1 OASIS In-Space Architecture - A Commercialization Analysis OASIS In-Space Architecture - A Commercialization Analysis May 3, 2002 The Boeing Company

PowerPoint PresentationOrbital Aggregation & Space Infrastructure Systems (OASIS) is an in-space architecture concept consisting of highly reusable systems and resources that provide a common infrastructure for enabling a large class of space missions
FY01 RASC studies focused on preliminary design of OASIS elements and analysis of Lunar Gateway and commercial mission scenarios
This study package summarizes results of FY01 OASIS commercialization analyses
OASIS capability and potential commercial markets (traffic model)
Economic viability analysis
*
OASIS performance has been evaluated for commercial satellite applications
OASIS commercial traffic models have been developed based on satellite delivery; considered the “floor”
for potential commercial applications
OASIS Economic Viability
HPM/CTM has commercial potential when used as an orbital transfer stage in conjunction with a
low cost booster to LEO at flight rates greater than 3 per year per HPM/CTM
OASIS commercial viability is highly sensitive to infrastructure costs, mission rates and Earth-to-LEO
launch costs
*
Earth Neighborhood commercial and DoD
space missions in the +2015 timeframe
Determine key needs for projected commercial/DoD missions
that OASIS may support (e.g., deployment, refueling/servicing,
retrieval/disposal)
Quantify levels of potential commercial utilization and develop ROM estimates for economic impacts
Study Drivers
ETO transportation costs (trades vs. non-OASIS architectures, cost of resupply propellant)
Assumptions
A low cost Earth-to-LEO transportation capability is required
Highly reliable RLV or ELV for sensitive cargo
Lower cost LEO delivery system for propellant resupply
Industry adopts common infrastructure (e.g., attach fittings, refueling ports, plug-and-play avionics)
Goal - Maximize potential commercial opportunities
(i.e., Greatest number of satellites deployed/serviced with minimum number of OASIS elements)
Sun
Synch
GEO
GTO
Molniya
LEO-MEO
Polar
Single and multiple OASIS operations
High and Low Traffic Models
Integrated Commercial, Military & Exploration
ETO estimate for HPM resupply propellant
HPM/CTM life cycle revenue potential
ETO cost targets (satellite delivery and HPM resupply propellant)
HPM/CTM non-recurring start-up cost
Research technology development efforts
OASIS resizing options
Traffic Models
Technology development cost estimates
FY02 Study Products
FY01 Study Products
Commercial
( >5,445 kg)
Commercial launch demand trends:
Consolidation of spacecraft manufacturers/owners
DoD
DoD applications difficult to identify; programs under definition
Trend toward greater value and functionality per satellite unit mass; initial “picosatellite” experiments have been completed
AF Science Advisory Board: distributed constellations of smaller satellites offer better prospects for “global, real-time coverage” and “advantages in scaling, performance, cost, and survivability”
Potential for very large antenna arrays for optical and radio-frequency imaging utilizing advanced structures and materials technologies
Chart1
2001
2001
2001
2001
2002
2002
2002
2002
2003
2003
2003
2003
2004
2004
2004
2004
2005
2005
2005
2005
2006
2006
2006
2006
2007
2007
2007
2007
2008
2008
2008
2008
2009
2009
2009
2009
2010
2010
2010
2010
9
8
18
15
17
10
18
18
26
29
25
19
24
24
28
32
34
33
29
31
30
27
33
30
28
31
29
27
33
32
30
35
34
30
35
