Horizontal_Launch_-_a_Versatile_Concept
.pdf
Fi gures of Mer i t
Figure of Merit |
Definition |
Measures |
Proxy Parameters |
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Cost of operations |
Average annual |
Average annual costs |
Annual and per-mission System mass; |
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integration and |
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level of communications and navigation |
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maintenance costs after |
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infrastructure required; number and |
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IOC (fixed and variable) |
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complexity of major architecture |
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elements/systems; level of autonomy |
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(for ground and flight operations) of |
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architecture systems; maintainability/ |
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life of architecture systems; level of |
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reusability of architecture systems |
Cost of mission |
Average cost of failure |
failure |
occurring during a |
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mission, including all |
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direct and indirect |
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return-to-flight costs. |
Average cost of mission failure; time to return to flight after mission failure
Number and type of alternate launch systems; level of commonality and modularity between systems; system production costs; recurring cost per flight
Factors quantitatively calculated
Factors qualitatively determined using expert elicitation
A v er sat ile concep t for a ssur ed space access |
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77 |
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Appendix B
APPENDIX B
PAYLOAD MARKET AND COMMERCIAL
VIABILITY ANALYSIS
A realistic payload demand forecast underpins the commercial viability analysis performed in this study. The market forecast was derived by projecting future launch demand forward from the last ten years of satellite launch history. Sources of data included the Union for Concerned Scientists, the NASA National Space Science Data Center (NSSDC), AMSAT, and other indepen- dently verified sources. The demand forecast was calibrated with near-term forecasts published by industry monitoring organizations such as Teal Group, Euroconsult, and the Commercial Space Transportation Advisory Committee (COMSTAC). A Gompertz curve (an S-curve function commonly used for economic applications) was employed as the forecast model. The shape of this curve was determined by solving for the inflection point and growth parameterthat best fit the historical data as well as near-term growth estimates. Market demand was projected for the period of 2010 to 2060. All historical data was normalized to low-Earth orbit equivalent delivered payload in order to represent the total demand to all orbital destinations.
In order to produce meaningful demand predictions across the broad range of vehicle payload capabilities examined, the market forecast was stratified into payload classes (by mass).
To account for the fact that the payload capability of an available launch vehicle would likely influence the design mass of real world payloads, the payload classes were binned according to a span of plus or minus 20 percent from the target payload mass. Thus, multiple forecast curves were produced representing the forecast with error bands of plus or minus 20 percent of payload masses. Competition in the marketplace would prevent a launch vehicle from capturing the entirety of the forecasted demand, so a market capture percentage is applied to the overall demand forecast.
The potential for dual manifesting was accounted for by summing the market forecast at the target payload together with half the market forecast of the payload class that is half the mass of the target payload.
Examples of the binned market demand are shown on page 79 in the growth of market demand over time. In the detailed analysis, payloads were binned at a higher fidelity.
Commercial viability was assessed forall concepts considered in the screening process, as well as for the three point designs. The commercial viability margin was defined as the difference of the breakeven price from the market price, divided by the breakeven price.
Commercial Viability Margin = (Market Price – Breakeven Price) / Breakeven Price
A positive value represented commercial viability, meaning the breakeven price is lower than the market, and the concept could generate profit. A negative value indicated that the market price was lower than the breakeven price, and the concept would not be profitable over the campaign.
