[특허]Aero-assisted pre-stage for ballistic rockets and aero-assisted flight vehicles

Ustinov, Eugene Alexis

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특허 상세정보

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Aero-assisted pre-stage for ballistic rockets and aero-assisted flight vehicles

특허상세정보
국가/구분	United States(US) Patent 등록
국제특허분류(IPC7판)	B64D-005/00 B64G-001/40 B64G-001/62
미국특허분류(USC)	244/002; 244/158.9; 244/171.4
출원번호	US-0658656 (2010-02-12)
등록번호	US-8403254 (2013-03-26)
발명자 / 주소	Ustinov, Eugene Alexis
출원인 / 주소	Ustinov, Eugene Alexis
인용정보	피인용 횟수 : 2 인용 특허 : 19

초록
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An aero-assisted pre-stage (10) with a commensurably large wing area having a short-burn rocket propulsion system providing sufficient thrust is used to launch a variety of single-stage and multiple-stage space vehicles (20), such as conventional ballistic rockets and prospective spaceplanes, from conventional runways. This method of launch eliminates the need for dedicated ground launch structures and/or dedicated long runways. The vehicle to be launched (20) is mated to this aero-assisted pre-stage (AP) (10), with their flight directions aligned, using a lock-and-release mechanism (30). The resulting stack takes off like a conventional airplane using the propulsion and aerodynamic lift of the AP. After the desired trajectory of the vehicle is achieved and propulsion system of the AP is shut down, the vehicle is separated from the AP, the propulsion system of the vehicle is ignited, and the vehicle continues its ascent. The AP returns back to the surface for reuse or disposal. Thus, a wide variety of conventional airfields can be used for launch of ballistic and aero-assisted flight vehicles, without any payload mass penalties.

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1. An aero-assisted pre-stage for launch of single-stage and multiple-stage space vehicles, comprising: a. an airframe to which a space vehicle is attached to form a stack, said airframe having an aerodynamic shape capable of providing aerodynamic lift sufficient for take-off at subsonic airspeeds and ascent of said stack using propulsion of said pre-stage,b. short-burn rocket propulsion means mounted to said airframe for providing thrust to said stack, said thrust being sufficient for take-off and ascent of said stack to a separation altitude,c. said airframe having a planform suitable for launch and transport of said space vehicle to said separation altitude,d. said airframe having an undercarriage for enabling roll-out of said stack at take-off,e. said airframe having a flight control system for providing flight control of said stack and glide of said airframe after separation, andf. said airframe having a hold-and-release mechanism for holding said vehicle to said airframe and releasing said vehicle as soon as said separation altitude is reached,whereby said aero-assisted pre-stage enables said vehicle to be launched from runways in a horizontal take-off fashion. 2. The aero-assisted pre-stage of claim 1 wherein said airframe has a delta-wing planform. 3. The aero-assisted pre-stage of claim 2 wherein the structure of said airframe has a longitudinal notch to accommodate the thrust vector of said vehicle to be launched, said notch being adjacent the center of gravity of said airframe. 4. The aero-assisted pre-stage of claim 2 wherein said airframe comprises more than one wing to increase the total wing area and reduce take-off airspeed. 5. The aero-assisted pre-stage of claim 1 wherein said undercarriage for providing roll-out is selected from the group consisting of wheels, floats, air cushions, and skids. 6. The aero-assisted pre-stage of claim 1 wherein said hold-and-release mechanism is located on an upper or lower surface of said airframe. 7. The aero-assisted pre-stage of claim 1 wherein said airframe is converted from an airframe of a pre-existing aircraft with necessary modifications for preventing the exhaust plume of the engine of said space vehicle from damaging said pre-stage and to ensure unobstructed release of said space vehicle at the separation point. 8. The aero-assisted pre-stage of claim 1 wherein said airframe has low-power propulsion means selected from the group consisting of engine-driven propellers, jet engines, and rocket engines, for short-distance self-transportation, flight back to launch site, and test flights. 9. The aero-assisted pre-stage of claim 1 wherein said space vehicle is selected from the class comprising ballistic rockets and aero-assisted flight vehicles. 10. An aero-assisted pre-stage for launch of single-stage and multiple-stage space vehicles, comprising: said pre-stage having short-burn rocket propulsion means mounted thereon, said means providing thrust sufficient for take-off and ascent of said pre-stage with a space vehicle to separation altitude,said propulsion means being selected from the class consisting of liquid rocket engines and solid rocket motors,ascent-assisting means to which said space vehicle is attached to form a stack, said ascent-assisting means providing aerodynamic lift sufficient for take-off and ascent of said vehicle using said propulsion means of said pre-stage,said ascent-assisting means having an undercarriage to provide roll-out of said stack at take-off,said ascent-assisting means having a flight control system for providing flight control of said stack and glide of said ascent-assisting means after separation, andsaid ascent-assisting means arranged to hold said space vehicle to said ascent-assisting means and to release said ascent-assisting means as soon as said separation altitude is reached,whereby said ascent-assisting means provides a capability to launch said vehicle from airport runways, with a subsonic take-off airspeed. 11. The aero-assisted pre-stage of claim 10 wherein said ascent-assisting means has a delta-wing planform. 12. The aero-assisted pre-stage of claim 11 wherein said ascent-assisting means has a longitudinal notch to accommodate a thrust vector of said vehicle to be launched, said notch being adjacent the center of gravity of said airframe. 13. The ascent-assisting means of claim 11 wherein said ascent-assisting means comprises more than one wing to increase the total wing area and reduce take-off airspeed. 14. The aero-assisted pre-stage of claim 10 wherein said ascent-assisting means includes roll-out means selected from the group consisting of wheels, floats, air cushions, and skids. 15. The aero-assisted pre-stage of claim 10 wherein said ascent-assisting means includes hold-and-release means on an upper or lower surface of said airframe. 16. The aero-assisted pre-stage of claim 10 wherein said ascent-assisting means has been converted from an airframe of a pre-existing aircraft with modifications for preventing the exhaust plume of the engine of said space vehicle from damaging said pre-stage and to ensure unobstructed release of said space vehicle at the separation point. 17. The aero-assisted pre-stage of claim 10 wherein said ascent-assisting means includes low-power propulsion means selected from the group consisting of engine-driven propellers, jet engines, and rocket engines, whereby said low-power propulsion means can provide short-distance self-transportation, flight back to launch site, and test flights. 18. The aero-assisted pre-stage of claim 10 wherein said ascent-assisting means is arranged to hold a space vehicle selected from the class comprising ballistic rockets and aero-assisted flight vehicles.

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