WO1998030449B1 - Space launch vehicles configured as gliders and towed to launch altitude by conventional aircraft - Google Patents
Space launch vehicles configured as gliders and towed to launch altitude by conventional aircraftInfo
- Publication number
- WO1998030449B1 WO1998030449B1 PCT/US1998/000750 US9800750W WO9830449B1 WO 1998030449 B1 WO1998030449 B1 WO 1998030449B1 US 9800750 W US9800750 W US 9800750W WO 9830449 B1 WO9830449 B1 WO 9830449B1
- Authority
- WO
- WIPO (PCT)
- Prior art keywords
- launch
- vehicle
- launch vehicle
- aircraft
- spacecraft
- Prior art date
Links
- 210000004279 Orbit Anatomy 0.000 claims abstract 8
- 238000003780 insertion Methods 0.000 claims 6
- 230000001808 coupling Effects 0.000 claims 4
- 238000010168 coupling process Methods 0.000 claims 4
- 238000005859 coupling reaction Methods 0.000 claims 4
- 230000001174 ascending Effects 0.000 claims 2
- 230000004048 modification Effects 0.000 abstract 1
- 238000006011 modification reaction Methods 0.000 abstract 1
Abstract
An orbital launch vehicle (1) equipped with aerodynamic lifting surfaces (2) is towed as a glider behind a conventional aircraft (19). The launch vehicle (1) is used to place spacecraft (16) into low earth orbit. The lift from the aerodynamic surfaces (2) enables the launch vehicle (1) to be towed by means of a flexible cable (18) from a conventional runway using existing aircraft (19). As with 'conventional air-launch', this permits spacecraft launch into orbit to originate from any conventional runway consistent with constraints of public safety, thus eliminating the need to build dedicated launch pads at geographic locations from which a full range of orbital inclinations can be reached. The method of towing the launch vehicle (1), utilizing the lift of its wings (2) to fully offset its weight, permits at least an order of magnitude increase in the weight of vehicle which can be launched compared to 'conventional air-launch' methods whereby the launch vehicle (1) is carried on, or within a conventional aircraft (19). This in turn enables an order of magnitude increase in the weight of spacecraft (16) which can benefit from the inherent flexibility and low cost of 'air-launch'. The tow launch method also requires fewer and simpler modifications to a conventional aircraft than do any other current or proposed air-launch methods.
Claims
AMENDED CLAIMS
[received by the International Bureau on 27 July 1998 (27.07.98); original claims 1, 9, 10, 12, 14 and 16 amended; original claim 20 cancelled; new claims 20-48 added; remaining claims unchanged (10 pages)] 1. A towed glider space launch vehicle for deploying a spacecraft, the glider adapted to be towed by conventional aircraft and comprising: aerodynamic lifting surfaces providing lift sufficient to support atmospheric flight of the vehicle for lifting the vehicle to a predetermined launch altitude while being towed by the conventional aircraft; a support for carrying the spacecraft; and a throttleable rocket propulsion system for propelling the vehicle beyond the sensible atmosphere.
2. A towed glider space launch vehicle as recited in claim 1 wherein the aerodynamic lifting surfaces are capable of supporting atmospheric flight of the vehicle at an airspeed equal to the takeoff speed of the tow aircraft.
3. A towed glider space launch vehicle as recited in claim 1 wherein the launch vehicle has a take-off speed that is greater than the take-off speed of the tow aircraft.
4. A towed glider space launch vehicle as recited in claim 1 wherein the aerodynamic lifting surfaces are capable of supporting atmospheric flight of the vehicle at an airspeed less than the takeoff speed of the tow aircraft.
5. A towed glider space launch vehicle as recited in claim 1 wherein the propulsion system propels the vehicle to an altitude from which the vehicle can coast beyond the atmosphere.
6. A towed glider space launch vehicle as recited in claim 1 wherein the propulsion system propels the vehicle to an altitude of about 350,000 feet.