78 Horizontal l aunch
Payload Market and Commercial Viabilit y Analysis
Market Demand (number of llaunches)
14 |
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2015 |
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12 |
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2020 |
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10 |
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8 |
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6 |
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4 |
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2 |
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0 |
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5,000, |
10,000, |
15,000, |
20,000, |
25,000, |
30,000, |
35,000, |
40,000, |
LEO Equivalent Payload (lbs)
Global Market Demand for Commercial Launches
A v er sat ile concep t for a ssur ed space access |
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aunch l Horizontal 80
APPENDIX C
STUDY SURVEY
Concept |
Government/ |
Performer |
Last |
Design |
Design |
Technology |
System Description |
Name |
Agency |
|
Year |
Payload (lbs) |
Maturity |
Timeframe |
|
|
|
|
|
|
|
|
|
ABLV-02 |
US/NASA |
Astrox |
2001 |
25,000 lb |
1-Low |
3-Far |
Air breathing launch vehicle with various low speed operating |
|
|
|
|
|
|
|
system engine concepts accelerating vehicle to DMRSJ |
|
|
|
|
|
|
|
takeover at M3+, followed by various methods of transitioning |
|
|
|
|
|
|
|
to rocket propulsion (Hunt , 2001) |
|
|
|
|
|
|
|
|
ABLV-04 (LACE) |
US/NASA |
Langley |
2001 |
25,000 |
1-Low |
3-Far |
Air breathing launch vehicle with various low speed operating |
|
|
Research |
|
|
|
|
system engine concepts accelerating vehicle to DMRSJ |
|
|
Center |
|
|
|
|
takeover at M3+, followed by various methods of transitioning |
|
|
|
|
|
|
|
to rocket propulsion (Hunt , 2001) |
|
|
|
|
|
|
|
|
ABLV-04a (LOX) |
US/NASA |
Langley |
2001 |
25,000 |
1-Low |
3-Far |
Air breathing launch vehicle with various low speed operating |
|
|
Research |
|
|
|
|
system engine concepts accelerating vehicle to DMRSJ |
|
|
Center |
|
|
|
|
takeover at M3+, followed by various methods of transitioning |
|
|
|
|
|
|
|
to rocket propulsion (Hunt , 2001) |
|
|
|
|
|
|
|
|
ABLV-04b (AceTR) |
US/NASA |
Langley |
2001 |
25,000 |
1-Low |
3-Far |
Air breathing launch vehicle with various low speed operating |
|
|
Research |
|
|
|
|
system engine concepts accelerating vehicle to DMRSJ |
|
|
Center |
|
|
|
|
takeover at M3+, followed by various methods of transitioning |
|
|
|
|
|
|
|
to rocket propulsion (Hunt , 2001) |
|
|
|
|
|
|
|
|
ABLV-04c (ABTJ) |
US/NASA |
Langley |
2001 |
25,000 |
1-Low |
3-Far |
Air breathing launch vehicle with various low speed operating |
|
|
Research |
|
|
|
|
system engine concepts accelerating vehicle to DMRSJ |
|
|
Center |
|
|
|
|
takeover at M3+, followed by various methods of transitioning |
|
|
|
|
|
|
|
to rocket propulsion (Hunt , 2001) |
|
|
|
|
|
|
|
|
ABLV-04e (ABTJ) |
US/NASA |
Langley |
2003 |
25,000 |
1-Low |
3-Far |
Air breathing launch vehicle with various low speed operating |
|
|
Research |
|
|
|
|
system engine concepts accelerating vehicle to DMRSJ |
|
|
Center |
|
|
|
|
takeover at M3+, followed by various methods of transitioning |
|
|
|
|
|
|
|
to rocket propulsion (Hunt , 2001) |
|
|
|
|
|
|
|
|
ABLV-05 |
US/NASA |
Pratt and |
2001 |
25,000 |
1-Low |
3-Far |
Air breathing launch vehicle with various low speed operating |
|
|
Whitney |
|
|
|
|
system engine concepts accelerating vehicle to DMRSJ |
|
|
|
|
|
|
|
takeover at M3+, followed by various methods of transitioning |
|
|
|
|
|
|
|
