based use.
Reusable, Space-Based OTV's
Scenarios IIa, IIb, IIIc and IV assume the development of a reusable,
space-based OTV for transporting payloads from LEO to their final earth-or-
bital destination. These vehicles will be transported to the LEO Space
Station or OTV servicing facility by the STS and will be maintained and
serviced at the Space Station.
The reusable space-based 0TV has been assumed to be a cryogenic, aero-
braked stage with geosynchronous orbit capability equal at least to that of
the Shuttle-based Centaur, i.e., 13,500 pounds. The capability to service
GEO-based payloads with an OTV/TMS combination would be available at the
inception of Space Station/OTV service facility operation. The OTV would be
of modular space-based design to allow maintenance, servicing and mission
modifications on-orbit.
8. O'I'V SERVICING FACILITY
The permanent OTV servicing facility will consist of the following
elements:
a. An unpressurized enclosure with the necessary equipment to service,
maintain, and protect the OTV from meteoroids and space debris during servic-
Declassified and Approved For Release 2012/03/14: CIA-RDP92B00181 R001901730063-1
 i
Declassified and Approved For Release 2012/03/14: CIA-RDP92B00181 R001901730063-1
ing and storage. A high level of automation will be employed to perform
servicing and checkout functions. The crew will repair, maintain and provide
backup for the automated equipment through EVA.
b. A similar unpressurized protective enclosure for service, mainte-
nance and checkout, will be utilized for OTV payloads. A common remote
manipulator system (IM) on tracks will provide a means of receipt, deploy-
ment, mate/demate and transfer for both the OTV and the OTV payloads.
C. A pressurized module to provide accommodations to support a crew of
approximately four for up to 30 days, plus contingency time, will be
provided.
d. An unpressurized utility element to provide electrical power (30 )
avg) for all facility elements (including propellant reliquefaction). The
attitude control and reboost system will be contained in this module.
e. A central core element with external viewing ports will house the
OTV and RMS control stations. Air locks and berthing ports will provide
ingress/egress and allow Orbiter docking.
f. A logistics module of sufficient volume to house consumables for
the crew for the allotted stay time, the waste management system, and for OTV
spares.
The permanent facility in space which is manned is termed the "Space
Station." However, the characteristics and capabilities of the Space Station
vary with the different scenarios. These characteristics and capabilities
are delineated into two general types of Space Stations: (a) initial and (b)
growth. -
a. Initial
This manned Space Station will support technological, canrercial, and
scientific research and development laboratories. It will also support a
satellite servicing capability.
The capabilities of this Space Station are described as follows:
o Provide laboratory facilities (including power, environment con-
trol, data management, etc.) as well as permanent-manned-presence
in order to conduct research and development in technological,
cammercial, and scientific disciplines.
o Accammcdate attached, unpressurized payload pallets with accurate
pointing and environmental control in addition to pressurized
laboratory modules for research and development pursuits.
o Retrieve free-flying satellites to the Space Station by means of
the Teleoperator Maneuvering System (ThIS) for servicing by EVA
and/or place free-flying satellites into their operational orbits
with the CIS.
q Declassified and Approved For Release 2012/03/14: CIA-RDP92B00181 R001901730063-1
 Declassified and Approved For Release 2012/03/14: CIA-RDP92B00181 R001901730063-1
o Service, refuel, replenish consumables, change experiments and/or
payloads, and repair failed subsystems of free-flying satellites at
the Space Station.
o Store propellants for the TMS, satellite refueling, and Space
Station orbit maintenance at the Space Station.
b. Growth
The growth station includes (1) a phased increase of laboratory capabil-
ity and (2) support for a space-based reuseable orbital transfer vehicle
(OTV) .
The space-based, reuseable orbital Transfer Vehicle (OTV) will provide
access to geosynchronous orbit and beyond. The manned Space Station at which
the OTV is based will becorre a transportation mode to serve all user carinu-
nities. This station will have the capability to:
o Provide structure for OTV docking, servicing, refueling, and
payload mating.
o Coordinate OTV servicing, launch, and retrieval.
o Provide facilities for OTV propellant storage and handling.
II Declassified and Approved For Release 2012/03/14: CIA-RDP92B00181 R001901730063-1