A NASA CAPABILITIES EVALUATION DOCUMENT

• Document Type: CREST
• Collection: General CIA Records
• Document Number (FOIA) /ESDN (CREST): CIA-RDP85M00364R000400550056-0
• Release Decision: RIFPUB
• Original Classification: K
• Document Page Count: 34
• Document Creation Date: December 21, 2016
• Document Release Date: July 30, 2008
• Sequence Number: 56
• Publication Date: June 24, 1983
• Content Type: REPORT

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A NASA CAPABILITIES EVALUATION DOCUMENT
June 24, 1983
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SIG DOCUI4FNT
Table of Contents
- Page
1.0
2.0
INrA00 Jc'ncN
MM MM=
2.1
Mission Model
2.1.1
2.1.2
Mission Model Development
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 Est irrating
2.2.1 I YT&E Costs
3.0 SCD R1OS
3.1
Scenario I
3.1.1
Description
3-3
3.1.2
Capabilities
3-3
3.1.3
Cost
3-4
3.2
Scenario Ia
3.2.1
Description
3-5
3.2.2
Capabilities
3-5
3.2.3
Cost
3-5
3.3
Scenario II
3.3.1
Description
3-6
3.3.2
Capabilities
3-6
3.3.3
Cost
3-7
3.4
Scenario Ila
3.4.1 Description
3-8
3.4.2 Capabilities
3-8
3.4.3 Cost
3-8
i
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3.5
Scenario Iib
3-9
1
5
3
Description
.
.
2
5
3
Capabilities
3-9
.
.
3-9
3.5.3
post
3.6
Scenario IIIa
3-10
1
6
3
Description
.
.
2
6
3
Capabilities
3-10
.
.
3-11
3.6.3
Cost
3.7
Scenario IIIb
3-12
7
1
3
Description
.
.
2
7
3
Capabilities
3-12
.
.
3-12
3.7.3
Cost
3.8
Scenario IIIc
3-13
8
1
3
Description
.
.
3
2
8
Capabilities
3-13
.
.
3-14
3.8.3
Cost
3.9
Scenario IV
3-15
1
9
3
Description
.
.
3
9
2
Capabilities
3-15
.
.
3-15
3.9.3
Cost
APPS DIX B: CAPABILITIES OF SUPPOKTING EtDg3JTS B-1
4.0 SU419 Y
APPENDIX A: MISSION MDDEL
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1.0 INTT40DUC'TICN
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
tune 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
fora 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 developnental cost of each of the scenarios.
The approach used is to increase capabilities incrementally fram one scenario
to the next. The scenarios begin with the "baseline" of today's STS capabil-
ity augmented by a Teleoperated maneuvering System (MS) and progress through
options of varying capabilities to a manned Space Station scenario. The
scenarios are shoran 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 develop? ent costs
and their life cycle cost would be used to determine the benefit of the a55ed
capability. To determine the value or benefit of each capability, a nor-
malization of scenario to scenario of long duration missions (years) would
require an exorbitant number STS launches. The cost of these additional
launches (at $122 M average for Eastern Test Range or Western Test Rance
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 conclusions drawn from this evaluation are
presented in the Summary Section 4.0.
The mission model is the result of a one year NASA effort of planning mission
sets that represent the Agency's plans for the period 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. Upon examination, many mission
requirements can be at least partially net with existing facilities, e.g., a
free flying satellite allows long mission duration and STS sortie missions
allow manned interaction, but only the Space Station provides both long
duration missions and manned interaction.
Fbllewing the mission analysis study and the architectural options survey,
the costs data for the Design, Development, Vest, 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 DOLT&E cost offers additional understanding to evaluate the
added capabilities.
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Finally, Section 3.0 develops an evaluation of each scenario to determine if
the scenario aooamodates the mission set and provides the cost for added
capability.
This doc-zr ent is based an a first iteration of a set of space Ipi s lions and a
Space Station concept that will continue to be refined in the next few
months.
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2.0 M rHODOIDGY
2.1 P41SSICN MODEL
2.1.1 Mission Model DevelcpTmt
The mission model was developed by merging the "STS Mission Model 1983-2000
-- Ncminal Version" (Advanced planning Division, TULSA Headquarters, Decerrber
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 three major areas: Science and Applications, CcCrrercial, and Technology
as a means to merge the results of the industry Mission Analysis Study
results of the past year with ?ZiSA's space mission plans. This activity can
be perceived as one of refocusing MZSA mission plans to include a capability
in excess of the present STS in terms of orbit stay time. This need has been
recognized for any years, but mission planning has been constrained by the
lack of long-term, manned cn-orbit capability.
The term "mission" is used very broadly in this model. In same cases, the
term refers to (1) a single instrur,ent (e.g., a telescope), or (2) a single
launch of a spacecraft, or (3) a series of experiments.
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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 Mown as missions requiring one to ten years on-orbit to
complete their mission objectives. The long duration is required because the
observation of just one object can require integration of photons over a
period of hours or days and many objects must be surveyed and compared;
simultaneous observations at several different wavelengths are often rewired
for each object; and detection of changes over periods of years are often
important. 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 an-orbit with extensive crew involvement. The rrajor objective
of these missions is to understand, and develop counterrreeasures for, the
effects of lack of gravity on humans.
2.1.2.5 Conrrranication Satellites. The ccrnmanications 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 time on orbit with extensive manned interaction.
This facility would allow realization of the potential of WS research to
yield new ai,r ercial enterprises and technology advances.