to rocket propulsion (Hunt , 2001) |
|
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|
|
ABLV-06 (RBCC |
US/NASA |
Boeing, |
2001 |
25,000 |
1-Low |
3-Far |
Air breathing launch vehicle with RBCC in Air-Augmented |
Rocketdyne) |
|
Aerojet, |
|
|
|
|
Rocket mode to DMSJ takeover at M2.5+, followed by |
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McKinney |
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transition to rocket propulsion (Moses , 1999) |
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Associates |
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C Appendix
access space ed ssur a for t concep ile sat er v A
Concept |
Government/ |
Performer |
Last |
Design |
Design |
Technology |
System Description |
Name |
Agency |
|
Year |
Payload (lbs) |
Maturity |
Timeframe |
|
|
|
|
|
|
|
|
|
ABLV-07a (RBCC |
US/NASA |
Boeing, |
2001 |
25,000 |
1-Low |
3-Far |
Air breathing launch vehicle with RBCC in Air-Augmented |
Aerojet) |
|
Aerojet, |
|
|
|
|
Rocket mode to DMSJ takeover at M2.5+, followed by |
|
|
McKinney |
|
|
|
|
transition to rocket propulsion (Moses , 1999) |
|
|
Associates |
|
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|
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|
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|
|
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|
|
ABLV-07c (RBCC |
US/NASA |
Boeing, |
2001 |
25,000 lb |
2-Med |
3-Far |
Air breathing launch vehicle with RBCC in air-augmented |
Aerojet) |
|
Aerojet, |
|
|
|
|
rocket mode to DMSJ takeover at M2.5+, followed by transition |
|
|
McKinney |
|
|
|
|
to rocket propulsion (Moses , 1999) |
|
|
Associates |
|
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|
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|
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|
|
ABLV-07c- |
US/NASA |
Boeing, |
2001 |
25,000 |
2-Med |
3-Far |
Air breathing launch vehicle with launch assisst with RBCC |
LaunchAssist (RBCC |
|
Aerojet, |
|
|
|
|
in Air-Augmented Rocket mode to DMSJ takeover at M2.5+, |
Aerojet) |
|
McKinney |
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|
followed by transition to rocket propulsion (Moses , 1999) |
|
|
Associates |
|
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|
|
ABLV-08 (PDE GE) |
US/NASA |
Lockheed |
2001 |
25,000 |
1-Low |
3-Far |
Air breathing launch vehicle with PDE low speed operating |
|
|
|
|
|
|
|
system DMSJ takeover at M3+, followed by transition to rocket |
|
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|
|
|
propulsion (Moses , 1999) |
|
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|
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|
|
|
ABLV-09 (AceTR / |
US/NASA |
Boeing |
2001 |
25,000 |
1-Low |
3-Far |
Air breathing launch vehicle with various low speed operating |
ATSD) |
|
Company |
|
|
|
|
systems engine concepts accelerating vehicle to DMRSJ |
|
|
|
|
|
|
|
takeover at M3+, followed by various methods of transitioning |
|
|
|
|
|
|
|
to rocket propulsion (Moses , 1999) |
|
|
|
|
|
|
|
|
ABLV-10 |
US/NASA |
Boeing |
2001 |
25,000 |
1-Low |
3-Far |
Air breathing launch vehicle with various low speed operating |
|
|
Company |
|
|
|
|
systems engine concepts accelerating vehicle to DMRSJ |
|
|
|
|
|
|
|
takeover at M3+, followed by various methods of transitioning |
|
|
|
|
|
|
|
to rocket propulsion (Moses , 1999) |
|
|
|
|
|
|
|
|
ABLV-GT |
US/NASA |
Aerojet, |
2000 |
25,000 |
1-Low |
3-Far |
ABLV-GT accelerates with aerospike tail rocket and turboramjet |
|
|
Georgia |
|
|
|
|
to Mach 3. From Mach 3-18 the vehicle uses DMSJ and |
|
|
Tech |
|
|
|
|
