Horizontal_Launch_-_a_Versatile_Concept
.pdf
D et ails of the Aero d ynamic and Tr ajec tor y A nal y ses
Trajectory Analysis Data Summary for the Flight Test 1
ltitAltitude (t(thousands ft)feet)
125 |
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Downrange (nmi)( i)
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700 |
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11 |
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Altitudeltit |
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12 |
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600 |
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500 |
(thousands(t |
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100 |
feet)t)f |
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0 200 400 600 800 1,000, 1,200, 1,400, 1,600, Downrange (nmi)( i)
STAGE1 STAGE2 STAGE3 STAGE4
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Relative |
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Time |
Weight |
Altitude |
Velocity |
Mach |
Dynamic |
Gamma |
Alpha |
ID |
Event |
(s) |
(lb) |
(ft) |
(ft/s) |
Number |
Pressure (psf) |
(deg) |
(deg) |
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Aircraft |
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1 |
separation |
0 |
179469 |
25,000 |
711 |
0.7 |
270 |
5.0 |
8.0 |
2 |
Stage 1 ignition |
10 |
179468 |
25,322 |
657 |
0.6 |
228 |
-0.4 |
8.0 |
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Aerosurface |
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3 |
jettison |
50 |
121005 |
47,690 |
3,314 |
3.4 |
2,232 |
19.0 |
2.2 |
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Maximum |
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4 |
dynamic pressure |
53 |
109764 |
50,736 |
3,577 |
3.7 |
2,248 |
18.3 |
2.2 |
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Stage 1 burnout |
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5 |
and separation |
90 |
64215 |
102,540 |
7,715 |
7.8 |
877 |
12.6 |
4.1 |
6 |
Stage 2 ignition |
92 |
53666 |
105,871 |
7,687 |
7.7 |
745 |
12.3 |
4.3 |
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Stage 2 burnout |
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7 |
and separation |
159 |
20561 |
215,168 |
16,106 |
16.1 |
38.0 |
6.7 |
1.8 |
8 |
Stage 3 ignition |
161 |
17691 |
218,903 |
16,098 |
16.2 |
32.6 |
6.6 |
1.6 |
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Stage 3 burnout |
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9 |
and separation |
229 |
9083 |
335,239 |
22,128 |
24.7 |
0.2 |
4.5 |
0.4 |
10 |
Fairing jettison |
236 |
7950 |
347,474 |
22,111 |
24.7 |
0.1 |
4.4 |
0.2 |
11 |
Stage 4 ignition |
462 |
7150 |
593,720 |
21,768 |
24.3 |
0.0 |
1.2 |
-7.5 |
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Stage 4 burnout |
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12 |
and separation |
528 |
5460 |
607,444 |
24,187 |
27.0 |
0.0 |
0.0 |
-6.5 |
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A v er sat ile concep t for a ssur ed space access |
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Appendix H
Flight Test Demonstrator 2
46.6 ft |
11.7 ft |
5.1 ft |
11.2 ft |
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53.4 ft
18.8 ft
26.0 ft
Approximate CG
Schematic used in aerodynamics analysis
CL versus Alpha at Constant Mach Number
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2.5 |
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Mach0..7 |
0..7 |
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2 |
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Mach0..9 |
0..6 |
iftLift tffiCoefficient |
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Mach1..1 |
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1..5 |
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0..4 |
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0..3 |
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0.2 |
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0..5 |
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DragCoefficientffit . |
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0..1 |
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0 |
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2 |
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6 |
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Alphal (deg)( ) |
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Drag Polar at Constant Mach Number
Mach0..7
Mach0..9
Mach1..1
0 |
0..5 |
1 |
1..5 |
2 |
2..5 |
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Liftift Coefficientffi i t |
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L/D versus Alpha at Constant Mach Number |
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CM versus Alpha at Constant Deflection Angle |
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toifttoLiftDrag tioRatio |
10 |
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Mach0..7 |
titMomentPitchingtffiCoefficient |
0..04 |
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0deg |
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-0..03 |
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Mach0..9 |
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0..03 |
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5deg |
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Mach1..1 |
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0..02 |
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10deg |
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0..01 |
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5 |
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0..00 |
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-0..01 |
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2 |
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-0..02 |
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S =159ft22 |
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refref |
ft |
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L =74.6ft22 |
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refref . |
ft |
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2 |
4 |
6 |
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12 |
14 |
16 |
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4 |
6 |
8 |
10 |
12 |
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16 |
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Alphal (deg)( ) |
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Alphal (deg)( ) |
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Aerodynamic results |
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118 Horizontal l aunch
D et ails of the Aero d ynamic and Tr ajec tor y A nal y ses
Trajectory Analysis Data Summary for the Flight Test 2
ltitAltitude (t(thousands ft)feet)
150 |
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Downrange (nmi)( i)
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700 |
Altitudeltit |
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500 |
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(thousands(t |
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100 |
feet)t)f |
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0 |
200 |
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800 1,000, |
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Downrange (nmi)( i)
STAGE1 STAGE2
ID |
Event |
Time |
Weight |
Altitude |
Velocity |
Mach |
Dynamic |
Gamma |
Alpha |
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(s) |
(lb) |
(ft) |
(ft/s) |
Number |
Pressure (psf) |
(deg) |
(deg) |
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1 |
Aircraft separation |
0 |
81,914 |
25,000 |
711 |
0.7 |
270 |
5.0 |
8.0 |
2 |
Stage 1 ignition |
10 |
81,914 |
25,250 |
665 |
0.7 |
233 |
-1.5 |
8.0 |
3 |
Aerosurface jettison |
40 |
68,249 |
37,264 |
1,703 |
1.8 |
970 |
35.1 |
5.1 |
4 |
Maximum dynamic |
44 |
62,673 |
41,662 |
1,902 |
2.0 |
980 |
32.7 |
5.1 |
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pressure |
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5 |
Stage 1 main |
144 |
17,141 |
228,996 |
13,125 |
13.5 |
14.2 |
15.5 |
5.2 |
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engine cut off and |
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separation |
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6 |
Stage 2 ignition |
146 |
13,259 |
235,960 |
13,108 |
13.6 |
10.5 |
15.3 |
5.2 |
7 |
Fairing jettison |
175 |
12,676 |
329,295 |
13,333 |
14.9 |
0.1 |
12.9 |
7.2 |
8 |
Stage 2 main |
612 |
3,980 |
606,306 |
24,189 |
27.0 |
0.0 |
0.0 |
10.8 |
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engine cut off and |
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separation |
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A v er sat ile concep t for a ssur ed space access |
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119 |
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Appendix H
Time:i : 0..0 seconds |
Time:i : 0..5 seconds |
Separation:ti : 0..0 feetf t |
Separation:ti : 0..3 feetf t |
Time:i : 1..5 seconds |
Time:i : 2..5 seconds |
Separation:ti : 18..2 feetf t |
Separation:ti : 56..9 feetf t |
Separation simulation snapshots for a Flight Test Demonstrator
120 Horizontal l aunch
APPENDIX I
GROUND CREW REQUIREMENTS
Surge call-up time and minimum turn around time (TAT) were calculated for the three point designs. Minor variations in the necessary crew sizes were calculated, which can be attributed to factors such as smaller LOX tanks that take less time to fuel or an increased diameter which allows more technicians to work on integration. If staff sizes are assumed to be the same, turn- around times would generally equalize for these vehicles.
