A NASA CAPABILITIES EVALUATION DOCUMENT, JUNE 24, 1983

• Document Type: CREST
• Collection: General CIA Records
• Document Number (FOIA) /ESDN (CREST): CIA-RDP90B01013R000400010004-9
• Release Decision: RIPPUB
• Original Classification: T
• Document Page Count: 35
• Document Creation Date: December 27, 2016
• Document Release Date: July 18, 2013
• Sequence Number: 4
• Publication Date: July 15, 1983
• Content Type: MEMO

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A NASA CAPABILITIES EVALUATION DOCUMENT
dune 24, 1983
Vtiz?
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SIG DOCUMENT
Table of Contents
1.0
2.6
INTRODUCTION
METHODDIAGY
2.1 Mission Model
?age
1-1
2-1
2-1
2.1.1
Mission Model Develcprent
2-1
2.1.2
Mission Categories
2-2
2.1.2.1 Astrophysics
2-2
2.1.2.2 Earth Science And
2-2
Applications
2.1.2.3 Solar System Exploration
2-2
2.1.2.4 Life Sciences
2-2
2.1.2.5 Communication Satellites
2-2
2.1.2.6 Materials Processing
2-2
2.1.2.7 Satellite Servicing
2-2
2.1.2.8 Technology Development
2-2
2.2
Cost Estimating
2-3
2.2.1
DIOT&E Costs
2-3
3.0
SCENARIOS
3-1
3.1
Scenario I
3-3
3.1.1
Description
3-3
3.1.2
Capabilities
3-3
3.1.3
Cost
3-4
3.2
Scenario Ia
3-5
3.2.1
Description
3-5
3.2.2
Capabilities
3-5
3.2.3
Cost
3-5
3.3
Scenario 11
3-6
3.3.1
Description
3-6
3.3.2
Capabilities
3-6
3.3.3
Cost
3-7
3.4
Scenario ha
3-8
3.4.1
Description
3-8
3.4.2
Capabilities
3-8
3.4.3
Cost
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3.5 Scenario 'lb
3.5.1 Description
3.5.2 Capabilities
3.5.3 Cost
3.6 Scenario IIIa
3:6.1 Description
3.6.2 Capabilities
3.6.3 Cost
3.7 Scenario Illb
3.7.1 Description
3.7.2 Capabilities
3.7.3 Cost
3.8 Scenario Inc
3.8.1 Description
3.8.2 Capabilities
3.8.3 Cost
3.9 Scenario IV
? 3.9.1 Description
3.9:2 Capabilities
3.9.3 Cost
4.0 SUMMARY
APPENDIX A: MISSION KYDEL
APPMDIX B: CPPABILITTF.S OF SUPPORITNG ELEIAENTS
11
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3-11
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3-12
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1.0 INFRODUCTION
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 CMS) and progress through
options of varying capabilities 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, CT figure of nerit, 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 CT 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 ofthese additional
launches (at $122 M average for Eastern Test Range or We-stern Test Range
launch) causes the life cycle costs of the scenarios without long duration
mission capability to be very unrealistic.
Therefore, a qualitative evaluation of the capabilityof 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 nission
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.
F011owing the mission analysis study and the architectural options survey,
the costs data for the Design, Development, Test, and Evaluation (DIME) 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 DOTtE 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 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.
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2.0 METHODOLOGY
2.1 vassum MODEL
2.1.1 Mission Nbdel Development
The mission model was developed by merging the "STS Mission M6-del 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 three major areas: Science and Applications, Commercial, and Technology
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 any 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 some cases, the
term refers to (1) a single instrument (e.g., a telescope), or (2) a single
launch of a spacecraft, CT (3) a series of experiments.
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k
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. The long duration is required because the
observation of just one object can require integration of photons over a
period of hours CT days and many objects must be surveyed and compared;
simultaneous observations at several different wavelengths are often required
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 (0TV'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 tatellites require
launch capability to geosynchronous orbit.
2.2.2.6 Materials Processing. Effective development of Naterja).s 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 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 same cases, on-orbit asseMbly and deployment of satel-
lites. Servicing satellites at geosynchronous orbit is also proposed.