aerospike rocket. From Mach 18 to orbit, thrust is provided by |
|
|
|
|
|
|
|
the rocket exclusively. (Bradford, 2000) |
|
|
|
|
|
|
|
|
ABLV-VTHL |
US/NASA |
Boeing, |
2000 |
25,000 |
1-Low |
3-Far |
Same as ABLV-07c, except for VTO (configuration assumed |
|
|
Aerojet, |
|
|
|
|
compatible with VTO, not technically correct) - analysis done |
|
|
McKinney |
|
|
|
|
solely as “what if?” trade (Moses, 1999) |
|
|
Associates |
|
|
|
|
|
|
|
|
|
|
|
|
|
Advanced Reusable |
US/NASA |
Langley |
1999 |
2,000 |
1-Low |
3-Far |
Air-launched from An-225 (Moses, 1999) |
Small Launch |
|
Research |
|
|
|
|
|
System |
|
Center |
|
|
|
|
|
|
|
|
|
|
|
|
|
Airbourne |
NA |
Dassault |
2008 |
154 |
1-Low |
1-Near |
Two stage solid/liquid upper stage air-launched from Rafale |
Microlauncher“MLA” |
|
|
|
|
|
|
fighter (Dassault, 2008) |
|
|
|
|
|
|
|
|
vey Sur y d Stu
81
aunch l Horizontal 82
Concept |
Government/ |
Performer |
Last |
Design |
Design |
Technology |
System Description |
Name |
Agency |
|
Year |
Payload (lbs) |
Maturity |
Timeframe |
|
|
|
|
|
|
|
|
|
Air-launched SS-520 |
Japan |
IHI |
NA |
37 |
1-Low |
1-Near |
SS-520 sounding rocket air-dropped from a C-130 (HLS Team, |
|
|
Aerospace |
|
|
|
|
2011) |
|
|
|
|
|
|
|
|
ALS - Boeing |
US/Air Force |
Boeing |
1999 |
7,500 lb |
2-Med |
1-Near |
Modified Boeing 747 carrier aircraft air-launches a three-stage, |
Airlaunch with 747 |
|
Company |
|
|
|
|
winged upper stage. Upperstage is basically an Athena rocket |
(Fuselage) |
|
|
|
|
|
|
with wings. (Boeing, 2000) |
|
|
|
|
|
|
|
|
ALS - Boeing |
US/Air Force |
Boeing |
2000 |
7,500 |
1-Low |
1-Near |
Modified Boeing 747 carrier aircraft air-launches a three-stage, |
AirLaunch with 747 |
|
Company |
|
|
|
|
winged upper stage. Upper stage is basically an Athena rocket |
(Underwing) |
|
|
|
|
|
|
with wings. (Boeing, 2000) |
|
|
|
|
|
|
|
|
ALSV - Air Launched |
US/Air Force |
Boeing |
1981 |
3,000 |
1-Low |
1-Near |
Modified Boeing 747 (attachment hardware, dewar, tail rocket) |
Sortie Vehicle |
|
Company |
|
|
|
|
carries an all-rocket orbiter and cylindrical drop tank to altitude |
|
|
|
|
|
|
|
for air launch. (Day, 2010) |
|
|
|
|
|
|
|
|
ALSV - Air Launched |
US/Air Force |
General |
1981 |
5,000 |
1-Low |
1-Near |
Modified Boeing 747 (new H-tail, attachment hardware) carries |
Sortie Vehicle |
|
Dynamics |
|
|
|
|
an all-rocket orbiter and V-shaped drop tank to altitude for air |
|
|
|
|
|
|
|
launch. (Day, 2010) |
|
|
|
|
|
|
|
|
ALSV - Air Launched |
US/Air Force |
Rockwell |
1981 |
3,000 |
1-Low |
1-Near |
Modified Boeing 747 (new V-tail, attachment hardware) carries |
Sortie Vehicle |
|
International |
|
|
|
|
an all-rocket orbiter and drop tank to altitude for air launch. |
|
|
|
|
|
|
|
(Day, 2010) |
|
|
|
|
|
|
|
|
AMSC - Trans- |
US/Air Force |
Rockwell |
1984 |
10,000 |
1-Low |
2-Mid |
Modified Boeing 747 air-launches reusable orbiter and drop |
Atmospheric |
|
|
|
|
|
|
tanks. Orbiter accelerates to orbit using rocket propulsion. |
Vehicle (747- |
|
|
|
|
|
|
(Sanborn, 1984) |
Launched 1.5 Stage) |
|
|
|
|
|
|
|
|
|
|
|
|
|
|
|
AMSC - Trans- |
US/Air Force |
Rockwell |
1984 |
10,000 |
1-Low |
3-Far |
Ground effect machine (GEM) launch assist is used to |
Atmospheric |
|
|
|
|
|
|
accelerate a reusable delta-winged orbiter to takeoff velocity. |
Vehicle (GEM- |
|
|
|
|
|
|
Orbiter continues to accelerate using rocket thrust. (Sanborn, |
Launched SSTO) |
|
|
|
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|
|
1984) |
|
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|
|
|
|
|
|
ARTS |
IRAD |
SpaceWorks, |
2003 |
40,000 |
1-Low |
3-Far |
Maglev launch assist accelerates vehicle to Mach ~0.8. Dual- |