2.1.2.7 Satellite Servicing. On-orbit satellite servicing in low earth
orbit is e>,pected to became 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
instnments, and, in some cases, on-orbit assembly and deployment of satel-
lites. Servicing satellites at geosynchronous orbit is also proposed.
2.1.2.8 Technology bevel tt. 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. Scree of the missions provide significant
technology development for areas such as large antenna developTent for
commercial ccmmmication.
2-2
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2.2 COST ES IMA77 1G
The cost estimates used for the Space Station System were derived from a cost
model developed by NASA. This model is based on a historical manned space-
craft (Gemini, Apollo, Skylab, Spaoelab, STS orbiter) and urrrani ed spacecraft
(Landsat, HEAD, ATS, and others) data base. This model uses cost estimating
relationships (CSR's) to determine the subsystem and system level costs. The
CER's in the cost model were developed from 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 new elements (i.e., PEP, Platform, Space Station, see Appendix B for
details) are required to support a scenario, a DDT&E cost for the ele7ent is
factored into the total cost. The cost includes design and development of
such items as structures, thermal control, electrical paver, ccrrunications,
data handling, attitude control, and environmental control and life support
subsystems. It also includes the systems test hardware, integration,
asse-rbly, checkout, ground support equipment, and program re-naoement cost
estimates. The initial DDT&E cost includes the cost of the first unit. If
additional elements (second buy's) are required, these elements are proxurer
at a significantly lower price since the initial units include the design and
development cost.
Exa-rples of second unit cost can be seen by revierNing DDT&t cost for Scenario
II. The cost of the 28.5? Space Platform is $650 M. The cost for the 90`
Space Platform (a second unit) is $305 M.
Another exarrple of reduction in cost for like elements can be_ seen in Scen-
ario IIIc. The cost for the first 2B.5` Space Platform is $550 MIL less than
in Scenario II since same development cost is covered by the Space Station
development. The second Space Platform (90?) for this Scenario is also less
($260 t IL) .
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 from 1991 through 2000. The life cycle cost utilized for the STS
was based on STS historical data which includes the ground processing an3
flight operations costs for each flight. However, as stated in the introdu:-
tion, this operational life cycle cost was not used.
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3.0 SCET]AR1OS
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 per extension package, has
been added to some of the scenarios to evaluate its ability to fulfill the
miA,sion model requirements
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T11BTE 3.1
II
lib
Illa
111b
111c
IV
I=
II
a
_I
ms
STS
STS
STS
Sets
Srs
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
7m
71''LS
7m
Im
,n? S
TMS
?
im
?
0
TLS
5
PEP
SP28.5?
PEP
SP900
SS28.5
SS28.5
0
SS28.5
?
SS28.5
?
SP900
SBO-IV
SP28.50
PEP
SP90
SP90
SP90
o
PEP
OTV/SS
SBmV
Orv @SS
0
SP 28.5
?
cnv/SS
SP 28.5
SS90
OFV @ SS
STS - SPACE TPIWSPORTIITICN IM - TEUXYE.N-TOR MANEW ING SYSTI?1 SBOVF - SPACE BASED ORBITER TRANSFER VERME
SY5TP31 PEP - POWER EXTF 4SIC7N PM K G1 (PEP) MPS - MATERThIS PROCESSING IN SPACE
S/L - SPACELM - SOTQ'IES MV/SS - ow SPACE TIT TiM ON @LSS - OTV CAPABILITY AMED '10 E(ISrrNG
U/S - UPPER STAGES SPACE STATION ~ ~
FF - FM FLYERS SS - SPACE STATION
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3.1 sCEN B1o I
3.1.1 Description
present STS system augmented with ..an STSbased
Tesorer Ileoperator utilizes Maneuvering the System (71-S) to enhance capabilities fcar deployment, retravial, service, and on-orbit maintenance of free flying
and a satellites.
le
other elements in the scenario are free flying
upper stages (PAM-A, PAP D, IUS, and Cr' taur) that are used to lipayloads
from the shuttle orbit to geosynchrmo-ls and other high energy orbits.
3.1.2 Capabilities
The Materials Processing missions preferred node of accarmodation is the
Space Station. These missions require long duration, uninterrupted time
on-orbit with extensive manned interaction. These missions cannot be accorrr
nodated by the capabilities of this scenario. A limited amount of research
can be acccrplished by STS sortie flights. These limited R&D missions could
provide early precurser equipment development leading to the eventual product
cality, but the potential of materials processing in space cannot be
plyi
fully developed with intermittent
at~ss~ rel ur,ching the in ~u~~,ts for
require the expense of re-integr g
only a wee):'s a perimeantation.
The astrophysics missions require long tire on-orbit (one to ten years) and
many of these missions also desire manned involverent foservicing
adjustment of instruments. The total mission set cannot be
within the capabilities of Scenario I. Sam of the missions will be flaan as
free-flying satellites. The remaining missions will be placed on STS sortie
flights, where they do receive the benefit of manned involvet; but in this
o the
case, the attainment of mission objectives is severely limited because Starlab
cbser-
short duration of the STS flights. For example, iis such uast and Solar optical Telescope that need three to four years
_
vation time are limited to one or pore STS mistime of
u~~ tfore even
days each. Since several days of outgassing
observations can be performed with these instruments, the amount of good
quality data obtained is questionable.