33
28
9
6
3
8
7
1
18
13
5
15
14
1
17
14
3
10
8
2
18
14
4
18
16
2
26
20
6
29
26
3
25
21
4
19
18
1
24
20
4
24
20
4
28
23
5
32
27
5
33
27
6
30
24
6
30
23
7
29
22
7
32
24
8
34
26
8
33
25
8
MLV
900
1983.6
ILV
1815
4000.26
HLV
4083
8998.932
XLV
5445
12000.78
input:
02/07/01
Astrium
1360
2997
1360
2997
9
8
18
15
17
10
18
18
26
29
25
19
30
24
31
1
35
0
31
0
32
0
31
0
30
0
28
0
30
0
29
0
30
0
7
2
0
1
4
3
12
2
4
7
3
5
8
6
3
2
3
5
4
12
2
1
13
4
7
16
3
3
26
0
7
17
1
1
16
2
2
17
4
0
1
0
0
0
0
0
0
0
0
0
0
0
0
0
0
0
0
0
0
0
0
0
0
0
0
0
0
0
0
0.7777777778
0.2222222222
0
0.125
0.5
0
0.6666666667
0.1111111111
0
0.4666666667
0.2
0
0.4705882353
0.3529411765
0
0.2
0.3
0
0.2222222222
0.6666666667
0
0.0555555556
0.7222222222
0
0.2692307692
0.6153846154
0
0.1034482759
0.8965517241
0
0.28
0.68
0
0.0526315789
0.8421052632
0
0.0833333333
0.7083333333
0
0.0769230769
0.5769230769
0
0.1481481481
0.3703703704
0.1111111111
0
0.5483870968
0.1612903226
0
0
0
0
0
0
0
0
0
0
0
0
0
0
0
0
0
0
0
0
0
Company/Organization name:
Number of satellites to be launched by year/by mass classification
Launch Mass Classification
> 9000 (> 4090)
* Launch mass classification based on the amount of launch vehicle performance requried
to reach nominal 200 x GEO GTO orbit and lifetime requirements assuming launch at 28°N
** Heavy is defined as greater than any current or existing U.S. launch vehicle
Inputs sht
0
0
0
0
0
0
0
0
0
0
0
0
0
0
0
0
0
0
0
0
0
0
0
0
0
0
0
0
LEO = Low Earth Orbit
MEO = Medium Earth Orbit
ELI = Elliptical Earth Orbit
Ha = Height of Apogee
Hp = Height of Perigee
Commercial/Military parameter summary
Altitude range => 556 to 2,800 km
Except for GPS (20,200 km), New ICO (10,390 km), Rostelesat (10,360 km), 3 elliptical constellations
Inclination range => 45 to 117 degrees
Except for ECCO, ECO-8, and Ellipso (part) all at 0 degrees
Orbit planes => 1 to 8
Data available for 27 constellations for OASIS traffic model analysis
Mission evaluation
Mission Types
GPS
Globalstar
24
2
8
1
48
3
6
12
21
2
12
24
36
3
2
2
6
8
2
7
48
66
48
4
12
10
96
11
48
48
24
32
8
8
NGSO Military Satellite Summary
ref: various web sites
KH-12
3
0
14,107
31,101
37,176
LEO
800
808
432
436
Altitude (km)
Inc (deg)
NGSO results best case
NGSO Analysis BEST CASE Results Summary (assumes 1 degree RA change one way)
Parking Orbit Conditions
Altitude (km)
Inc (deg)
ORBCOMM (i=108)
4.7237021253
deg/day
Differential Right Ascension Summary
-1.1186614993
deg/day
Differential RA from HPM inclination of:
Satellite
51.6
54
90.3
98
Alt
Inc
System
(km)
(deg)
(deg/day)
(deg/day)
(deg/day)
(deg/day)
(deg/day)
Commercial
ORBCOMM 45
4.9918290795
deg/day
Phase Time
Less than 30 days
Differential Right Ascension Analysis
for near ISS constellations
Phase time to align HPM and Satellite right ascensions (days)
HPM block II
-0.0422515833
deg/day
Phase Time
Less than 30 days
For near Polar Constellations
System
Satellite
98
HPM block II
Block II
Block I
HPM block I
Tyulpan
6
6
1
1
Rostelesat
91
7
13
3
SDS
1
1
1
1
15
9
19
4
19
4.13905019
deg/day
5.0575104862
deg/day
Phase Time
System
Satellite
59
HPM block I
Less than 30 days
System
Satellite
90.3
HPM block II
Phase Time
Less than 30 days
Differential RA from
HPM Constellation Allocation
HPM inclination of:
470
97.3
-0.985296681
-0.133365
134.97
1
0.00
0.00
DMSP
830
99
-1.0139862209
-0.104675
171.96
1
0.00
0.00
19
8.30
4.15
< Average
* Phase times greater than 30 days operate propulsively with no phasing required
Mission Count (54,90.3)
Phase Time
Less than 30 days
HPM inclination of:
470
97.3