|
|
Gray |
|
|
|
|
fuel, all-rocket propulsion used during remained of mission. |
|
|
Research |
|
|
|
|
Vehicle is reusable. (Wallace, 2003) |
|
|
|
|
|
|
|
|
Astroliner |
IRAD |
Kelly |
1993 |
10,030 |
1-Low |
2-Mid |
Astroliner towed to altitude by 747. Used LOX/Kerosene rocket |
|
|
Aerospace |
|
|
|
|
engines to accelerate to Mach 6.5 staging point. Released |
|
|
|
|
|
|
|
upper stage. (Sarigul-Klijn, 2001) |
|
|
|
|
|
|
|
|
C Appendix
access space ed ssur a for t concep ile sat er v A
Concept |
Government/ |
Performer |
Last |
Design |
Design |
Technology |
System Description |
Name |
Agency |
|
Year |
Payload (lbs) |
Maturity |
Timeframe |
|
|
|
|
|
|
|
|
|
Athena |
US/NASA |
University |
1994 |
3,773 |
1-Low |
1-Near |
Three stage liquid rocket air-dropped from C-5B carrier aircraft. |
|
|
of Michigan |
|
|
|
|
Rocket carried in C-5B cargo bay. (Booker, 1994) |
|
|
|
|
|
|
|
|
ATS Option 3 SSTO |
US/NASA |
Langley |
1993 |
25,000 lb |
2-Med |
3-Far |
Vehicle takes off under low-speed airbreathing plus rocket |
(AB/R) |
|
Research |
|
|
|
|
mode. Transition to ramjet mode occurs at Mach 3, followed |
|
|
Center |
|
|
|
|
by transition to scramjet mode at Mach 6. Rocket mode |
|
|
|
|
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|
|
accelerates the vehicle from Mach 15 to orbit. (NASA, 1994) |
|
|
|
|
|
|
|
|
ATS Option 3 TSTO |
US/NASA |
Ames |
1994 |
25,000 |
2-Med |
3-Far |
Vehicle takes off under turbo-ramjet thrust. Staging between |
(AB/R) |
|
Research |
|
|
|
|
the booster and orbiter occurs at Mach 5. (NASA, 1994) |
|
|
Center |
|
|
|
|
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|
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|
|
|
|
AVATAR |
India |
DRDO |
2001 |
2,500 |
1-Low |
3-Far |
AVATAR takes off horizontally using turbo-ramjet engines. |
|
|
|
|
|
|
|
Scramjet mode is then used from Mach 4 to 8. During this |
|
|
|
|
|
|
|
phase, air is collected and liquid oxygen is stored. A rocket |
|
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|
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|
|
|
mode is then used to complete the ascent to orbit. (HLS Team, |
|
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|
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|
2011) |
|
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|
|
B-52H Responsive |
US/DARPA |
Orbital |
2004 |
500 |
2-Med |
1-Near |
Three-stage rocket air-launched from B-52. (Frick, 2004) |
Air Launch |
|
Sciences, |
|
|
|
|
|
|
|
Schafer |
|
|
|
|
|
|
|
|
|
|
|
|
|
Bantam-X Argus |
US/NASA |
Georgia |
1999 |
300 |
1-Low |
3-Far |
Ground launch assist system provides 800 ft/s initial velocity. |
|
|
Tech |
|
|
|
|
Vehicle accelerates with supersonic ejector ramjet (SERJ) in |
|
|
|
|
|
|
|
ejector mode, transitions to ramjet mode at Mach 3, transition |
|
|
|
|
|
|
|
from ramjet to rocket primary at Mach 6 and continues to orbit. |
|
|
|
|
|
|
|
(St. Germain, 1999) |
|
|
|
|
|
|
|
|
Bantam-X KLIN |
US/NASA |
Georgia |
1999 |
20,000 |
1-Low |
3-Far |
Ground launch assist system provides 800 ft/s initial velocity. |
Argus |
|
Tech |
|
|
|
|
Deeply cooled turbojet operate together up to Mach 1.5, DCTJ |
|
|
|
|
|
|
|
alone provides thrust to Mach 4, rockets throttled back up |
|
|
|
|
|
|
|
between Mach 4 and 6, final transition to rocket mode at Mach |
|
|
|
|
|
|
|
6 and above (St. Germain, 1999) |
|
|
|
|
|
|
|
|
Bantam-X PDRE |
US/NASA |
Georgia |
1999 |
20,000 |
1-Low |
3-Far |
Ground launch assist system provides 800 ft/s initial velocity. |
Argus |
|
Tech |
|
|
|
|
PDRE provides all thrust until Mach 2, ramjets used from Mach |