Life science missions require extended, uninterrupted time on-orbit with
extensive crew involvement. These missions cannot be fulfilled in this
scenario. Only precursor experiments can be accomplished in this scenario
(flying these experiments as sortie missions an the STS). The long
manned
objectives of these missions can only be accxrplished with a permanent
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 an free flyers in this scenar .chose
missions requiring man intervention because of the complexity of the vents, will be flown as S1 sortie s ion mission but again the short duration on
orbit severely buts the attainment of Satellite servicing missions preferred accommodation nodes are, satellite return to the on-orbit servicing facility, or remote servicing at the
3-3
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satellite location. These missions can be accarrplished with the STS, 7MS,
and expendable launch vehicles. However, the servicing equipment mist be
brought to orbit on planned STS flights for each mission.
Ccmnunications satellites which require geosynchr?nous orbit will be launched
via the STS with an expendable upper stage (PAM-A, PAM D, RE, oxr'Centaur).
Since the technology development missions in this model were designed
specifically as Space Station missions, most of the objectives cannot be
accovplished in this scenario. However, different versions of many of these
missions could be done an the 515. Additionally, the STS can be used to
enhance the technology required to build the initial Space Station.
The STS can be utilized for the developrent of same techniques and equipment
for eventual use by the Space Station in fulfilling same of its mission
objectives (e.g., satellite servicing).
In Scenario the solar
(IUS or Centaur) launched flan the STSc~lished
with expendable upper
The following are the cost associated with Scenario I:
Dt7T&E Cost
Cost
STS
(Developed)
0
Spacelab
(Developed)
0
Upper Stages
(Developed)
0
7MS
$ 232 NIL
*Free Flyers
(26 FF x $200)
$5200 NIL
Total Cost
$ 5432 NIL
The Free Flyers cost is for the bus only, not instruments.
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3.2 SCMkPIOIA
3.2.1 Description
This scenario utilizes the present STS system augmented wittr (1) a power
extension package (PEp) which extends the shuttle on-orbit stay time from a
maximm of 7 to 20 days and (2) a STS based telecperator maneuvering system
(S) 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 (PAN A,
PAM-D, RS, and Centaur) that are used to lift payloads from the shuttle
orbit to geosynchronous and other high energy orbits.
3.2.2 Capabilities
Tne major change in capabilities to this scenario fram Scenario I, is the
addition of the PEP (Power Extension Package). This addition has a small
iJrpact on the fulfilling of the mission model. The significant impact is in
the increased orbitor stay tine for the Spacelab/sortie missions. Most
sortie missions benefit is an increase in the on-orbit staytirre, but still
fail to acccrplish a significant fraction of the mission objectives.
DDT&E
Cost
STS
(Developed)
0
Spacelab
(Developed)
0
Upper Stages
(Developed)
0
T
$232 MIL
-*Free Flyers _
-(27 x $200 To Support
5400 MIL
The Scenario)
PEP 150 MIL
RMS $ 25 MIL
Total Cost $ 5807 MIL
* The free flyers cost is for the bus only, not instruments.
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? 3.3 S(~~'IOII
3.3.1 Description
Scenario II utilizes the present STS system augmented with a per ext nsion
package (PEP) which extends the Shuttle on?orbit stay time from (7 Ito to
maximiin of 20 days and a STS based Teleoperator Maneuvering System
roe capabilities for deployment, retrieval, service, and on-orbit r,iinten-
anoe of free flying satellites. Other elements in the scenario arc free
flying satellites and expendable upper stages (PAM-A, PArS-D, IUS, an- Cen-
taur) that are used to lift payloads from the shuttle orbit to geosynch-onus
and other high energy orbits.
-The major elements added to this scenario- ever previous scenarios are space
platforms located at 28.5? and 90? inclinations.
3.3.2 Capabilities
In Scenario II, the long duration astrophysics missions are acccrmndated an
the platforms. They provide indefinite on-orbit stay time; however, there is
a small percentage of tine that manned interaction is available. ?an is
present only during periodic STS servicing /supply missions -- probably twice
a year. The addition of PEP to the STS in this scenario does not increase
the mission accommodation capability, but does provide longer servicing
periods. Another consideration for the astrophysics missions in this scen-
ario is that the platforms are cost-effective because the instrumnts are
placed on a cannon bus, thus saving design, development, and production
costs.
The long duration earth science and applications missions are accorrn dated on
the platform-with the save advantages and restrictions as for the astro-
physics missions.
The solar system exploration ande eosynchron s asattelltthe e previous io ssoere stages launched from the STS with expendable
arios.
The same limitations identified in Scenario Ia apply to life science missions
in this scenario.
The aceomodation of Materials Processing Research is also inhibited as in
Scenario Ia, because of the short duration orbit time of the Shuttle.
Satellite servicing in this scenario will be performed fram the STS as in the
Scenario Ia. The servicing of instruments grouped or mounted on the plat-
forms will be more efficient because servicing can be done in tandem with the
platform resupply missions.
The accommodation of Technology Development missions in this scenario is
similar to that of Scenarios I and Ia.
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The Free Flyers that are included in this scenario are those that were
cn-orbit before the Space Platform, those that require unusual orbits or have
other unusual characteristics incompatible with the Space Station orbit, and
those that have been launched beyond low earth orbit for solar system explor-
ation or geosynchrormous missions.