-0.985296681
0.943045
19.09
1
19.09
9.54
DMSP
830
99
-1.0139862209
0.971735
18.52
1
18.52
9.26
19
16.70
8.35
< Total
Mission Count (51,59)
Phase Time
Less than 30 days
HPM inclination of:
690
68
2.6000897415
1.538960
29.24
1
29.24
14.62
4
22.19
11.09
< Total
Cum count data
30 Day Delay
2
2
2
2
3
3
3
3
4
4
4
4
5
5
5
5
6
6
6
6
7
7
7
7
8
8
8
8
9
9
9
9
10
10
10
10
Near ISS constellations
Near Polar constellations
Cumulative Count of Serviceable Constellations
Cumulative Number of Constellations Serviced vs HPM Plane Count 30 Day Delay for HPM/Satellite Orbit Alignment
3
3
0
0
7
7
1
0
8
8
1
4
8
9
1
4
8
10
2
5
9
11
4
6
12
12
7
7
12
12
9
11
12
12
12
12
2
2
2
2
3
3
3
3
4
4
4
4
5
5
5
5
6
6
6
6
7
7
7
7
8
8
8
8
9
9
9
9
10
10
10
10
7
8
1
4
8
10
2
5
10
11
7
6
11
11
10
6
11
11
10
6
11
11
10
7
12
12
11
8
12
12
11
11
12
12
12
12
HPM constellation location
Missions in service area of each HPM*
32
24
12.2
16.3
34 old value
10.7
11.4
12.2
8.1
12.2
16.3
Total Mission rate (1 per # days)
10.7
7.1
10.7
14.2
Mission
HPM/CTM
23 old value
16.3
10.8
16.3
21.7
Polar
10
8
5
15
2
Polar
10
4.8
2.4
0
Omitted
11.4
7.6
11.4
15.2
GTO
2
10
18
15
13
GTO
2
17.5
12.5
2
8.8
Exploration
4
91
1
91
1
Exploration
4
1.0
1.0
0
Omitted
Total
24
2.6
66
99.0
66
50
Area
Allocation
100
138
100
79
GTO
2
12
15
Exploration
4
91
1
Total
24
3.7
@
2,669,057
3,683,299
2,669,057
2,108,555
1,147,695
< KGS
444,843
613,883
444,843
351,426
191,282
< KGS
@
5,884,263
8,120,284
5,884,263
4,648,568
2,530,233
< LBS
980,711
1,353,381
980,711
774,761
421,706
< LBS
%
%
Market Share
Traffic Model
Multi-satellite*
HPM/CTMs required
16
15
24
16
16
16
16
24.4
26.0
16.3
24.4
16.3
24.4
32.5
17.1
45.5
11.4
17.1
11.4
17.1
22.8
For mid inclination constellations:
15
15
15
15
26.0
17.3
26.0
34.7
Mission
HPM/CTM
45.5
30.3
45.5
60.7
Area
Allocation
Near ISS
24
24
24
24
Polar
10
8
5
15
2
Polar
10
4.6
2.4
0
Omitted
Omitted
16.3
10.8
16.3
21.7
GTO
2
10
18
15
13
GTO
2
17.5
12.5
2
8.8
6.3
11.4
7.6
11.4
15.2
Exploration
4
91
1
91
1
Exploration
4
1.0
1.0
0
Omitted
Omitted
Total
30
2.8
62
92
62
46
Polar
10
11
3
96
131
96
75
Total
26
3.8
@
2,562,295
3,496,465
2,562,295
2,001,793
480,430
427,049
582,744
427,049
333,632
80,072
@
5,648,893
7,708,385
5,648,893
4,413,198
1,059,167
941,482
1,284,731
941,482
735,533
176,528
%
%
"Refined" traffic model
Co-located satellites offset by 2 degree latitude increments for display
Source data: www.lyngsat.com
Deployment
Next generation, follow-on to DARPA Orbital Express (OE) Space Operations Architecture Program
OE demonstration planned for CY2006
OE uses “industry standard” interfaces
400 KM HPM Parking Orbit
Satellite Operational Orbit
(1) ELV launches HPM resupply propellant; HPM/CTM perform rendezvous/dock and refueling operations
(2) RLV launches and deploys one or more satellites to LEO
(3) HPM/CTM perform rendezvous/docking and maneuver to satellite operational orbit
(4) HPM/CTM deploy satellite in operational orbit and return to parking orbit
(5) HPM/CTM complete maneuver to parking orbit
*
Integrated Architecture Elements
Preliminary performance analyses based on manipulation of the
rocket equation
where DV = velocity change, g = gravity constant, Isp = specific impulse, mi = initial mass, mf = final mass
*
Market
Future NGSO constellations will exist in similar orbits as recently envisioned
Launch Vehicle
Delivers payloads to 400 km circular parking orbits at inclination (inc) and
right ascension (RA) of stored OASIS elements closest to final orbit
HPM
A propellant reserve provides 150 mps velocity reserve for maneuvers