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 communication.
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2.2 COST ESTIMATING
The cost estimates used for the Space Station System were derived fram a cost
model developed by NASA. This godel 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 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 element is
factored into the total cost. The cost includes design and development of
such items as structures, thermal control, electrical power, comunications,
data handling, attitude control, and environmental control and life support
subsystems. It also includes the systems test hardware, integration,
assembly, checkout, ground support equipment, and program management cost
estimates. The initial NOM cost includes the cost of the first unit. If
additional elements (second buy's) are required, these elements are procured
at a significantly lower price since the initial units include the design and
development cost.
Examples of second unit cost can be seen by reviewing DDT&E cost for Scenario
II. The cost of the 28.5? Space Platform is $650 M. TheCost for the 90?
Space Platform (a second unit) is $305 NL
Another example of reduction in cost for like elements can be_seen in Scen-
ario Inc. The cost for the first 28.5' Spa-6e Platform is $550 NIL less than
in Scenario II since same development cost is covered by the Space Station
development. The second Space Platform (90?1 for this Scenario is also less
($260 MEL).
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 and
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 SCENARIOS
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 same of the scenarios to evaluate its ability to fulfill the
mission model requirements
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TABLE 3.1
Ta
IIa
lib
IIIa
IIrb
Inc
TV
STS
STS
STS
STS
STS.
STS
STS
STS
STS
Sit
S/L
Sit
S/L
S/L
S/L
Sit
Sit
Sit
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
r/F
F/F .
F/F
F/F
'IMS
TMS
TMS
TMS
Tms
TMS
TMS
TMS
TMS
PEP
SP28.5?
PEP.
SP900
SS28.50
SS28.50
SS28.5?
SS28.5?
SP90?
SBOTV
SP28.5?
PEP
SP90?
SP90?
SP90?
PEP
OTV/SS
SBOTV
cnv @SS
SP 28.5?
OTV/SS
SP 28.5?
SS90?
CfIV @ SS
LEGEND:
STS - SPACE TRANSPORTATION VS
SYSTIN PEP -
S/L SPACELAB - SORTIES SP -
U/S - UPPER STAGES OTV/SS
FF FREE FLYERS SS
PERATOR , NG 'SYSTEM SBOVT -
PU4ER SION PACKAGE (PEP) MPS -
UNMANNED SPACE KATFORM L/S -
OTV SPACE. STATION OTV @ SS -
SPACE STATION
DI De
SPACE BASED ORBITER TRANSFER VEHICLE
MATERIALS PROCESSING IN SPACE
LIFE sm.=
CTV CAPABILITY ADDED TO EXISTING
SPACE STATICN
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3.1 SCENARIO I
3.1.1 Description
Scenario I utilizes the present STS system augmented with_an STS-based
Teleoperator Maneuvering System (DE) 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-40, 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 accommodation is the
Space Station. These missions require long duration, uninterrupted time
on-orbit with extensive 'Tanned interaction. These missions cannot be accam-
=collated by the capabilities of this scenario. A limited amount of research
can be accomplished by STS sortie flights. These limited R&D missions could
provide early precurser equipnent development 3eading to the eventual product
? capability, but the potential of materials processing in space cannot be
fully developed with intermittent missions that cause much lost time and
require the expense of re-integrating and relaunching the instruments for
only a week's experimentation.
The astrophysics missions require long time on-orbit (one to ten years) and
many of these missions also desire nanned involvement for servicing and
adjustment of instruments. The total mission set cannot be acconmodated
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 tofour years of on-orbit obser-
vation time are limited to one CT 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 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 on the STS). The long term
objectives of these missions can only be accurplished 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
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 acconmodation nodes are, satellite
return to the on-orbit servicing facility, or remote servicing at the
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satellite 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.
Communications satellites which require geosynchronous orbit w-ilrbe launched
via the STS with an expendable upper stage (PAM-A, PAM-D, IUS, or
Since the technology development missions in this model were designed
specifically as Space Station missions, most of the objectives cannot be
accomplished in this scenario. However, different versions of many of these
missions could be done on the STS. Additionally, the STS can be used to
enhance the technology required to build the initial Space Station.