7. A towed glider space launch vehicle as recited in claim 1 wherein the propulsion system propels the vehicle to an altitude beyond the atmosphere.
8. A towed glider space launch vehicle as recited in claim 1 further comprising a second stage propulsion system connected to the spacecraft.
9. A towed glider space launch vehicle for deploying a spacecraft, the glider adapted to be towed by an aircraft and comprising: delta wings for supporting atmospheric flight of the vehicle for lifting the vehicle to a predetermined launch altitude while being towed at subsonic speeds; and a throttleable propulsion system for propelling the glider from the predetermined altitude to an altitude from which the glider can coast beyond the sensible atmosphere.
10. A method for launch of a spacecraft carried by a launch vehicle having aerodynamic lifting surfaces providing lift sufficient to support atmospheric flight of the launch vehicle while being towed, and a propulsion system, the method comprising the steps of: releasably attaching a tow line from a conventional tow aircraft to the launch vehicle; accelerating the tow aircraft to takeoff on a runway; flying the tow aircraft; controlling the launch vehicle for takeoff; flying the tow aircraft to a desired launch location; starting the propulsion system of the launch vehicle; releasing the tow line from the launch vehicle; controlling the launch vehicle for climb to a predetermined altitude and velocity; and releasing the spacecraft carried by the launch vehicle.
11. A method as recited in claim 10 wherein the step of flying the tow aircraft to a desired location comprises the step of flying the tow aircraft at subsonic speeds.
12. A method for launch of a spacecraft carried by a second vehicle having an upper stage propulsion system, the second vehicle being carried by a launch vehicle having aerodynamic lifting surfaces providing lift sufficient to support atmospheric flight of the launch vehicle while being towed, and a propulsion system, the method comprising the steps of: releasably attaching a tow line from a conventional tow aircraft to the launch vehicle; accelerating the tow aircraft to take off on a runway; flying the tow aircraft; controlling the launch vehicle for takeoff; flying the tow aircraft to a desired launch location; starting the propulsion system of the launch vehicle;
-18- releasing the tow line from the launch vehicle; controlling the launch vehicle for climb to a predetermined altitude and velocity; releasing the second vehicle carrying the spacecraft; and operating the upper stage propulsion system for insertion of the spacecraft into orbit.
13. A method as recited in claim 12 wherein the step of flying the tow aircraft to a desired location comprises the step of flying the tow aircraft at subsonic speeds.
14. A method for launch of a spacecraft carried by a launch vehicle having aerodynamic lifting surfaces providing lift sufficient to support atmospheric flight of the launch vehicle while being towed, and a propulsion system, the method comprising the steps of: releasably attaching a tow line from a conventional tow aircraft to the launch vehicle; accelerating the tow aircraft past its rotation speed on a runway; controlling the launch vehicle for takeoff; rotating the tow aircraft for takeoff upon the launch vehicle attaining a suitable altitude; flying the tow aircraft to a desired launch location; starting the propulsion system of the launch vehicle; releasing the tow line from the launch vehicle; controlling the launch vehicle for climb to a predetermined altitude and velocity; and releasing the spacecraft carried by the launch vehicle.
15. A method as recited in claim 14 wherein the step of flying the tow aircraft to a desired location comprises the step of flying the tow aircraft at subsonic speeds.
16. A method for launch of a spacecraft carried by a second vehicle having an upper stage propulsion system, the second vehicle being carried by a launch vehicle having aerodynamic lifting surfaces providing lift sufficient to support atmospheric flight of the launch vehicle while being towed, and a propulsion system, the method comprising the steps of: releasably attaching a tow line from a conventional tow aircraft to the launch vehicle; accelerating the tow aircraft past its rotation speed on a runway; controlling the launch vehicle for takeoff;
ΓÇó19- rotating the tow aircraft for takeoff upon the launch vehicle attaining a suitable altitude; flying the tow aircraft to a desired launch location; starting the propulsion system of the launch vehicle; releasing the tow line from the launch vehicle; controlling the launch vehicle for climb to a predetermined altitude and velocity; releasing the second vehicle carrying the spacecraft; and operating the upper stage propulsion system for insertion of the spacecraft into orbit.