(e.g., rendezvous, proximity operations and docking, reboost in storage orbits, etc)
CTM
HPM chemical engine applies DV impulsively at locally optimal orbit locations
Perigee and Apogee (i.e., Hohmann transfers) for altitude variation
Node crossings for inclination changes
Nodal complement locations for right ascension changes
Propellant is available to autonomously pre-position to HPM rendezvous point as necessary
SEP
Not considered in analyses due to mission duration impact and refurbishment costs
Satellite
*
apogee of transfer orbit
* Sequence steps 2 and 3 reversed if
satellite inclination > HPM/CTM inclination
Calculate DV required for delivery and return
Compare DV to HPM/CTM capability
Adjust HPM/CTM inclination and orbit planes
to improve performance
Need 3 constellations, total of 30 HPM/CTMs
(10 in each constellation)
Results
Need 2 constellations, total of 18 HPM/CTMs
Launch windows occur within 30 days
Line of nodes
HPM/CTM and satellite orbits eliminates need
for Right Ascension plane change
But, requires time to align orbit planes
Nodal Regression Rate
*
Planar launch window opportunities within 30 days
MEO satellites (e.g., GPS) are delivered to transfer orbits using “near ISS” HPM/CTMs
Nominal Traffic Model for 18 total HPM/CTMs
Mission evaluation
Mission Types
GPS
Globalstar
24
2
8
1
48
3
6
12
21
2
12
24
36
3
2
2
6
8
2
7
48
66
48
4
12
10
96
11
48
48
24
32
8
8
NGSO Military Satellite Summary
ref: various web sites
KH-12
3
0
14,107
31,101
37,176
LEO
800
808
432
436
Altitude (km)
Inc (deg)
NGSO results best case
NGSO Analysis BEST CASE Results Summary (assumes 1 degree RA change one way)
Parking Orbit Conditions
Altitude (km)
Inc (deg)
ORBCOMM (i=108)
4.7237021253
deg/day
Differential Right Ascension Summary
-1.1186614993
deg/day
Satellite
51.6
54
90.3
98
Alt
Inc
System
(km)
(deg)
(deg/day)
(deg/day)
(deg/day)
(deg/day)
(deg/day)
Commercial
ORBCOMM 45
Delta RA 54, 51.6 deg
4.9918290795
deg/day
Phase Time
Less than 30 days
Differential Right Ascension Analysis
for near ISS constellations
HPM block II
-0.0422515833
deg/day
Phase Time
Less than 30 days
System
Satellite
98
HPM block II
Block II
Block I
HPM block I
Tyulpan
6
6
1
1
Rostelesat
91
7
13
3
SDS
1
1
1
1
15
9
19
4
19
4.13905019
deg/day
5.0575104862
deg/day
Phase Time
System
Satellite
59
HPM block I
Less than 30 days
System
Satellite
90.3
HPM block II
Phase Time
Less than 30 days
HPM inclination of:
470
97.3
-0.985296681
-0.133365
134.97
1
0.00
0.00
DMSP
830
99
-1.0139862209
-0.104675
171.96
1
0.00
0.00
19
8.30
4.15
< Average
Mission Count (54,90.3)
Phase Time
Less than 30 days
HPM inclination of:
470
97.3
-0.985296681
0.943045
19.09
1
19.09
9.54
DMSP
830
99
-1.0139862209
0.971735
18.52
1
18.52
9.26
19
16.70
8.35
< Total
Mission Count (51,59)
Phase Time
Less than 30 days
HPM inclination of:
690
68
2.6000897415
1.538960
29.24
1
29.24
14.62
4
22.19
11.09
< Total
Cum count data
30 Day Delay
2
2
2
2
3
3
3
3
4
4
4
4
5
5
5
5
6
6
6
6
7
7
7
7
8
8
8
8
9
9
9
9
10
10
10
10
3
3
0
0
7
7
1
0
8
8
1
4
8
9
1
4
8
10
2
5
9
11
4
6
12
12
7
7
12
12
9
11
12
12
12
12
2
2
2
2
3
3
3
3
4
4
4
4
5
5
5
5
6
6
6
6
7
7
7
7
8
8
8
8
9
9
9
9
10
10
10
10
7
8
1
4
8
10
2
5
10
11
7
6
11
11
10
6
11
11
10
6
11
11
10
7
12
12
11
8
12
12
11
11
12
12
12
12
HPM constellation location
Missions in service area of each HPM*
32
24
12.2
16.3
34 old value
10.7
11.4
12.2
8.1
12.2
16.3
Total Mission rate (1 per # days)
10.7
7.1
10.7
14.2
Mission
HPM/CTM
23 old value
16.3
10.8
16.3
21.7
Polar
10
8
5
15
2
Polar