The STS can be utilized for the development of some techniques and equipment
for eventual use by the Space Station in fulfilling same of its mission
objectives (e.g., satellite servicing).
In Scenario I, the solar system exploration missions will be accomplished
with expendable upper stages MS CT Centaur) launched fram the STS.
3.1.3 Cost
The following are the cost associated with Scenario I:
DDT&E Cost
STS
Spacelab .
Upper Stages
TMS
*Free Flyers
(Developed)
(Developed)
(Developed)
(26 FF x $200)
Total Cost -
Cost
0
$ 232 NEL
$5200 NEL
$ 54-3-2 MIL
* The Free Flyers cost is for the bus only, not instruments.
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.3.2 SCENARIO IA
3.2.1 Description
This scenario utilizes the present STS system augmented wittr (1) a power
extension package mal which extends the shuttle on-orbit stay time from a
maximum of 7 to 20 days and (2) a STS-based teleoperator maneuvering system
(TMS) 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 fram 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 orbiter 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
DDT&E
STS
Spacelab.
Upper Stages
TMS
-*Free Flyers -
PEP
(Developed)
(Developed)
(Developed)
(27 x $200 To Support
The Scenario)
Total Cost
Cost
0
0
$232 mu,
5400 MIL
150 MIL
$ 25 MIL
$ 5807 MIL
.1,
* The free flyers cost is for the bus only, not instruments.
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.3.3 SCENARIO II
3.3.1 Description
Scenario II utilizes the present STS system augmented with a power ext nsion
package (PEP) which extends the Shuttle on-orbit stay time Iran 7 to a
maximum of 20 days and a STS-based Teleoperator Maneuvering System (T IS) to
enhance capabilities for deployment, retrieval, service, and on-orbit riinten-
ance of free flying satellites. Other elements in the scenario arc free
flying satellites and expendable upper stages (PAM-A, PAM-D, IUS, an- Cen-
taur) that are used to lift payloads from the shuttle orbit to geosynch.:onous
and other high energy orbits.
---The major elements added to this scenario over previous scenarios are
platforms located at 28.50 and 900 inclinations.
3.3.2 Capabilities
In Scenario II, the long duration astrophysics missions are accommodated on
the platforms. They provide indefinite on-orbit stay time; however, there is
a small percentage of time that manned interaction is available. Fan 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 instrirrents are
placed on a common bus, thus saving design, development, and production
costs.
space
The long duration earth science and applications rdssions.arieracccmmodated on
.the- platforms .withthe same ?advantages and restrictionsas for the astro-
physics missions.
The solar system exploration and geosynchronous satellite missions are
launched fram the STS with expendable upper stages as in the previous scen-
arios.
The same limitations identified in Scenario Ia apply to life science missions
in this scenario.
The accommodation 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 nee Flyers that are included in this scenario are those that were
on-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 geosynchronous missions.
3.3.3 Cost
The following are costs associated with this scenario:
DCTSE Cost
STS
Spacelab -
Upper Stages
TMS
*Free Flyers
Platforms
PEP
RMS
(Developed)
(Developed)
(Developed)
(20 x $$200)
28.50
90?
Total Cost
0
0
0
$ 232 ICL
4000 Nal,
650 MIL
305 NIL
150 rim
25 NIL
$5362 mi.,
* The Free Flyprs cost is for the bus only, not instruments.
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-3.4 SCENARIO IIa
3.4.1 Description
Scenario ha utilizes the present space transportation system um augmented
with a power extension package (PEP) which extends the Shuttle on-orbitstay
time. Other elements required in the scenario are (1) free flying satel-
lites for 1p91, (2) expendable upper stages for 1991, and (3) an STS-based
Teleoperator Maneuvering System (TMS).
This scenario contains a space-based DIV capability in 1992. The OTV is
launched from a named OTV servicing station. The TMS 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 nate payloads to OTV's on-orbit.