3.3.3 Cost
The follcuing are costs associated with this scenario:
UYP&E
Cost
STS
(Developed)
0
Spacelab
(Developed)
0
Upper Stages
(Developed)
0
TMS
$ 232 YCL
*Free Flyers
(20 x $$200)
4000 MIL
Platforms
28,50
650 MIL
900
305 NIL
PEP
150 MIL
RMS
25 NIL
Total Cost
$5362 MIL
* The Free Flyers cost is for the 2ris only, not instr r eats.
3-7
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. 3.4 SCENARIO IIa
3.4.1 Description
space transportation system (5 S) augmented
Scenario IIa utilizes the present
with a power extension package (PEP) v*dch extends the Shuttle-on-orbit stay
time. Other elements required in the scenario are (1) free flying vastly
lites for 1991, (2) expendable upper stages for 1991, and (3) an STS based
Tlelecperator Maneuvering System (7MS).
based O1V capability in 1992. The OTV is
This scenario contains a spa
launched from a manned MV servicing station. The 7MS will also be space-
based at that time.
3.4.2 capabilities
Scenarios IIa adds to the capabilities of scenario Ia the capability to service and launch space-based (TV's and to mate payloads to OrV's on-
Orbit-The oar-orbit MV payload grating capability allows greater flexibility in M
payload manifesting, thus potentially increasing the STS load factor.
Greater flexibility in satellite design is allowed because the payload can be
assembled on-orbit prior to mating to the diV. The nurber launch f STvflig is
will also be reduced because flights to bring the expendable c
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 7TLS or other servicing egsip-
nent.
This station has no capability to provide for attached payloads or laboratory
modules. The acccrrodation of missions that do not use the DiV are the sane
as in Scenario Ia.
The advantages of the PEP in this scenario are the same as in Scenario Ia.
3.4.3
Cost
DDT&E
cost
STS (Developed)
0
0
Spaoelab (Developed)
0
Upper stages (Developed)
232 DM
TMS
,
$
*Free Flyers (27 FF x $200 To
5400 Mn
Support this Scenario)
25 MIL
PEP
150 MIL
DTV Servicing Station
6808 MIL
IL
0
M
160
07V
Total cost
$14215 MIL
The Free Flyers cost is for the bus only, not instruments.
3-8
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3.5 SCENhRI0 IIb
3.5.1 Description
Scenario IIb utilizes the present space transportation system _(STS). Other
elements required in the scenario are 11) free flying satellites, (2) expend-
able upper stages (phased cut in 1992), and (3) an shuttle-bases] Teleoperator
Maneuvering System (714S) .
This scenario adds two unmanned space platform with operational capability
beginning in 1991 and a space based MV capability in 1992. The OTV is
launched from a manned ow servicing station. The ZMS will also be
space-based at that time.
3.5.2 Capabilities
The capabilities of Scenario IIB are the sun of the capabilities of Scenarios
II and IIa. As in Scenario II the long duration missions are acccrrodatedon
platforms. As in Scenario IIa the ow servicing station provides capability
for rbly of rog orbit f and servicing of satlenlglite payloads to MV's,
eosynchr ro ous
asse~n'oly payloads on-
orbit.
3.5.3
Cost
t
C
os
STS
Spacelab
Upper stages
"WC
(Developed)
(Developed)
(Developed)
0
0
0
$ 232 MIL
*Free Flyers
(22 FF x $200)
4400 MIL
Manned OIV
Servicing station
6808 KM
O TV
1600 MIL
Platforms
28.5?
550 M]1
900
260 MIL
Total Cost
$13850 KIL
* The free flyers cost is for the bus only, not insts .nts.
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3.6 SC EKhRIO Il la
3.6.1 Descri ion
space transportation system (STS)- Other elements
in the Scenario scenario utilizes the satellites, and (2) expendable upper
enario are (1) free flying
stages (PAM A, PAM D, ILLS, and Centaur) that are usedo launch payloads from
the -STS orbit to geosynchron us and other high energy
This scenario adds a manned space Station that is operational in 1991 and
grows to support mission requirements. When the station is activated the 71S
will be moved from shuttle-based to space-based.
3.6.2 Capabilities
In Scenario III o 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 mww-od intervention. The missions that are
free-flyers in this scenario those that have unl on-orbit ~bef~o~re~ cSpaa
Station became operational or orbits that are not compatible with the Space Station.
Most of the earth science and applications missions mst be acca*r- ted on
high inclination orbiting free-flyers in this scenario.
The Space Station defined in this scenario has no reusable MV cap bility,
therefore, the geosynchronous satellites and planetary missions will utilize
expendable upper stages as in Scenarios I, Ia, and II.
This scenario acconrodates 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 (TIPS) research
and development. A man-tended laboratory on the Station will
produce both
develop these MPS capabilities which have the potential
oamercial enterprises and technology advances.
near 28.50 inclination will be serviced fran the Space Station.
Free flying
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, communications, and other areas. One of the major areas to be developed, is the capability
structures on orbit. This technology is required for large
to construct large cations satellites. Technology will also be
antennas, telescopes, and oammmuni
developed for science missions including optics assembly techniques and earth
observation instrument developent.
The high energy missions are accomplished by a space-based 01V as described in
Scenario IIa.
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The addition of PEP to the STS in this scenario does not increase the mission
capability since the long duration missions are acccrmodated by the Space
Station and space based 7iS.
The Free Flyers that are included in this scenario are those that were
on-orbit before the Space Station, those that require unusual orbits or have
unusual characteristics inearrpatible with the Space Station orbit, and those
.that- have been launched beyond low earth orbit for solar system exploration or
geosynchronous missions.