The following figures show the results of the operational analysis using current integration and checkout practices for launch vehicles.
Carrier aircraft preparation |
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Full turnaround activities |
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Call-up activities (also in TAT) |
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Stage 1,2,2 alignment |
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Margin |
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and assembly |
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Stage 1,2,2 mate and |
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interfaces |
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Stage 2,3,3 alignment |
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and assembly |
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Stage 2,3,3 mate and |
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interfaces |
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Carrier aircraft fueling |
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Integrate launch vehicle |
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with aircraft |
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Margin (20%) |
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0 |
8 |
16 |
24 |
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32 |
40 |
48 |
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Time Elapsed (hrs) |
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Results of the operational analysis for Point Design 1.
A v er sat ile concep t for a ssur ed space access |
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121 |
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A p p en di x I
Carrier aircraft preparation |
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Full turnaround activities |
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Call-up activities (also in TAT) |
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Stage 1,2,2 alignment |
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Margin |
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and assembly |
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Stage 1,2,2 mate and |
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interfaces |
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Carrier aircraft fueling |
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Integrate launch vehicle |
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with aircraft |
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Liquid Propellant Loading |
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Margin (20%)
0 |
8 |
16 |
24 |
32 |
40 |
48 |
56 |
64 |
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Time Elapsed (hrs) |
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Results of the operational analysis for Point Design 2.
Carrier aircraft preparation |
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Full turnaround activities |
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Stage 1,2,2 alignment |
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Call-up activities (also in TAT) |
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Margin |
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and assembly |
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Stage 1,2,2 mate and |
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interfaces |
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Carrier aircraft fueling |
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Integrate launch vehicle |
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with aircraft |
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Liquid Propellant Loading |
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Margin (20%)
0 |
8 |
16 |
24 |
32 |
40 |
48 |
56 |
64 |
72 |
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Time Elapsed (hrs) |
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Results of the operational analysis for Point Design 3.
122 Horizontal l aunch
Ground Crew Requirements
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A v er sat ile concep t for a ssur ed space access |
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123 |
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124 Horizontal l aunch
TEAM MEMBERS
CoreDavidTeamF. Voracek, Project Manager, NASA
Paul A. Bartolotta, Principal Investigator, NASA
Alan W. Wilhite, Analysis Lead, Georgia Institute of Technology
Paul L. Moses, Technology Lead, NASA
Ramon Chase, Booz Allen Hamilton
Walter C. Engelund, NASA
Lawrence D. Huebner, NASA
Roger A. Lepsch, NASA
Unmeel B. Mehta, NASA
Daniel Tejtel, Air Force Research Laboratory
Randall T. Voland, ACEnT Laboratories LLC
Analysis Team
AnalyScotticalAngsterMechanics Associates
Matt Toniolo
Patrick Chai
Georgia Institute of Technology
Matthew Fischer
McKinLeonMcKinneyAssociates
NASAJeffrey Bowles
Veronica Hawke
Loc Huynh
JamesKless
Kurt J. Kloesel
Syri J. Koelfgen
John Melton
ShishirPandya
Jeffrey S. Robinson
Paul Tartabini
A v er sat ile concep t for a ssur ed space access |
|
|
125 |
|
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Team Members
Analysis Team (continued)
SpaceWoJohn Bradfordks Enterprises, Inc.
Elizabeth Buchen
A.C. Charania
Dominic DePasquale
Kevin Feld
Michael Kelly
John Olds
Brad St. Germain
Jon Wallace
AndrewWillis
Technology Gap Team
AnalyScotticalFaatzMechanics Associates
CharlesSchafer
Michael Seal
Ken Smith
GloyerPaul-TaylorGloyerLaboratories, LLC
NASAJohn G. Martin
SpaceWorksA.J. PiplicaEnterprises, Inc.
Mark Schaffer
Report Team
SpaceWorksMark ElwoodEnterprises, Inc.
Alan Mackey
StrategicBecky BortnickAnalysis,AferganInc.
Greg Byerly
Toni Marechaux
126 Horizontal l aunch