The on-orbit OTV payload rating capability allows greater flexibility in STS
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 noting to the DIV. 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 DIV provides round-trip
transportation to geosynchronous orbit for the TMS or other servicing equip-
rent.
This station has no capability to provide for attached payloads or laboratory
nodules. The accommodation of missions that do not use the OTV are the same
as in Scenario Ia.
The advantages of the PEP in this scenario aie the same as in ?Cenario Ia.
3.4.3 Cost
DDT&E
STS
Spacelab
Upper Stages
TMS
*Free Flyers
(Developed)
(Developed)
(Developed)
(27 FF x $200 To
Support this Scenario)
HMS
PEP
OW Servicing Station
cav
Total Cost
Cost
0
0.
$ 232 MIL
5400 MIL
25 MIL
150 MIL
6808 MIL
1600 MIL
$14215 MIL
* The Free Flyers cost is for the bus only, not instrumnts.
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3.5 SCENANIO lib
3.5.1 Description
Scenario Ilb utilizes the present space transportation systomJSTS). Other
elements required in the scenario are (1) free flying satellite, (2) expend-
able upper stages (phased out in 1992), and (3) an shuttle-based Ttleoperator
Maneuvering System (TMS).
This scenario adds two unmanned space platform with operational capability
beginning in 1991 and a space-based OTV capability in 1992. The OTV is
launched Iran 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 ha. As in Scenario II the long duration missions are accommodated on
platforms. As in Scenario ha the OTV servicing station provides capability
for servicing and launching of OTV's, on-orbit gating of payloads to OTV's,
assembly of payloads on-orbit, and servicing of satellites at geosynchronous
orbit.
3.5.3 Cost
DDT&E
STS ?
Spacelab
Upper Stages
*Free Flyers
Manned ON
OTV
Platforms
(Developed)
(Developed)
(Developed)
(22 FF x $200)
Servicing Station
28.5c
_90?
Total Cost
Cost
0
0
0
$ 232 MIL
4400 MIL
-6808 MIL
1600 MIL
550 NIL
260 NIL
$13850 NIL
* The free flyers cost is for the bus only, not instruments.
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SOMAMO IIIa
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, PM-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 III rost astrophysics missions are accommodated on the Space
Station at 28.50; 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 rust be accormcdated on
high inclination orbiting free-flyers in this scenario.
The Space Station defined in this scenario has no reusable OW capability,
therefore, the geosynchronous satellites and planetary miSsions will utilize
expendable upper stages as in Scenarios I, Ia, and II.
This scenario accommodates life sciences research. It provides laboratory
research facilities and 'Teets the requirements for extended time on orbit with
manned interaction.
This scenario also fully enables Materials Processing in Space (MPS) respArch
and development. A man-tended laboratory on the Station will be utilized to
develop these MPS capabilities which have the potential to produce both
commercial enterprises and technology advances.
Free flying near 28.5? 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, ccumunications,
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 oarmunications satellites. Technology will also be
developed for science missions including optics assertibly techniques and earth
observation instrument develqpment.
The high energy missions are accomplished by a space-based (IN as described in
Scenario ha.
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The addition of PEP to the SI'S in this scenario does not increase the mission
Capability since the long duration missions are accorrucdated by the Space
Station and space based TMS.
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 incompatible with the Space Station orbit, and those
that have been launched beyond law earth orbit for solar system exploration or
geosynchronous missions.
3.6.3 Cost
DDT&E
STS
Spacelab
Upper Stages
TMS
*Free Flyers
Manned Space
PEP
RMS
(Developed)
(Developed)
(Developed)
(27 FF x $200)
Station at 26.50
Total Cost
Cost
0
0
0
$ 232 VAIL
5400 MIL
Initial 7520 MIL
Growth 4745 MIL
150 MIL
$ 25 MIL
$18072 MIL
* The free flyers cost is for the bus only, not instrumen
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?
3.7 SCENARIO IlIb
3.7.1 Description
Scenario II/b utilizes the present Space Transportation System -(S). Other
elements in the scenario are (1) free-flying satellites and (2) expendable
upper stages (PAM Aq PAM El, IUS, and Centaur) that are used to lift payloads
from shuttle orbit to geosynchronoos 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 fram orbiter based to space-based.