|
|
|
|
|
|
|
2 to 6, and then PDREs propel vehicle to orbit (St. Germain, |
|
|
|
|
|
|
|
1999) |
|
|
|
|
|
|
|
|
Bantam-X Stargazer |
US/NASA |
Georgia |
1999 |
300 |
1-Low |
3-Far |
Vehicle accelerates in ejector mode from liftoff to Mach 3, dual- |
|
|
Tech |
|
|
|
|
mode ramjet/scramjets accelerate to Mach 10, transition to |
|
|
|
|
|
|
|
rocket mode from Mach 10 to Mach 14 staging point. Rocket |
|
|
|
|
|
|
|
upper stage continues to orbit. (Olds, 1999b) |
|
|
|
|
|
|
|
|
vey Sur y d Stu
83
aunch l Horizontal 84
Concept |
Government/ |
Performer |
Last |
Design |
Design |
Technology |
System Description |
Name |
Agency |
|
Year |
Payload (lbs) |
Maturity |
Timeframe |
|
|
|
|
|
|
|
|
|
Bantam-X Starsaber |
US/NASA |
Georgia |
2001 |
300 |
1-Low |
2-Mid |
Vehicle accelerates in ejector mode until Mach 3.5, utilizes |
|
|
Tech |
|
|
|
|
ramjet mode from Mach 3.5 to 5.5, and then rocket mode from |
|
|
|
|
|
|
|
Mach 5.5 to staging at Mach 10. Rocket upper stage continues |
|
|
|
|
|
|
|
to orbit (St. Germain, 2001) |
|
|
|
|
|
|
|
|
Beta |
US/NASA |
Boeing |
1991 |
50,000 |
1-Low |
3-Far |
Fully reusable system with combined air-breathing and rocket |
|
|
Company |
|
|
|
|
propulsion on the booster, and rocket propulsion on the |
|
|
|
|
|
|
|
orbiter. Staging at Mach 8. (Nadell, 1992) |
|
|
|
|
|
|
|
|
Beta II |
US/NASA |
LaRC, |
1992 |
17,500 lb |
1-Low |
3-Far |
Fully reusable system with air-breathing booster and rocket |
|
|
Boeing |
|
|
|
|
orbiter. Mach 6.5 staging point. (Nadell, 1992) |
|
|
|
|
|
|
|
|
Black Colt |
US/Air Force |
Martin |
1994 |
1,000 |
2-Med |
2-Mid |
Black Colt takes off under turbojet power, climbs, and |
|
|
Marietta |
|
|
|
|
rendezvous with tanker. Tanker transfers liquid oxygen |
|
|
|
|
|
|
|
enabling Black Colt to accelerate to a Mach 12 staging |
|
|
|
|
|
|
|
condition. From there, Star-48 motor accelerates payload to |
|
|
|
|
|
|
|
orbit. (Zubrin, 1995) |
|
|
|
|
|
|
|
|
Black Horse |
IRAD |
Pioneer |
2000 |
1,000 |
1-Low |
2-Mid |
Black Horse takes off under turbojet power, climbs to altitude, |
|
|
Astronautics |
|
|
|
|
and rendezvous with tanker. Tanker transfers liquid oxygen |
|
|
|
|
|
|
|
enabling Black Horse to accelerate to orbit using a tail- |
|
|
|
|
|
|
|
mounted rocket. (Zubrin, 1995) |
|
|
|
|
|
|
|
|
BladeRunner |
US/Air Force |
SMC |
2004 |
2,000 |
1-Low |
2-Mid |
Bladerunner can be air-dropped from a C-17A at Mach 0.8, 40 |
|
|
|
|
|
|
|
kft. System accelerates to Mach 11 under rocket power. Staging |
|
|
|
|
|
|
|
occurs and upper stage proceeds to orbit. Booster is re-used. |
|
|
|
|
|
|
|
(Hampsten, 2004) |
|
|
|
|
|
|
|
|
Boeing F-15 Global |
IRAD |
Boeing |
2006 |
600 |
2-Med |
1-Near |
Modified F-15 aircraft carries two-stage rocket upper stage on |
Strike Eagle (F-15 |
|
Company |
|
|
|
|
top of fuselage. Staging is supersonic. (Chen , 2006) |
GSE) |
|
|
|
|
|
|
|
|
|
|
|
|
|
|
|
Crossbow |
IRAD |
Teledyne |
2010 |
NA |
1-Low |
2-Mid |
Specialized, all-new carrier aircraft is used to deploy a two- |
|
|
Brown |
|
|
|
|
stage liquid rocket at high gamma. (Sorensen, 2004) |
|
|
|
|
|
|
|
|
Dedalus Air Launch |
France |
CNES, |
NA |
330 |
1-Low |
1-Near |
Air-launch from new carrier aircraft at Mach 0.7. A three-stage |
Concept |
|
ONERA |
|
|
|
|
solid upper stage carries the payload to orbit. (Talbot, 2008) |
|
|
|
|
|
|
|
|
DF-09 RBCC |
US/Air Force |
Boeing |
1998 |
5,000 |
1-Low |
3-Far |
Vehicle uses RBCC propulsion. Staging point is Mach 10. |
|
|
Company |
|
|
|
|
(Scuderi, 1998) |
|
|
|
|
|
|
|
|
DF-09 TBCC |
US/Air Force |
Boeing |
1998 |
5,000 |
1-Low |
3-Far |