17. A method as recited in claim 16 wherein the step of flying the tow aircraft to a desired location comprises the step of flying the tow aircraft at subsonic speeds.
18. A method for launch of a spacecraft as recited in claims 10, 12, 14, or 16 wherein the step of controlling the launch vehicle for takeoff comprises the step of remotely controlling the launch vehicle for takeoff, and wherein the step of controlling the launch vehicle for climb comprises the step of remotely controlling the launch vehicle for climb.
19. A method for launch of a spacecraft as recited in claims 10, 12, 14 or 16 further comprising the step of increasing the length of the tow line after takeoff of the launch vehicle.
20. A towed glider space launch vehicle as recited in claim 1 wherein the aerodynamic lifting surfaces provide lift sufficient to support atmospheric flight of the vehicle for lifting the vehicle to a predetermined launch altitude while being towed at subsonic speeds.
21. A towed glider space launch vehicle for deploying a spacecraft, the glider adapted to be towed by an aircraft and comprising: delta shaped aerodynamic lifting surfaces for providing lift sufficient to support atmospheric flight of the vehicle for lifting the vehicle to a predetermined launch altitude while being towed; a support for carrying the spacecraft; and a throttleable rocket propulsion system for increasing the velocity of the vehicle.
22. A towed glider space launch vehicle as recited in claim 21 wherein the aerodynamic lifting surfaces provide lift sufficient to support atmospheric flight of the vehicle to a predetermined launch altitude while being towed at subsonic speeds.
-20-
23. A method for launch of a spacecraft carried by a launch vehicle having delta wings for providing lift sufficient to support atmospheric flight of the launch vehicle while being towed, and a propulsion system, the method comprising the steps of: releasably coupling the launch vehicle to tow aircraft; accelerating the tow aircraft to takeoff on a runway; maintaining flight of the tow aircraft; controlling the launch vehicle for takeoff; further ascending the tow aircraft upon takeoff of the launch vehicle; flying the tow aircraft to a desired launch location; starting the propulsion system of the launch vehicle; releasing the launch vehicle from the tow aircraft; controlling the launch vehicle for climb to a predetermined altitude and velocity; and ejecting the spacecraft carried by the launch vehicle.
24. A method as recited in claim 23 wherein the tow aircraft is a conventional aircraft.
25. A method as recited in claim 23 wherein the step of flying the tow aircraft at the desired location comprises the step of flying the tow aircraft subsonic speeds.
26. A method as recited in claim 23 wherein the spacecraft comprises an upper stage propulsion system, the method further comprising the step of operating the upper stage propulsion system for insertion of the spacecraft into orbit.
27. A method for launch of a spacecraft carried by a launch vehicle having delta wings for providing lift sufficient to support atmospheric flight of the launch vehicle while being towed, and a propulsion system, the method comprising the steps of: releasably coupling the launch vehicle to a tow aircraft; accelerating the tow aircraft on a runway; controlling the launch vehicle for takeoff; rotating the tow aircraft for takeoff upon the launch vehicle attaining a suitable altitude; flying the tow aircraft to a desired launch location; starting the propulsion system of the launch vehicle; releasing the launch vehicle from the tow aircraft;
-21 - controlling the launch vehicle for climb to a predetermined altitude and velocity; and ejecting the spacecraft carried by the launch vehicle.
28. A method as recited in claim 27 wherein the tow aircraft is a conventional aircraft.
29. A method as recited in claim 27 wherein the step of flying the tow aircraft at the desired location comprises the step of flying the tow aircraft subsonic speeds.
30. A method as recited in claim 27 wherein the spacecraft comprises an upper stage propulsion system, the method further comprising the step of operating the upper stage propulsion system for insertion of the spacecraft into orbit.