3.7.2 Capabilities
With the capability of the Space Station at 28.5? 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 ccruunication are accorplished.
3.7.3 Cost
DDT&E
STS
Spacelab
Upper Stages
TMS
*Free Flyers
Manned Space
Platform
(Developed)
(Developed)
(Developed)
(22 FF x $200 To
Station at 28.5?
Initial
Growth
90?
Cost
0
0
$ 232 ma,
4400 MIL
7520 Ma,
4745 MIL
550 MTh
Total Cost $17447 kat
* The free flyers cost is for the bus only, not instructions.
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3.8 SCENARIO IIIc
3.8.1 Description
Scenario IIIc uses the present Space Transportation System(STS). Other
elements in the scenario are (1) free flying satellites and (2) expendable
upper stages (PMA, PAM D, IUS, and Centaur) until 1995.
This scenario contains a panned Space Station beginning in 1991 with growth
to support mission requirements. When the station is activated, the TMS will
benoved from shuttle-based to space-based. DIV space-based operations will
commence in 1994.
In addition,-two space platforms, one at 28.50 and one at 900, are added to
this scenario.
. 3.8.2 Capabilities
Scenario IIIc adds a 28.5? platform and space-based DIV to the capabilities
of Scenarios Dia and II/b. The DIV capability of this scenario is function-
ally the same as that of scenarios Ha 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 instruments that are on-orbit at 26.5' will be the same as
those in Scenario Ilia, but telescopes and other instruments that do not
require frequent manned interaction will be placed on the Space Platform at
28.5?. The orbit of the Platform will be compatible withgthat 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 readilyr available manned intervention) and an unmanned
platform (for the benefits of very low distuxbance levels_cat.Ined with the
periodic availability of manned interventionvia 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 accomplished with the OTV, and include satellite servicing at both
low earth and geosynchronous orbit.
The life sciences and Materials Processing in Space accornrdations in for
this Scenario are the same as described in Scenarios IIIa and nib.
The technology development missions accomodate in this scenario will be the
same as those of Ilia and Mb.
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?
3.8.3 Cost
DDT&E
STS
Spacelab
Upper Stages.
TMS
*Free Flyers
Manned Space
OW
Platforms
(Developed)
(Developed)
(Developed)
(20 FF x $200 Nap
Station at 28.5?
Initial
Growth
OTV Ser.
28.5?
90?
TOtal Cost
Cost
0
0
0
$232 MIL
4000 MIL
7520
4745
1400
1600
550
260
* The free flyers cost is for bus only, not instructions.
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3.9 SCENARIO IV
3.9.1 Description
Scenario IV utilizes the present Space Transportation System- (Sm). Other
elements in the scenario are (1) free flying satellites and (2) expendable
upper stages (PAMA, 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
move from orbiter-based to space-based. OTV space-based operations will
commence in 1994 and phase out the use of expendable uFper 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 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
DDT&E
STS
Spacelab.
Upper Stages
TMS
*Free Flyers
Manned Space
Ow
Platforms
Manned Space
(Developed)
(Developed)
(Developed)
(20 FF x $200)
Station at 28,5?
Initial
Growth
OTV Ser.
28.5?
90?
Station at 90?
Total Cost
Cost
$232 MIL
4000 MIL
-7520 NIL
4745 MIL
1400 MIL
1600 MIL -
550 NIL
260 MIL
$5000 MIL
$25307 MIL
*The free flyers cost is for bus only, not instruments.
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4.0 SIVPIARY
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
duYation in space with continuous yenned 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 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 neet
all of the objectives of naterials processing, life sciences, and
the majority of astrophysics missions.
4) The Space Platform scenarios neat the long duration requirements,
but extensive manned interaction required for specific missions is
not provided.
5) Both the Space Station and Space Platform offer an cost avoidance
through the grouping of payloads on a common 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 OW that has the
potential of increase in the STS load factor. This is acomplished
by manifesting more individual payloads per launch, since the
expenaable stages are not required. As such, the Space Station as
a transportation node can offer some 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 development 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.