3.6.3 Cost
Cost
STS (Developed)
0
Spacelab (Developed)
0
Upper Stages (Developed)
0
Zl,iS
$ 232 MIL
*Free Flyers (27 FF x $200)
5400 MIL
)!armed Space Station at 26.5?
Initial
7520 MIL
Growth
4745 MIL
PEP
150 MIL
P'S
$ 25 MIL
Total Cost
$36072 MIL
* The free flyers cost is for the bus only, not instnr:ents.
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3.7 SCD RIO 11Th
3.7.1 Description
Scenario 1Im 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
fram shuttle orbit to geosynchrorous and other high energy orbit.
This scenario adds a marred space station beginning in 1991 with growth to
platform at 90?. When the station
support mission requirements, and a space P based.
is activated the R1S will be moved from orbiter based to spa
3.7.2 Capabilities
ili of the Space Station at 28.5? and the space platform at
With the the mission ~' ragare~nents of astrophysics, material processing, and life
i
90
sciences are all fulfilled.
with the -basic capabilities of the STS and the expendable launch vehicles for
satellite servicing, the mission reauire:rernts for solar system exploration,
and canrercial conrrrlnication are accomplished'
3.7.3
Cost
Cost
STS (Developed)
0
0
spacelab (Developed)
0
Upper stages (Developed)
232 1 L
S
*Free Flyers (22 FF x $200 To
?
4400 J' L
Manned Space Station at 28.5
7520 r~
Initial
Growth
4745 MIL
90?
550 MIL
Platform
Total Cost
$17447 AFL
* The free flyers cost is for the bus only, not instructions.
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3.8 SCENARIO 111c
3.8.1 Description
Scenario IIIc uses the present Space Transportation Systan'(STS). Other
elements in the scenario are (1) free flying satellites and 12) expendable
upper stages (PAM A, PAM D, RE, 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. OI'V 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 28.50 platform and space-based OTV to the capabilities
of Scenarios Ilia and IIIb. The O1V capability of this scenario is function-
ally the sane as that of scenarios IIa and lIb, but physically it is differ-
ent because this facility is attached to an existing station rather than
being a unique facility.
The astrophysics instranents that are on-orbit at 28.5? will be the same as
those in Scenario ilia, but telescopes and other instnrnents that do not
require frequent manned interaction will be placed on the Space Platform at
28.5?. The orbit of the Platform will be cc patible with that of the Space
Station. In addition to allowing the total required mission duration, this
scenario offers the astrophysics missions a choice between a manned station
(for the benefits of readily -available iranned intervention) and an un a-used
platform (for the benefits of very low disturbance levels. cam`? ned with the
periodic availability of manned intervention via servicing from the station).
In this scenario the OTV 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 aeccnplished with the ON, and include satellite servicing at both
low earth and geosynchronous orbit.
The life sciences and Materials Processing in Space aecc rnodations in for
this Scenario are the sane as described in Scenarios Ilia and 111b.
The technology development missions aceamndate in this scenario will be the
sane as those of :Ilia and 111b.
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3.8.3
Cost
Wr&E
t
Cos
STS
(Developed)
0
S aaoelab
(Developed)
0
Upper Stages
(Developed)
0
$232 KIM
*Free Flyers
(20 FF x $200 MIL)
4000 KM
Manned Space
Station at 28.50
Initial
7520
Growth
4745
OTV Ser.
1400
1600
07V
Platforms
28.5?
550
90?
260
Total Cost
$20,307 rM,
The free flyers cost is for bus only, not instructions.
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3.9 S( MA-RIO IV
3.9.1 Description
Scenario IV utilizes the present space Transportation Systan-(STS). Other elements in the scenario are (1) free flying satellites and (2) expendable
upper stages (PAM A, PAM D, n Z, 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 TLS will
move from orbiter based to space based. OW space-based operations will
camence 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 ands a manned Space station at polar orbit to the capabilities of
Scenario IIIc. 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
0
Spacelab
(Developed)
0
Upper Stages
(Developed)
$232 rIL
7MS
*Free Flyers
(20 FF x $200)
?
4000 MIL
Fanned Space
Station at 28.5
7520 NSI
Initial
Grow-th
.
4745 KM
OlV Ser.
1400 KM
1600 MU
cry
?
550 AFL
Platforms
28.5
?
260 KM
wed Space Station at 90?
Total Cost
$5000 M1.
$25307 KI.
*The free flyers cost is for bus only, not instruments.
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4.o Suer
The ability to acocriplish the nation's civil space goals have been evaluated
by ccriparing the capabilities of a nuTber 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 developrent, as well
as life sciences research and many missions in other areas.
3) The extended orbiter capability provided by the Power 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
all of the objectives of materials processing, life sciences, and
the majority of astrophysics missions.
4) The Space Platform scenarios meet the long duration require-ents,
but extensive panned interaction required for specific missions is
not prcr'ided.
5) Both the Space Station and Space Platform offer an cost avoidance
through the grouping of payloads on a corrrron bus.
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 enables a reusable space-based aiV that has the
potential of increase in the STS load factor. This is acccrplished
by manifesting more individual payloads per launch, since the
expendable stages are not required. As such, the Space Station as
a transportation node can offer same cost avoidance.
8) The Space Station as a satellite servicing facility can offer ef-
ficient, readily available service to satellites and platforms near
the Space Station orbital inclination.