31. A method for launch of a spacecraft carried by a launch vehicle having lifting surfaces for providing lift sufficient to support atmospheric flight of the launch vehicle while being towed by a conventional aircraft, and a propulsion system, the method comprising the steps of: releasably coupling the launch vehicle to a conventional aircraft for being towed by the conventional aircraft; accelerating the conventional aircraft to takeoff on a runway; maintaining flight of the conventional aircraft; controlling the launch vehicle for takeoff; further ascending the conventional aircraft upon takeoff of the launch vehicle; flying the conventional aircraft to a desired launch location; starting the propulsion system of the launch vehicle; releasing the launch vehicle from the conventional aircraft; controlling the launch vehicle for climb to a predetermined altitude and velocity; and ejecting the spacecraft carried by the launch vehicle.
32. A method as recited in claim 31 wherein the step of flying the conventional aircraft at the desired location comprises the step of flying the conventional aircraft subsonic speeds.
33. A method as recited in claim 32 wherein the spacecraft comprises an upper stage propulsion system, the method further comprising the step of operating the upper stage propulsion system for insertion of the spacecraft into orbit.
-22-
34. A method for launch of a spacecraft carried by a launch vehicle having lifting surfaces for providing lift sufficient to support atmospheric flight of the launch vehicle while being towed by a conventional aircraft, and a propulsion system, the method comprising the steps of: releasably coupling the launch vehicle to a conventional tow aircraft for being towed by the conventional aircraft; accelerating the conventional aircraft on a runway; controlling the launch vehicle for takeoff; rotating the conventional aircraft for takeoff upon the launch vehicle attaining a suitable altitude; flying the conventional aircraft to a desired launch location; starting the propulsion system of the launch vehicle; releasing the launch vehicle from the conventional aircraft; controlling the launch vehicle for climb to a predetermined altitude and velocity; and ejecting the spacecraft carried by the launch vehicle.
35. A method as recited in claim 34 wherein the step of flying the conventional aircraft at the desired location comprises the step of flying the conventional aircraft subsonic speeds.
36. A method as recited in claim 35 wherein the spacecraft comprises an upper stage propulsion system, the method further comprising the step of operating the upper stage propulsion system for insertion of the spacecraft into orbit.
37. A towed vehicle space launch system for deploying a spacecraft, the system comprising: a spacecraft; a launch vehicle adapted to be towed by an aircraft and comprising, delta wings for providing lift sufficient to support atmospheric flight of the launch vehicle, a support for carrying the spacecraft, and a throttleable rocket propulsion system for increasing the velocity of the vehicle; and a tow aircraft for towing the launch vehicle to a predetermined launch altitude wherein the tow aircraft provides thrust to the launch vehicle and wherein the delta wings provide at least part of the lift for attaining the predetermined altitude.
-23-
38. A system as recited in claim 37 wherein the delta wings provide all of the lift to the launch vehicle for attaining the predetermined altitude.
39. A system as recited in claim 37 further comprising a second stage propulsion system coupled to the spacecraft.
40. A towed vehicle space launch system for deploying a spacecraft, the system comprising: a spacecraft; a launch vehicle adapted to be towed by a conventional aircraft and comprising, aerodynamic lifting surfaces for providing lift sufficient to support atmospheric flight of the launch vehicle, a support for carrying the spacecraft, and a throttleable rocket propulsion system for increasing the velocity of the vehicle; and a conventional aircraft for towing the launch vehicle to a predetermined launch altitude wherein the conventional aircraft provides thrust to the launch vehicle and wherein the lifting surfaces provide at least part of the lift for attaining the predetermined altitude.
41. A system as recited in claim 40 wherein the lifting surfaces provide all of the lift to the launch vehicle for attaining the predetermined altitude.
42. A system as recited in claim 40 wherein the conventional aircraft tows the launch vehicle at subsonic speeds to the predetermined launch altitude.