TBCC DF-9 takes off under turbo-ramjet thrust and transitions |
|
|
Company |
|
|
|
|
to ramjet-scramjet operation starting at Mach 4. The vehicle |
|
|
|
|
|
|
|
uses a linear rocket system to provide thrust during a pop-up |
|
|
|
|
|
|
|
maneuver. (Scuderi, 1998) |
|
|
|
|
|
|
|
|
C Appendix
access space ed ssur a for t concep ile sat er v A
Concept |
Government/ |
Performer |
Last |
Design |
Design |
Technology |
System Description |
Name |
Agency |
|
Year |
Payload (lbs) |
Maturity |
Timeframe |
|
|
|
|
|
|
|
|
|
DF-10 TBCC |
US/Air Force |
Boeing |
1996 |
10,000 |
2-Med |
2-Mid |
Study produced a quick-reaction, global reach ISR Mach 10 |
|
|
Company |
|
|
|
|
aircraft capable of delivering a 10 klb payload globally and |
|
|
|
|
|
|
|
returning to CONUS (Scuderi, 1998) |
|
|
|
|
|
|
|
|
DRLV |
Israel |
Israel Inst. |
2008 |
165 |
1-Low |
1-Near |
F-15I carrier aircraft deploys 2-stage solid rocket. (HLS Team, |
|
|
Tech. |
|
|
|
|
2011) |
|
|
|
|
|
|
|
|
F-15 Microsatellite |
US/Air Force |
Boeing |
2003 |
440 |
2-Med |
1-Near |
Solid rocket upper stage carried on centerline beneath F-15 |
Launch Vehicle |
|
Company |
|
|
|
|
fighter. (HLS Team, 2011) |
|
|
|
|
|
|
|
|
FALCON Quick |
US/DARPA |
AirLaunch |
2004 |
1,000 lb |
2-Med |
1-Near |
Quick Reach is air-dropped from a C-17 and uses 2 liquid stages |
Reach |
|
LLC |
|
|
|
|
to put its payload in LEO. (AirLaunch, 2007) |
|
|
|
|
|
|
|
|
Frequent Flyer (Dan |
IRAD |
Teledyne |
NA |
1,000 |
1-Low |
2-Mid |
Frequent Flyer is boosted by an expendable rocket first |
DeLong) |
|
Brown |
|
|
|
|
stage. After first stage burnout, a winged-body second stage |
|
|
|
|
|
|
|
proceeds to a second staging point. A rocket upper stage |
|
|
|
|
|
|
|
accelerates the payload to orbit under rocket thrust. (XCOR, |
|
|
|
|
|
|
|
2011) |
|
|
|
|
|
|
|
|
Global Range TAV |
IRAD |
ANSER, |
2009 |
20,000 |
3-High |
1-Near |
All-rocket vehicle derived from RASV database, with detailed |
|
|
McKinney |
|
|
|
|
scaling algorithms. (HLS Team, 2011) |
|
|
Associates |
|
|
|
|
|
|
|
|
|
|
|
|
|
HOTOL |
UK |
British |
1982 |
17,600 |
1-Low |
2-Mid |
HOTOL takes off using a rocket-propelled sled. The vehicle |
|
|
Aerospace |
|
|
|
|
then uses a novel RB545 air/LH2/LOX rocket engine to |
|
|
|
|
|
|
|
accelerate to Mach 5. From Mach 5 to orbit the vehicle uses |
|
|
|
|
|
|
|
pure rocket propulsion. (Sarigul-Klijn, 2001) |
|
|
|
|
|
|
|
|
HOTOL - Interim |
UK |
British |
1991 |
NA |
1-Low |
3-Far |
Air-launched from a Ukrainian An-225 Mriya aircraft. Interim |
with An-225 |
|
Aerospace |
|
|
|
|
HOTOL would separate from the carrier aircraft at subsonic |
|
|
|
|
|
|
|
speeds, and would then pull up for the ascent to orbit. It |
|
|
|
|
|
|
|
would return via a gliding re-entry and landing on gear on a |
|
|
|
|
|
|
|
conventional runway. (Neiland, 1991) |
|
|
|
|
|
|
|
|
HRST Argus |
US/NASA |
Georgia |
1998 |
20,000 |
1-Low |
3-Far |
Argus utilizes Maglifter launch assist to reach 800 ft/s at launch. |
|
|
Tech |
|
|
|
|
Main engines are initially in supercharged ejector mode and |
|
|
|
|
|
|
|
transitions to fan-ramjet mode between Mach 2 and 3. Argus |
|
|
|
|
|
|
|
flies in fan-ramjet/ramjet mode until Mach 6, at which point it |
|
|
|
|
|
|
|
transitions to rocket mode for the final leg to orbit. (Olds, 1998) |
|
|
|
|
|
|
|
|
HRST ATS with MHD |
US/NASA |
Lockheed, |
1998 |
25,000 |
1-Low |
3-Far |
Lockheed HRST concept used the NASA ATS configuration with |
|
|
Aerojet, |
|
|
|
|
a MHD Energy By-Pass engine system to “shift” the Aerojet |
|
|
ANSER, |
|
|
|
|
StrutJet engine performance back up along the Mach axis. |
|
|
McKinney |
|
|
|
|
(HLS Team, 2011) |