9) The Space Station program could provide a unique capability for
technology advancement due to the develogrent 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
develognent laboratory.
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APPLNDIX A
MISSION MODEL
Table A-1 is a listing of the various missirns and the flight--duraticn.
A-1
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TABLE A-1 MISSION MODEL
Mission Name _
Missions Fran I&ngley Model
C) Astrophysics
Spectra of Msmic Ray Nuclei
Starlab
Solar Optical Telescope
pinhole occulter Facility
Advanced Solar Observatory
Shuttle IR Telescope Facility
Transition Radiation & Ion Calorimeter
High Throughput Mission
High Energy Isotope
Space Telescope
Garin a Ray Observatory
X-Ray Tin-ing E>--peri t
Far UV SpectrosooW Exp.
Solar Corona Diagnostic Exp.
Solar Max mission
Ach,. X-Ray Astrophysics Facility
Very Long Baseline Interferometer
Large Deployable Reflector
Shuttle IR Telescope Facility/Sunsynch
Solar Dynamics Observatory
o Earth Science & Applications
LIDAR Facility
Earth Science Research
(includes SAR, IS, LAPHR other)
Ocean Topography Dcperiment
Geopotential Research Mission
Space Plasma Physics
Origin of Plasma in Earth's Neighborhood
o Solar System ~cploration
Mars Geoch n/Climatol Orbiter
lunar Geochan Orbiter
Cornet Rndezvous
Venus Atmosphere Probe
Titan Probe
Mission Duration
('91-1 Yr)
('92-'95)
('91-195)
('97-'98)
('99-2000)
('93-1 Yr)
('94-'95)
('96-'99)
('97-2000)
('91-2000)
('91-'93)
('91-'92)
('93-'94)
('99-2000)
('91-'93)
('93-2000)
('95-'97)
('98-'2000)
('98-2000)
('91 Launch)
('92-1 Yr)
('91-2000)
('91-'94)
('91-1 Yr)
('92-'93)
(92'-95)
('91 launch)
('91 Launch)
('91 Launch)
('94 Launch)
('93 Launch)
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Table A-1 (Continued)
Mission Name Flight Dates
Saturn Probe ('94 Launch)
Main Belt Asteroid Rendezvous (2-197
(' 97 Lunch) launches)
Saturn Orbiter Launch)
Near Earth Asteroid Rendezvous (''993 7 Launch)
Mars Sample Return
o Life Sciences
Health Maintenance Clinical Research
Animal/Plant Vivarium and Lba
Human Research Lab
('91-2000)
('91-2000)
('91-2000)
'
92-2000)
Closed Environmen`.al Life Support Exp. Sys. (
Closed Environrental Life Support Exp. Pallet ('93-'98)
Dedicated Closed Env. Life Support Mzdule ('99-2000)
o Pilot MPS Processes ('93-'95)
Pilot Biological Processes ('94-'96)
Pilot Containerless Processing (194-'96)
Pilot Furnace Processes
o Carr*ranications*
f
(~ 94 Launch)
orm
Experirental Geo. Plat
('93-2000)
Cannon cations Test Lab
PAM-D Class Satellite Deployment
('96(3), '97(5),__
-
, 2000(4))
'98(4), '99(4)
PAM-A Class Satellite Deployment
('96(3), '97(3),
198(3), 199(2), 2000(2))
IUS Class Satellite Deployment
('96(6), '97(6),
'
2000(7))
'98(6), '99(7),
Centaur Class Satellites
('96(1), '97(1),
'98(2), '99(2), 2000(2))
PAM D Class Satellite Servicing at GDD
('99(1))
1)
'99
'
PN -A Class Satellite Servicing at GDO
(
98(1),
(
2000(2))
IUS Class Satellite Servicing at GBD
,96(('96(1),2)97(100(3))
'
Centaur Class Satellite Serv. at GDO
97(2),
`99(1)),'99(1)),2
Ecchange Reconfigured Satellite
('95(2), '96(2), '97(3),
2000(3))
'
'
Spares On-orbit
99(3),
98(3),
* Geosynchranous launches from 1991-1995 are listed in the STS model section.
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Table A-1 (Continued)
Mission.Name--
Flight Dates
evelopnent)
o Materials Processing (Commercial
191-2000)
al
Materials Processing in Space
(
Materials Processing in Space Lab #2
('94-2000)
Electrophoretic Separation Production
(191-2000)
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 (Ccpmercial)
6
)
7
'
Remote Sensing Test/Develop. Facility
mo.