43. A system as recited in claim 40 further comprising a second stage propulsion system coupled to the spacecraft.
44. A system as recited in claim 40 wherein the lifting surfaces are delta wings.
45. A towed vehicle space launch system for deploying a spacecraft, the system comprising: a spacecraft; a launch vehicle adapted to be towed by an aircraft and comprising, delta wings for providing lift sufficient to support atmospheric flight of the launch vehicle,
-24- a support for carrying the spacecraft, and a throttleable propulsion system for propelling the vehicle to an altitude from which the vehicle can coast beyond the sensible atmosphere; and a tow aircraft for towing the launch vehicle to a predetermined launch altitude wherein the tow aircraft provides thrust to the launch vehicle and wherein the delta wings provide at least part of the lift for attaining the predetermined altitude.
46. A towed vehicle space launch system for deploying a spacecraft, the system comprising: a spacecraft; a launch vehicle adapted to be towed by a conventional aircraft and comprising, aerodynamic lifting surfaces for providing lift sufficient to support atmospheric flight of the launch vehicle, a support for carrying the spacecraft, and a throttleable propulsion system for propelling the vehicle to an altitude from which the vehicle can coast beyond the sensible atmosphere; and a conventional aircraft for towing the launch vehicle to a predetermined launch altitude wherein the conventional aircraft provides thrust to the launch vehicle and wherein the lifting surfaces provide at least part of the lift for attaining the predetermined altitude.
47. A towed vehicle space launch system for deploying a spacecraft, the system comprising: a spacecraft; a launch vehicle adapted to be towed by an aircraft and comprising, variable sweep wings for providing lifts sufficient to support atmospheric flight of the launch vehicle, a support for carrying the spacecraft, and a throttleable rocket propulsion system for increasing the velocity of the vehicle; and a tow aircraft for towing the launch vehicle to a predetermined launch altitude, wherein the tow aircraft provides only thrust to the launch vehicle and wherein the lifting surfaces provide at least part of the lift for attaining the predetermined altitude.
-25-
48. A towed vehicle space launch system for deploying a spacecraft, the system comprising: a spacecraft; a launch vehicle adapted to be towed by an aircraft and comprising,
X-wings for providing lift sufficient to support atmospheric flight of the launch vehicle, a support for carrying the spacecraft, and a throttleable of a rocket propulsion system for increasing the velocity of the vehicle; and a tow aircraft for towing the launch vehicle to a predetermined launch altitude, wherein the tow aircraft provides thrust to the launch vehicle and wherein the lifting surfaces provide at least part of the lift for attaining the predetermined altitude.
-26-
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| AU64332/98A AU6433298A (en) | 1997-01-13 | 1998-01-13 | Space launch vehicles configured as gliders and towed to launch altitude by conventional aircraft |
Applications Claiming Priority (2)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| US08/782,769 | 1997-01-13 | ||
| US08/782,769 US6029928A (en) | 1994-11-21 | 1997-01-13 | Space launch vehicles configured as gliders and towed to launch altitude by conventional aircraft |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| WO1998030449A1 WO1998030449A1 (en) | 1998-07-16 |
| WO1998030449B1 true WO1998030449B1 (en) | 1998-09-11 |