4-1
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APPENDIX A
vassim MODEL
Table A-1 is a listing of the various missions and the flight-duration.
"
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TABLE A-1 MISSION MODEL
Mission Name
Mission Duration
Missions FYlopt Langley Model
o Astrophysics
Spectra of Conic 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)
Gamma Ray Observatory
('91-'93)
X-Ray Timing Experiment
('91-'92)
Far UV Spectroscopy Eacp.
('93-'94)
Solar Corona Diagnostic Exp.
("99-2000)
Solar Max Mission
('91-'93)
Adv. X-Ray Astrophysics Facility
('93-2000)
Very Long Baseline Interferometer
('95-'97)
Large Deployable Reflector
('98-'2000)
Shuttle IR Telescope Facility/Sunsynch
C98-2004
Solar Dynamics Observatory
('91 Launch)
c) Earth Science & Applications
? LIDAR Facility C92-1 Yr)
Earth Science Research ('91-2000)
(Includes SAR, IS, LAMMR other)
Ocean Topography Eacperiment ('91-'94)
Geopotential Research Mission ('91-1 Yr)
Space Plasma Physics ('92-'93)
Origin of Plasma in Earth's Neighborhood (92 '-95)
o Solar System Exploration
Mars Geochem/Climatol Orbiter ('91 Launch)
Lunar Geochem Orbiter ('91 Launch)
Comet Rendezvous ('91 Launch)
Venus Atnosphere Probe ('94 Launch)
Titan Probe ("93 launch)
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Table A-1 (Continued)
Mission Name
Saturn PrObe
Main Belt Asteroid Rendezvous
Saturn Orbiter
Near Earth Asteroid Rendezvous
Mars Sample Return
c) Life Sciences
Health Maintenance Clinical Research
Animal/Plant Vivarium and Iba
Human Research Lab
Closed Environmental Life Support Exp. Sys.
Closed Environmental Life Support Exp. Pallet
Dedicated Closed Env. Life Support l?blule
o Pilot MPS Processes
Pilot Biological Processes
Pilot Containerless Processing
Pilot Furnace Processes
o Cammanications*
Experimental Geo. Platform
Communications Test Lab
PAM-D Class Satellite Deployment
PAM-A Class Satellite Deployment
IUS Class Satellite Deployment
Centaur Class Satellites
PAM-D Class Satellite Servicing at GED
PAR-A Class Satellite Servicing at GD)
IUS Class Satellite Servicing at GEO
Centaur Class Satellite Sexy, at GEO
EXchange Reconfigured Satellite
Spares On-orbit
Flight Dates
('94 Launch)
(2-'97 Launches)
('93 Launch)
('97 Launch)
('99 Launch)
('91-2000)
('91-2000)
('91-2000)
('92-2000)
(13-'98)
('99-2000)
('93-'95)
('94-'96)
('94-t96)
('94 Launch)
('93-2000)
C96(3), .
18(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))
('96(1), '97(1),
'98(2), '99(2), 2000(2))
('99(1))
(18(1), '99(1)
2000(2))
V96(1), 197(1),
'98(1), '99(2), 2000(3))
('95(1), '96(1), '97(1),
'98(1), '99(1), 2000(2))
(15(2), '96(2), '97(3),
'98(3), '99(3), 2000(3))
* Geosynchronous launches from 1991-1995 are listed in the STS model section.
A - 3
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*. ?
Table A-1 (Continued)
Missicaliarce
Flight Dates
o Materials Processing (Commercial Development)
Materials Processing in Space Lab 41
('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)
.Bioltgical Processes "
('94-2000)
? Merged Technology/Catalyst Prod.
o Earth and Ocean Observations (Commercial)
('93-2000)
Remote Sensing Test/Develop. Facility
('97-6m0.)
Stereo Multi-Linear Array
('91-2000)
Stereo SAR/MLA/CZCS Instnrrents
('99-2000)
o Technology Development Missions
Materials Performance Technology
? ('91-200,0.)