-
(
9
Stereo Mu) ti-Linear Array
('91-2000)
Stereo SAR/MLA/CZCS Instr-lTents
('99-2000)
o Technology Development Missions
Materials Performance Technology
('91-2000)
Materials Processing Technology
('91-'94)
'
Deploylient/Assembly /flonstruction
94)
('92
'
Structural Dynamics
94)
('92-
Design Verification Technology
(' 92-18rre. )
'
Waste Heat Rejection Technology
96)
('95-
'
Large Solar Concentrator Technology
97)
('96-
'
laser Per Transmission/Conversion
98)
('97-
'
93)
('92-
Attitude Control Technology
('92-'93)
Figure Control Technology
Telepresence and EVA Technology
('93-'94)
'
Interactive Human Factors
94)
('93-
'
Advanced Control Device Technology
99-lyr)
('94-lyr &
'
92)
('91-
Satellite Servicing-Technology
(191-193)
o7v Servicing Technology
('91-'94)
Habitation Technology
nnviro ental Effects Technology
('91-18mo, '96-18no)
'
94)
('91-
Medical Technology
('96-lyr)
power Systen- Technology Experiments
On-Board Operations Technology
('92-'97)
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Table A-1 (Continued)
Mission Nacre _ Flight Dates
Planetary Automated Orbit Cps. ('98-'99)
Large Space Antenna Technology ('93-'94)
Earth Observation Instrument Tech. ('92-'96)
Teleeanmunicatiens System Tech. ('96-lyr)
Space Interferometer System Tech. - ('95-lyr)
Fluid Management Technology ('91-'92)
lo'' Thrust Prapul sion (' 94-lyr, ' 97-1yr)
Fluid Dynamics Dcperiments ('94-'95)
cryogenic Physics E>cperiments (195-196)
Space Polymer Chemistry Dcperirnents ('95-'96)
General Relativity Experiments (99-lyr)
I?:issions from STS Yodel
Materials D+-perir t Assembly
EURfl (irropean free flyer)
Materials Processing in Space Processes
Tethered Satellite Systen
OSTA Materials Dcperiments
Radar Research Mission
Intelsat
Telesat
Satool.
Tropical Earth Resources Satellite
Geosynchronous Earth Cbs. Sys.
NOAH TIROS
Advanced Earth Resources Satellite
Sato=
Galaxy Satellite
Direct Broadcast Satellite
A-5
(Sortie missions in
'91, '92, '93, '94, '95,
'96, '97 & '2000)
('91, 193, '96, '99)
(Sortie missions in
'92, '94, '95, '96, '97,
'98, '99, '2000)
(Sortie missions in
'92, '94,'95, '97,
'98, 2000)
(Sortie missions in
'91, '92, '93, '95)
(Sortie in '91)
('91(3), '94(3),
'94(3), '95(2) Launches)
(Canadian - '91 Launch)
(Columbian - '91 Launch)
(Indonesia - '91,
' 93 launches)
('92, '95 launches)
('92, '93, '94, '96,
'98, '99 Launches)
(192, 994, 096, '98,
'99, launches)
(RCA - '92(2), '93(2),
' 94 (3) Launches)
(Hughes - '92, '93, '95
launches)
('92(2), '93(3),
'95(3) Launches)
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APPENDIX B
CAPABILITIES OF SUPPORTING ELEKDM
.The SIG scenarios involve the incorporation of various specific hardware
elements to acxrrplish mission goals. This appendix describes each of these
elements and presents general performance capabilities of the elects. The
supporting elements discussed herein are:
1. Space Transportation Systems (STS)
.2. Power Extension Package (PEP)
3. Teleoperator Maneuvering System (TA1S)
4. Free-Flying Spacecraft
5. Unmanned Space Platforms
6. Spacelab
7. Orbital Transfer Vehicles (Ground and Space-Based, Reusable and
Expendable).
8. MV Servicing Facility
9. Space Station
1. SPACE TRkNSPORTATIOK SYSTII-S (STS)
STS is used as an integral part of each scenario and will be used to
place all elements in la.-earth orbit (LED).
The orbiter on-orbit stay time is limited by the amount of consir- le_s
and their rate of consumption. Power is one of several cor srables that
1 unit -the --STS stay- time. A nominal- ~ level of 18-20 kW, lirrsts the
on-orbit stay tine to 7-10 days depending on the number o#. cryogenic tank
sets installed.
2. M-ER D SI0! 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 power 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
R. with the PEP providing two-axis sun tracking. More than one R"LS position
can be used for any orbiter orientation. This flexibility allows minimal
interference with payload viewing.
PEP operates with the regulated solar per in parallel with the orbiter
fuel cells. When in sunlight, the Orbiter fuel cells are off-loaded to
conserve fuel cell reactants (and nay, indeed, actually be enhanced by
electrolysis).
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3. TIIDDPSRAZOR MWEL ERR SYSTEM (71MS)
There will be two distinctly different 7N1S systems. -7!4S-1 will be
available for all scenarios and will be limited to the capability of deploy-
ing and/or retrieving free-flying spacecraft to/from the proximity of the
--( biter or- to/from the Space Station. ZMSl will not have the capability of
performing payload servicing remotely from the orbiter or Space Station.
7MS-2 will be available for all scenarios. 7MS2 will be a general-pur-
pose, remotely-controlled, free-flying vehicle capable of performing 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,
deuctrous manipulator operation for planned or contingency satellite ser-
vicing satellite viewing and science support as a free-flying subsetellite
operting in the vicinity of the STS or Space Station, resupply, change-out,
etc.
For Scenarios IIa, IIb, II Ic and IV, 714S can be space-based. The T
will receive routine service and repair in orbit. For major repairs or major
refurbishrent the 71,1S will be retrieved and returned to earth by the Orbiter.
%'r en the 7MS is Orbiter-based, it will be returned to earth in the Orbiter
payload bay at the completion of each servicing mission. The T,1S for Scenar-
ios IIIa, IIIb, IIIc and hid will be space based at the Space Station where
it will be harbored, serviced, and maintained.
4. F REE-FLYING SPAC.DCRhrr
- Free-flying -oecraft -include alb--dedicated missiO satellites that
cannot be accommodated in Space Platforms or attached. _ to 0_ Space Station
because of unique orbit location or unique instrument environrT ental re-
quirements. For Scenarios I, IA, and IIA this class of satellites includes
all missions that are not accarmcdated in the orbiter crew area or in the
Spacelab.