Family
ID=25127134
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| PCT/US1998/000750 WO1998030449A1 (en) | 1997-01-13 | 1998-01-13 | Space launch vehicles configured as gliders and towed to launch altitude by conventional aircraft |
Country Status (3)
| Country | Link |
|---|---|
| US (1) | US6029928A (en) |
| AU (1) | AU6433298A (en) |
| WO (1) | WO1998030449A1 (en) |
Families Citing this family (36)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US6543715B1 (en) * | 1999-07-29 | 2003-04-08 | Anatoly Stepanovich Karpov | Aerospace system |
| US6394392B1 (en) * | 1999-10-19 | 2002-05-28 | Trimbach Turbine, Ltd. | Aircraft having multiple fuselages |
| US20010018810A1 (en) * | 2000-08-30 | 2001-09-06 | Chafer Charles M. | Spacecraft advertisement method and system |
| WO2002077660A2 (en) | 2001-03-27 | 2002-10-03 | Space Launch Corporation | A system for the delivery and orbital maintenance of micro satellites and small space-based instruments |
| FR2839946B1 (en) | 2002-05-24 | 2004-12-24 | Dassault Aviat | COMPOSITE LOAD LAUNCHING ASSEMBLY IN SPACE |
| US6745979B1 (en) | 2002-10-22 | 2004-06-08 | Zhuo Chen | Spacecraft and aerospace plane having scissors wings |
| US7252270B2 (en) * | 2003-08-05 | 2007-08-07 | Israel Aircraft Industries, Ltd. | System and method for launching a missile from a flying aircraft |
| DE10343627B4 (en) * | 2003-09-20 | 2014-03-06 | Eads Deutschland Gmbh | Closure element for an area of the outer skin of an aircraft |
| US6913224B2 (en) * | 2003-09-29 | 2005-07-05 | Dana R. Johansen | Method and system for accelerating an object |
| JP4111903B2 (en) * | 2003-10-20 | 2008-07-02 | 東海旅客鉄道株式会社 | Flying object launching apparatus and flying object launching method |
| US7523892B2 (en) * | 2005-03-21 | 2009-04-28 | Michael Leon Cook | Centripetal reflex method of space launch |
| US20070120020A1 (en) * | 2005-11-29 | 2007-05-31 | Mei Technologies, Inc. | Small reusable payload delivery vehicle |
| US8534598B2 (en) * | 2006-10-12 | 2013-09-17 | Robert Salkeld | Direct flight far space shuttle |
| FR2907422B1 (en) | 2006-10-20 | 2009-12-18 | Astrium Sas | AIRCRAFT WITH AERODYNAMIC AND SPATIAL FLYWHEEL AND ASSOCIATED STEERING METHOD. |
| US20080223976A1 (en) * | 2007-03-13 | 2008-09-18 | Robert Stephen Turner | Space vehicle launch system |
| US8168929B2 (en) * | 2008-01-15 | 2012-05-01 | Eugene Alexis Ustinov | Non-powered, aero-assisted pre-stage for ballistic rockets and aero-assisted flight vehicles |
| DE102009016769B4 (en) * | 2009-04-07 | 2015-10-29 | Airbus Operations Gmbh | Rumpfbugtor |
| US8366037B2 (en) * | 2009-05-22 | 2013-02-05 | Heliplane, Llc | Towable aerovehicle system with automated tow line release |
| AU2010324768A1 (en) * | 2009-11-25 | 2012-06-14 | Aerovironment, Inc. | Automatic configuration control of a device |
| US8540183B2 (en) * | 2009-12-12 | 2013-09-24 | Heliplane, Llc | Aerovehicle system including plurality of autogyro assemblies |
| US8403254B2 (en) | 2010-02-12 | 2013-03-26 | Eugene Alexis Ustinov | Aero-assisted pre-stage for ballistic rockets and aero-assisted flight vehicles |
| US8646719B2 (en) | 2010-08-23 | 2014-02-11 | Heliplane, Llc | Marine vessel-towable aerovehicle system with automated tow line release |
| US9156564B2 (en) | 2013-01-22 | 2015-10-13 | Exhaustless, Inc. | Airport capacity from takeoff assist |
| US9079671B2 (en) | 2013-01-22 | 2015-07-14 | Exhaustless, Inc. | Aircraft thrust, assembly, and methods |
| US9944410B1 (en) | 2013-03-14 | 2018-04-17 | The United States Of America As Represented By The Administrator Of The National Aeronautics And Space Administration | System and method for air launch from a towed aircraft |