Materials Processing Technology
('91-'94)
- -? -Deployment/Assembly/Construction
('92'94)
Structural Dynamics
('92-'94)
Design Verification Technology
('92-18mo.)
Waste Heat Rejection Technology
('95-'96)
Large Solar Concentrator Technology
('96-'97)
Laser Power Transmission/Conversion
('97-'98)
Attitude Control 2"chnology
('92-'93)
Figure Control Technology
('92-'93)
Teleprese_nce and EVA Technology
('93-'94)
Interactive Human Factors
(' 93- ' 94)
Advanced Control Device Technology
('94-1yr & '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
(' 96-1yr)
On-Board Operations Technology
('92-"97)
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a.
Table A-1 (Continued)
Mission Mare
Planetary Autareted Orbit Ops.
Large Space Antenna Technology
Earth Observation Instrument Tech.
Teleccrnrnunications System Tech.
Space Interferaneter System Tech.
Fluid Management Technology
Iciw Thrust Propulsion
Fluid Dynamics Experiments
Cryogenic Physics Experiments
Space Polymer Chemistry EXperirnents
General Relativity Experiments
? Missions from STS MDdel ?
Materials Experiment Asse-nbly
EURECA (auwean free flyer)
Materials Processing in Space Processes
Tethered Satellite System
OST A Materials Experiments
Radar Research Mission
Intelsat
Telesat
Satool
Tropical Earth Resources Satellite
Geosynchronous Earth Obs. Sys.
NOM TIROS
Advanced Earth Resources Satellite
Satccrn
Galaxy Satellite
Direct Broadcast Satellite
A-5
Flight Dates
('98-'99)
('93-'94)
('92-'96)
('96-1yr)
('95-1yr)
('91-'92)
('94-1yr, '97-1yr)
('94-'95)
(195-'96)
('95-'96)
('99-1yr)
(Sortie missions in
'91, '92, '93, '94, '95,
'96, '97 & '2000)
('91, '93, '96, 199)
(Sortie missions in
'92, '94, '95, '96, '97,
'98, '99,'!,2000)
(Sortie missions in
192, /94, .?95, '97,
? '98 2000)
.."
(Sortie missions in
'91, '92, 193, '95)
(Sortie in '9])
('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)
('92, '94, '96, '98,
'99, Launches)
(RoDoh - '92 (2) , '93 (2) ,
694(3) Launches)
(Hughes - '92, '93, '95
Launches)
V92(2), '93(3),
'95(3) Launches)
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APPENDIX B
CAPABILITIES OF SUPPORTING ELEMENTS
.The SIC scenarios involve the incorporation of various specific hardware
elements to accomplish 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 Neneuvering System CMS)
4. Free-Flying Spacecraft
5. Unmanned Space Platforms
6. Spacelab
7. Orbital Transfer Vehicles (Ground and Space-Based, Reusable and
EXpendab)e).
8. OTV Servicing Facility
9. Space Station
1. SPACE TRANSPORIATICN SYSTEM (STS)
STS is used as an integral part of each scenario and will be used to
place all elements in low-earth orbit (1)0).
The Orbiter on-orbit stay time is limited by the. aunt of consumables
and their rate of consumption. Power is one of several . consumables that
-limit ,-the.---STS-sthy-,tine.? A, naminal-power- level of18-20 kW, limits the
on-orbit stay time to 7710 days depending, on the nuMber o. cryogenic tank
sets installed.
POWER EXTENSION PACKAGE (PEP)
? The PEP is a? 2000-pound solar array kit which provides most of the
required Orbiter/payload electrical power 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
power systaninast 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 MS 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).