|
|
Associates |
|
|
|
|
|
|
|
|
|
|
|
|
|
HRST ERJ / LACE |
US/NASA |
Langley |
1998 |
52,800 |
1-Low |
3-Far |
Vehicle uses LACE Ejector Ramjet (ERJ) RBCC propulsion. (HLS |
SSTO |
|
Research |
|
|
|
|
Team, 2011) |
|
|
Center |
|
|
|
|
|
|
|
|
|
|
|
|
|
vey Sur y d Stu
85
aunch l Horizontal 86
Concept |
Government/ |
Performer |
Last |
Design |
Design |
Technology |
System Description |
Name |
Agency |
|
Year |
Payload (lbs) |
Maturity |
Timeframe |
|
|
|
|
|
|
|
|
|
HRST Hyperion |
US/NASA |
Georgia |
1998 |
20,000 |
1-Low |
3-Far |
Hyperion uses its RBCC engines in ejector mode during |
|
|
Tech |
|
|
|
|
take-off and up to Mach 3. Between Mach 3 and Mach 5.5 |
|
|
|
|
|
|
|
the vehicle uses ramjet mode, and from Mach 5.5 to Mach 10 |
|
|
|
|
|
|
|
scramjet mode is used. Mach 10 to orbit is accomplished using |
|
|
|
|
|
|
|
rocket thrust. (Olds,1999a) |
|
|
|
|
|
|
|
|
HRST Space |
US/NASA |
Space |
1998 |
25,000 |
1-Low |
3-Far |
SSTO all-rocket vehicle with launch assist. Limited definition |
America Concept |
|
America |
|
|
|
|
available. (NASA, 1998) |
|
|
|
|
|
|
|
|
HRST SSTO |
US/NASA |
Rockwell |
1998 |
20,000 lb |
1-Low |
3-Far |
Waverider configuration (length/diameter=5). Uses maglev |
Waverider |
|
|
|
|
|
|
launch assist for take-off and 8 turbojets for low-speed |
|
|
|
|
|
|
|
propulsion. High speed propulsion is RBCC. (NASA, 1998) |
|
|
|
|
|
|
|
|
HSDTV |
India |
DRDO |
2007 |
NA |
1-Low |
3-Far |
Vehicle uses scramjet and rocket propulsion modes. Staging |
|
|
|
|
|
|
|
point is at Mach 6.5. (HLS Team, 2011) |
|
|
|
|
|
|
|
|
HTS-1 Turbines (+ |
US/NASA |
Boeing |
2000 |
25,000 |
1-Low |
3-Far |
Vehicle uses turbines plus tail rockets on the booster, and |
Tail Rocket) / Rocket |
|
Company |
|
|
|
|
rocket propulsion on the upper stage. (HLS Team, 2011) |
|
|
|
|
|
|
|
|
HTS-2 RBCC / Rocket |
US/NASA |
Boeing |
2000 |
25,000 |
1-Low |
3-Far |
Vehicle uses RBCC propulsion on the booster and rockets on |
|
|
Company |
|
|
|
|
the upper stage. (HLS Team, 2011) |
|
|
|
|
|
|
|
|
HTS-3 TBCC: |
US/NASA |
Boeing |
2000 |
25,000 |
1-Low |
3-Far |
Vehicle uses TBCC and tail rockets on the booster and rockets |
Turbines/RJ/SJ (+ |
|
Company |
|
|
|
|
on the upper stage. (HLS Team, 2011) |
Tail Rocket) / Rocket |
|
|
|
|
|
|
|
|
|
|
|
|
|
|
|
HTS-4 ACES/RBCC / |
US/NASA |
Boeing |
2000 |
25,000 |
1-Low |
3-Far |
Vehicles uses RBCC propulsion with ACES on the booster and |
Rocket |
|
Company |
|
|
|
|
rockets on the upper stage. (HLS Team, 2011) |
|
|
|
|
|
|
|
|
HTS-5 Turbines (+ |
US/NASA |
Boeing |
2000 |
25,000 |
1-Low |
3-Far |
Vehicle uses turbines and tail rockets on the booster and RBCC |
Tail Rocket) / RBCC |
|
Company |
|
|
|
|
on the upper stage. (HLS Team, 2011) |
|
|
|
|
|
|
|
|
HTS-6 TBCC: |
US/NASA |
Boeing |
2000 |
25,000 |
1-Low |
3-Far |
Vehicle uses TBCC propulsion on the booster and RBCC on the |
Turbines/RJ/SJ (+ |
|
Company |
|
|
|
|
upper stage. (HLS Team, 2011) |
Tail Rocket) / RBCC |
|
|
|
|
|
|
|
|
|
|
|
|
|
|
|
HTS-7 Turbines (+ |
US/NASA |
Boeing |
2000 |
25,000 |
1-Low |
3-Far |
Vehicle uses turbines and tail rockets on the booster and |
Tail Rocket) w/ 2nd |
|
Company |
|
|
|
|
rockets alone on the upper stage. (HLS Team, 2011) |
stage Rocket |
|
|
|
|
|
|
|
|
|
|
|
|
|
|
|
JSS - RALV-B |
US/NASA |
Langley |
2010 |
20,000 |
2-Med |
3-Far |
TBCC booster stage. (NASA, 2010) |
|
|
Research |
|
|
|
|
|
|
|
Center |
|
|
|
|
|
|
|
|
|
|
|
|
|
LauncherOne |
IRAD |
Scaled |
2010 |
440 |
2-Med |
1-Near |
White Knight 2 carries three-stage upper stage. (Amos, 2009) |
(WK2 + upper stage) |
|
Composites |
|
|
|
|
|
|
|
|
|
|
|
|
|
C Appendix