5. LAID SPACE P.IATF`'1S
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 nirrt tu astr crams, or a platform
payloads may all be of the sane discipline, e.g., ,
may accommodate a set of multi-disciplinary payloads. The platform design
allows payloads to be removed and replaced with new ones on-orbit when the
mission is omplete or in proved instruments are available.
Significant savings in the design and development costs for multiple
platforms will be realized by utilizing a oarrrrnr, design for all platforms
(high or low inclination). The design will be modular to allow for appro-
priate scaling and omit expansion of the electrical, thermal and other
capabilities of the platforms. initially each platform will provide approxi
B-2
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mately 12 MW of electrical pager and heat rejection capability. The modular
by the addition of more solar
design will allow on-orbit "growth" (e.g., the fut~e.
array panels) if additional resources are required in
6. SPAC LAB/SORTIE
Under international agreement* the European oa,m unity 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 rewnfiguration costs-Of-the-above hardware are the responsibility
of the U.S. Space Program. Sortie missions are those flying in the Spaeelab
module or on a Spacelab Pallet-
7. ORBI ThL TRANSFER VEHICLES (OI'V' S)
a. Ground based Upper Stages (STS~orrpatible)_
The initial STS will make use of a family of upper stages to transport
payloads beyond I.M. Included is a class of expendable solid rockets, the
largest being the IUS, capable of transporting 5,000 pounds from LBO to GD).
base.:,
k-)other ground-based o-IV currently under develop-en foiis ~the go?ro,,u,uts~ases-
Shuttle-deployed, Centaur vehicle. The Centaur's per all its trans-
PC'
fer to GDO for payloads of up to 13,500 pounds. They are and not
vehicles, adaptable to mating either on the ground or in space,
optimized for space based use.
_ b. Reusable; Space-Based OIV's
Scenarios IIa, IIb, IIIc and IV assume the development of a reusable,
space-based OTV for transporting payloads from LED to their final earth-or-
bital destination- These vehicles will be transported to the 1M Space
Station or OW servicing facility by the STS and will be maintained and
serviced at the Space Station.
The reusable space-based OTV has been assured to be a cryogenic, aero-
braked stage with geosy lronous orbit capability equal at least to that of
the Shuttle-based Centauri i.e., 13,500 pounds.
The capability to service the Gm-bas-Ad--payloads -with an c)7v/ThS owbination would awl mould be
cFlv
inception of Space Station/OI'V service facility operation.
of modular space-based design to allow maintenance, servicing and mission
modifications cn--orbit.
8. OIV SERVICING FACILITY
Tfie permanent ON servicing facility will consist of the following
elements:
a. An unpressurized enclosure with the necessary equipment to service, maintain, and protect the ORV from meteoroids and Space debris during servic-
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torac
je. A high level of autanation will be wplcjed
? s s. The crew will repair, maintain and provide
se rvicing and checkout func.'tlon to perform
.
se EVA
backup for the autanated equipment through
rote-
b. A similar unpressurized protective enclosure for servic remote
nanoe and -checkout, will be utilized for 07V payloads. A manipulator system I1 ?tracks will
r~ploy
?Vaa and tmeans he 0-TVf payloads.
O,I~
vent, mate/donate and transfer
c. A pressurized module to provide accO mDdations to support a crew be
approximately four for up to 30 days, plus contingency time, will provided:
d. An unpressurized utility element to provide electrical per (30 )6''
avg) for all facility elects (including propellant reliquefaction). The
attitude control and reboost system will be contained in this module.
e. A central core element' with external viehing ports will house the
OR'V and WS control stations. Air locks and berthing ports will provide
ingress/egress and alloy' Orbiter docking. f f. A logistics module of sufficient voles to houce~te s for Oor'
the crew for the allotted stay time, the waste n r1age-ent ' `
spares.
9. SPACE STATION
The permanent facility in space Mich is manned is termed the "Space
-Station However, the characteristics-and capabilities flf the Space Station
These -characteristics and capabilities
vary with the different ScO
are delineated into two general types of space stations: (a) initial and (b)
growth.
a. Initial
This manned space station will support to nological, c^r rercial, and
scientific research and developrent 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, environm-nt con-
trol, data management, etc.) as well as permanent-mnannerl-presence
in order to conduct research and developTent in technological,
commercial, and scientific disciplines.
o Aovarnrndate attached, unpressurized payload pallets with accurate
pointing and environrental control in addition to pressurized pointing
laboratory modules for research and development pursuits.
satellites to the Space Station by means of
o Retrieve free-flying
~''
the Teleoperator system Imo) for servicing by A
raneuvering ii y orbits
and/or place free-flying satellites into their open
with the 9IS.
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replenish cons~arables, change experiments and/or
? Service, refuel, payloads, and repair failed subsystem of free-flying satellites at
the Space station.
o Store propellants for the 'B'LS, satellite refueling, and Space
_... Station orbit zeintenanOe 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
(O7v) -
The space based, reuseable orbital Transfer Vehicle (OIV) will provide
geosynchronous orbit and beyond. The banned Space Station at which
t to will beoane a transportation mode to serve all user camrLI-
the eess OTV is based
nities. This station will have the capability to:
o Provide structure for OTV docking, servicing, refueling, and
payload crating.
o Coordinate OTV servicing, launch, and retrieval.
o Provide facilities for OW propellant storage and handling.
B-S
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