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3. ITELEOPERATOR MANEUVERING SYSTEM (TMS)
There will be two distinctly different TMS systems. -TMS-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
?Orbiter ow-to/from the Space Station. TMS1 will not have the capability of
performing payload servicing remotely fram 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 CT Space Station. The system
- iill provide spacecraft placement -services, planned CT contingency payload
retrieval functions, asseMbly/servicing support for large space systems,
dextrous manipulator operation for planned CT 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 ha, lib, IIIc and IV, TMS can be space-based. The TMS
will receive routine service and repair in orbit. For major repairs or major
refurbishnent the TMS will be retrieved and returned to earth by the Orbiter.
tirnen the TMS is Orbiter-based, it will be returned to earth in the Orbiter
payload bay at the carpletion of each servicing mission. The TMS for Scenar-
ios IIIa, IIIb, IIIc and Ind will be space-based at the Space Station where
it will be harbored, serviced, and maintained.
4. FREE-FLYING SPACECRAFT
*- Fre-lying -spececraft -include -all-dedicated-mission satellites that
cannot be accommodated in Space Platforms or attached ...to AL 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 acccruodated in the Orbiter crew area CT in the
Spacelab.
5. UNMANNED SPACE PiAaTCWIMS
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, CT a platform
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 complete CT improved instruments are available.
Significant savings in the design and development costs for multiple
platforms will be realized by utilizing a common design for all platforms
(high or low inclination). The design will be rcdular 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-
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mately 12 kW of electrical power and heat rejection capability. The nodular
design will allow on-orbit "growth" (e.g., by the addition of yore solar
array panels) if additional resources are required in the future.
6. SMCELAB/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 yenned laboratories, i.e.,
short and long nodules. Also included are several three-meter length pallets
and environmentally controlled sUbsystems in an "igloo" unit. All integre-
-? tion-and reconfiguration tosts-of-the?above tkardare are the responsibility
of the U.S. Space Program. Sortie missions are those flying in the Spacelab
nodule CT on a Spacelab pallet.
7. ORBITAL TRANSYEK vEmacLEs (cYw's)
a. Ground-based Upper Stages (STS-Compatible)
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 LEO to GED.
Another ground-based OW currently under develop-rent is the ground-based,
Shuttle-deployed, Centaur vehicle. The Centaur's performance permits trans-
fer to CEO for payloads of up to 13,500 pounds. They are all expenaAhle
vehicles, adaptable to meting either on the ground CT in space, and not
optimized for space-based use.
b.'Reusable,-Space-:BaSed OTV's
Scenarios ha, Iib, IIIc and IV assume the development of a reusable,
space-based CITV for transporting payloads from LEO to their final earth-or-
bital destination. These vehicles will be transported to the LEO Space
Station CT cnv servicing facility by the STS and will be maintained and
serviced at the Space Station.
The reusable space-based OTV 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
GE?)-based-payloads -with an CTV/TMS .combination would be available at the
inception of Space Station/OW service facility operation. The OW would be
of nodular space-based design to allow maintenance, servicing and mission
modifications on-orbit.
8. OW SERVICING FACILITY
? The permanent CTV servicing facility will consist of the following
elements:
a. An unpressurized enclosure with the necessary equiprrent to service,
maintain and protect the cav from neteoroids and space debris during servic-
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ing and storage. A high level of automation will be erployed 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 (RMS) on tracks will provide a means of receipt, deploy-
ment, mate/demate and transfer for both the OTV and the OTV payloads.
C. ApTessurized nodule 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 kW
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.
9. SPACE STATION
The permanent facility in space which is manned is termed the "Space
-Station:" "'However, the 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, commercial, 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,
commercial, and scientific disciplines.
o Acommodate attached, unpressurized payload pellets with accurate
pointing and environmental control in addition to pressurized
laboratory nodules for research and development pursuits.
o Retrieve free-flying satellites to the Space Station by means of
the Teleoperator Maneuvering System (MS) for servicing by EVA
and/or place free-flying satellites into their operational orbits
with the TMS.
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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
_ Station.orbit maintenance at the Space Station. - -
Space
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
CDTV).
The space-based, reuseable Orbital Transfer Vehicle onn will provide
access to geosynchronous orbit and beyond. The manned Space Station at which
the OW is based will become a transportation mode to serve all user cceralu-
nities. This station will have the capability to:
o Provide structure for OTV docking, servicing, refueling, and
payload mating.
o Coordinate OW servicing, launch, and retrieval.
o Provide facilities for ow propellant storage and handling.
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