| US9139311B2 (en) | 2013-03-15 | 2015-09-22 | Robert Salkeld | Reusable global launcher |
| US8727264B1 (en) * | 2013-06-11 | 2014-05-20 | Elbert L. Rutan | Dynamic tow maneuver orbital launch technique |
| US8960590B2 (en) | 2013-07-18 | 2015-02-24 | Elbert L. Rutan | Pressure-equalizing cradle for booster rocket mounting |
| US20170129626A1 (en) * | 2014-11-20 | 2017-05-11 | Harlan Donald Bryan | Leo lb-1a satellite launch system |
| CN104828260A (en) * | 2015-02-14 | 2015-08-12 | 邱世军 | Three-stage space carrying system |
| CN106767157B (en) * | 2016-12-15 | 2018-07-06 | 中国航空工业集团公司西安飞机设计研究所 | A kind of transporter rises to formula sky and penetrates carrier rocket method |
| US10106273B2 (en) | 2017-03-16 | 2018-10-23 | John A. Burgener | In-flight transfer of reactant from a towing or carrying airplane to an attached rocket or rocketplane |
| US10384797B2 (en) | 2017-03-16 | 2019-08-20 | John A. Burgener | In-flight transfer of reactant from a towing or carrying airplane to an attached rocket or rocketplane |
| US11014671B2 (en) * | 2017-05-08 | 2021-05-25 | Fenix Space, Inc. | Tow cable system and method of use |
| JP6644247B1 (en) * | 2018-07-20 | 2020-02-12 | 株式会社エアロネクスト | Flying object |
| US11866202B2 (en) | 2021-07-27 | 2024-01-09 | Fenix Space, Inc. | System and method for improved air-launch of a launch vehicle from a towed aircraft |
Family Cites Families (16)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US2402918A (en) * | 1942-05-14 | 1946-06-25 | All American Aviat Inc | Glider launching system |
| US2407634A (en) * | 1943-04-05 | 1946-09-17 | All American Aviat Inc | Shock absorbing aerial towline |
| US2477569A (en) * | 1944-06-14 | 1949-08-02 | John C Beirise | Automatically releasing aircraft towing gear |
| US2649262A (en) * | 1945-10-24 | 1953-08-18 | Delmer S Fahrney | Apparatus for remote control bombing |
| US2774547A (en) * | 1951-04-03 | 1956-12-18 | Flight Refueling Ltd | Reel |
| US2723812A (en) * | 1952-01-08 | 1955-11-15 | Bernhard A Hohmann | Glider pick-up |
| US2823880A (en) * | 1955-03-10 | 1958-02-18 | Honeywell Regulator Co | Aircraft fuel load center of gravity control means |
| US3437285A (en) * | 1966-08-04 | 1969-04-08 | Dario Manfredi | Space vehicle and launching means therefor |
| US3747873A (en) * | 1971-11-19 | 1973-07-24 | Susquehanna Corp | Tow cable assembly |
| US4265416A (en) * | 1978-05-30 | 1981-05-05 | The United States Of America As Represented By The Administrator Of The National Aeronautics And Space Administration | Orbiter/launch system |
| US4235399A (en) * | 1979-04-09 | 1980-11-25 | The Boeing Company | Cargo ramp |
| US4802639A (en) * | 1984-09-28 | 1989-02-07 | The Boeing Company | Horizontal-takeoff transatmospheric launch system |
| US4646994A (en) * | 1985-05-17 | 1987-03-03 | Rca Corporation | Spacecraft support and separation system |
| US4784354A (en) * | 1987-09-28 | 1988-11-15 | Tavano John B | Emergency aircraft fuel system |
| US5255873A (en) * | 1992-10-19 | 1993-10-26 | Nelson Robert L | Flying wing space launch assist stage |
| US5626310A (en) * | 1994-11-21 | 1997-05-06 | Kelly Space & Technology, Inc. | Space launch vehicles configured as gliders and towed to launch altitude by conventional aircraft |
-
1997
- 1997-01-13 US US08/782,769 patent/US6029928A/en not_active Expired - Lifetime
-
1998
- 1998-01-13 WO PCT/US1998/000750 patent/WO1998030449A1/en active Search and Examination
- 1998-01-13 AU AU64332/98A patent/AU6433298A/en not_active Withdrawn
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