10
4.8
2.4
0
Omitted
11.4
7.6
11.4
15.2
GTO
2
10
18
15
13
GTO
2
17.5
12.5
2
8.8
Exploration
4
91
1
91
1
Exploration
4
1.0
1.0
0
Omitted
Total
24
2.6
66
99.0
66
50
Area
Allocation
100
138
100
79
GTO
2
12
15
Exploration
4
91
1
Total
24
3.7
@
2,669,057
3,683,299
2,669,057
2,108,555
1,147,695
< KGS
444,843
613,883
444,843
351,426
191,282
< KGS
@
5,884,263
8,120,284
5,884,263
4,648,568
2,530,233
< LBS
980,711
1,353,381
980,711
774,761
421,706
< LBS
%
%
32
24
12.2 (4/yr)
16.3 (3/yr)
10.7
11.4
Propellant required Blk II
Market Share
Traffic Model
Multi-satellite*
HPM/CTMs required
16
15
24
16
16
16
16
24.4
26.0
16.3
24.4
16.3
24.4
32.5
17.1
45.5
11.4
17.1
11.4
17.1
22.8
For mid inclination constellations:
15
15
15
15
26.0
17.3
26.0
34.7
Mission
HPM/CTM
45.5
30.3
45.5
60.7
Area
Allocation
Near ISS
24
24
24
24
Polar
10
8
5
15
2
Polar
10
4.6
2.4
0
Omitted
Omitted
16.3
10.8
16.3
21.7
GTO
2
10
18
15
13
GTO
2
17.5
12.5
2
8.8
6.3
11.4
7.6
11.4
15.2
Exploration
4
91
1
91
1
Exploration
4
1.0
1.0
0
Omitted
Omitted
Total
30
2.8
62
92
62
46
Polar
10
11
3
96
131
96
75
Total
26
3.8
@
2,562,295
3,496,465
2,562,295
2,001,793
480,430
427,049
582,744
427,049
333,632
80,072
@
5,648,893
7,708,385
5,648,893
4,413,198
1,059,167
941,482
1,284,731
941,482
735,533
176,528
%
%
"Refined" traffic model
“Refined” commercial traffic model based on:
Higher usage rate missions only (> 3 flights per HPM per year)
Single launch site from ETR to eliminate duplication of ground infrastructure (excludes polar servicing)
50% market share (of high traffic model)
Traffic model variation is based on satellite lifetime extremes
Lifetime Estimates
Objective
Provide a preliminary economic viability assessment of HPM/CTM in future commercial satellite deployment/servicing markets as defined by the integrated traffic model
Approach
Compare potential life cycle earnings over range of critical economic factors
Identify economic factors with strong influence on earnings
Determine the economic sensitivity and establish hurdle values for these critical factors
Earning levels necessary for economic viability include allowance for non-recurring start up costs
Start up costs per HPM/CTM include: HPM/CTM procurement (ROM estimate: ~$150 million each), and initial launch, development and deployment of commercial peculiar infrastructure (e.g., HPM propellant processing facilities)
Start up costs per HPM/CTM assumed not to exceed $500 million; actual value varies inversely with fleet size
Industry leverages government investment in infrastructure development
*
Ch
Prop
P/L
R
Definition
their satellite
with full load (~32,000 kg) of
propellant per deployment
HPM/CTM flights per year
LCE = [Ch - (Prop + P/L)]*R*10 year HPM/CTM life
*
-6
-4
-2
0
2
4
6
0
500
1,000
1,500
2,000
Life Cycle Earnings ($ Billions)
-4
-2
0
2
4
6
8
10
0
500
1,000
1,500
2,000
3
15
HPM/CTM
Commercial Viability Requires:
Enough life cycle earnings to:
Cover start-up costs (HPM/CTM procurement/deployment and infrastructure estimated to be as much as $0.5 billion)
Provide desired return on investment
Low propellant delivery cost (< $1,000/kg)
HPM/CTM use rates > 3 flights per year
9
HPM/CTM
Technology development to TRL 6
First unit production of four elements
Assumptions/Groundrules:
Based on Boeing-derived parametric cost models with complexity factors and industry technology development forecasts
Includes industrial development factors
Solar Electric Propulsion Module
(Industry, NASA, DoD)
Futron Corporation. “Trends in Space Commerce” March 2001.
Provides trends for major space industry segments through 2020
Based on survey polls of 700 global aerospace companies
Federal Aviation Administration. “2001 Commercial Space Transportation Projections for
Non-geosynchronous Orbits (NGSO)” May 2001. [referred to as the Comstac Study]
Projects launch demand for commercial space systems through 2010
Based on survey of 90 industry organizations
Center for Strategic and Budgetary Assessments (CSBA). “The Military Use of Space; A Diagnostic Assessment” February 2001.
Assessment of the evolving capabilities of nations and other “actors” to exploit near-Earth space for military purposes over the next 20-25 years.
Based on interviews with key military personnel and web site research
Review of numerous Web sites
For satellite constellation detail
Information on current launch costs
*
“World Space Systems Briefing” , the Teal Group, Fairfax, Va., presented during the IAF 52nd International Astronautical Congress in Toulouse, France, October 2, 2001.
Summary of current satellite market
“Research and Development in CONUS Labs (RaDiCL) Data Base” 1999.
Military laboratory technology initiatives
NASA funded technology activities
Interviews with Boeing personnel
Orbital Express Program (DARPA) – to identify additional military analogs
3rd Generation RLV Enterprise – use of HPM or similar element in overall transportation architecture
Roy A. E., “The Foundations of Astrodynamics”, MacMillan Company, dated 1965
Closed-form delta-velocity calculations
*
OASIS - Pat Troutman, LaRC
HPM - Jeff Antol, LaRC
CTM - Vance Houston, MSFC
SEP - Tim Sarver-Verhey, GRC
CTV - Bill CiriIlo, LaRC
OASIS FY01 Final Report draft, ftp site taurus.larc.nasa.gov
Numerous web sites for specific technology details
NASA Cost Model, NASCOM, Version 96
Databases/Documents/Cost Models
satellitesspares(kg)(lbs)(years)(km)(km)(nmi)(nmi)(deg)
MissionHPMHigh Traffic ModelLow Traffic ModelHPMRefined Traffic Model
AreaAllocationAnnual Rate/HPMAnnual Rate/HPMAllocationAnnual Rate/HPM
NGSO Commercial Satellite Summaryref: Comstac assessment
Systemno. of no. of MassMassLifeOrbitHpHaHpHaPlanes @ Inc
satellitesspares(kg)(lbs)(years)(km)(km)(nmi)(nmi)(deg)
Leo One Worldwide4881924237LEO9509505135138@50
New ICO1022,7446,049LEO10,39010,3905,6065,6062@45
Signal483086796LEO1,5001,5008098094@74
Tyulpan62,5005,512MEO00
GPS2438621,9007.5MEO20,20020,20010,90010,9006@55
Missions in service area of each HPM*3224
Mission rate per HPM/CTM (1 per # weeks) 12.2 (4/yr) 16.3 (3/yr)
Total Mission rate (1 per # days)10.711.4
* Based on multiple satellites serviced per mission
Below 1,815kg
0
10
20
30
40
50
60
70
80
90
100
0
20
40
60
80
100
120
OASIS Performance
Deploy P/ L (all chemical)
Retrieve P/ L (all chemical)
P/L chem out + HPM elec in (hybrid stage)
OASIS System Capability
OASIS Performance
P/L chem out + HPM elec in (hybrid stage)
OASIS System Capability
Required electric V
LaRC
NASCOM
OE
RaDiCL
RASC
Xe
Xenon
Xfer
Transfer
ZBO
Al
Aluminum
AMA
C&DH
CONUS
CTM
DDT&E
DoD
EDD
ELI
Ex
Exploration
FTI
Inc