Method for controlling an aerospace system to put a payload into an orbit
원문보기
IPC분류정보
국가/구분
United States(US) Patent
등록
국제특허분류(IPC7판)
B64G-001/14
B64G-001/40
출원번호
US-0048174
(2002-01-29)
국제출원번호
PCT/RU99/00259
(1999-07-29)
국제공개번호
WO01/08974
(2001-02-08)
발명자
/ 주소
Karpov, Anatoly Stepanovich
Rachuk, Vladimir Sergeevich
Ivanov, Robert Konstantinovich
Monakhov, Jury Vladimirovich
Kovalevsky, Mikhail Markovich
Borisov, Andrei Vladimirovich
출원인 / 주소
Karpov
Anatoly Stepanovich, Rachuk
Vladimir Sergeevich, Ivanov
Robert Konstantinovich
대리인 / 주소
Burns, Doane, Swecker & Mathis, L.L.P.
인용정보
피인용 횟수 :
10인용 특허 :
8
초록▼
Aerospace technology, in particular, methods for orbital injection of payloads (communication satellites, monitoring satellites, etc.) into low and medium earth orbits with the aid of aerospace systems comprising a carrier aircraft (CA) and a launch vehicle (LV) with a payload (PL). In the present m
Aerospace technology, in particular, methods for orbital injection of payloads (communication satellites, monitoring satellites, etc.) into low and medium earth orbits with the aid of aerospace systems comprising a carrier aircraft (CA) and a launch vehicle (LV) with a payload (PL). In the present method, after the CA 1 takeoff from the base aerodrome, its flight in the maximum cruising speed mode to the LV 2 launch area, pitchdown 7 of the CA 1 is effected to gain the maximum permissible horizontal flight speed, and at the moment that speed is attained, CA 1 pitchup 8 with the maximum allowable angle of attack is executed, culminating in transition to an angle of attack with a near-zero g-load (zero-gravity condition), with the pitchup parameters chosen so that at the LV 2 with PL 3 point of separation from the CA 1, the CA 1 has attained a speed VD,flight altitude HDand a trajectory pitch angle Odensuring a maximum PL 3 and a near-zero normal g-load 9. Separation of the LV 2 from the CA 1 is executed, imparting the LV 2 with a CA 1 related speed assuring that the LV 2 lags behind the CA 1 at a safe distance 10, then the LV 2 sustainers are fired, and, either prior to the sustainers' ignition, or after the ignition (by sustainers), the launch vehicle with the PL 3 is turned into a position differing form the vertical by an angle of 10-30 ° in the vertical plane in the launch direction 11. At the LV 2-PL 3 separation point 22, the CA 1 position is stabilized in an inertial coordinate system. The present invention makes it possible to safely, efficiently and with maximum payload capacity, place payloads into designated orbits and deliver payloads to given terrestrial and oceanic areas.
대표청구항▼
1. A method for controlling an aerospace system to put a payload into an orbit, comprising the steps of starting a carrier aircraft 1 with a launch vehicle 2 and the payload 3 on board from a base aerodrome 4, flying it to a launch area 5 of the launch vehicle, separating the launch vehicle from the
1. A method for controlling an aerospace system to put a payload into an orbit, comprising the steps of starting a carrier aircraft 1 with a launch vehicle 2 and the payload 3 on board from a base aerodrome 4, flying it to a launch area 5 of the launch vehicle, separating the launch vehicle from the lagging the launch vehicle 2 behind the carrier aircraft 1 with subsequent launch of the launch vehicle 2 to a predetermined trajectory point and separation of the payload 3 from the launch vehicle 2, wherein the carrier aircraft 1 at a maximum cruising speed mode 6 in the launch area 5 of the launch vehicle 2 performs a dive 7 to gain a maximum permissible horizontal flight speed, at a moment that speed is reached by the carrier aircraft, a pitchup 8 is effected at a maximum permissible angle of attack, terminating with a transition 9 to an angle of attack ensuring a near-zero normal g-loading, wherein said pitchup parameters are chosen so as to be adequate to the achievement, at a preset time tp,of a flight trajectory point where a design flight speed VD,a flight altitude HDand trajectory pitch angle φDprovide a maximum launch vehicle 2 payload 3, as well as to ensure subsequent flight to the carrier aircraft 1 with allowable parameters both after separating the launch vehicle 2 and in the case of emergency non-separating the launch vehicle 2, after the carrier aircraft 1 reaches at the preset time tpa flight path point with VD,HD,φDparameters and with the near-zero normal g-loading, the launch vehicle 2 is separated from the carrier aircraft 1 and imparted with a speed relative to the carrier aircraft 1 equal to a design speed 10 at which the launch vehicle 2 lags behind the carrier aircraft 1 at a safe distance at a moment the launch vehicle 2 sustainers are ignited, and before the launch of the launch vehicle 2 to a scheduled trajectory point, the launch vehicle 2 mated with the payload 3 is turned 11 to a position differing from the vertical by an angle of 10-30° in a vertical plane in the launch direction. 2. The method according to claim 1, wherein turning of the launch vehicle 2 prior to its launch with the payload 3 into the scheduled trajectory point is executed by sustainers after their ignition. 3. The method according to claim 1, wherein turning of the launch vehicle 2 prior to its launch with a payload 3 into the scheduled trajectory point is executed by an additional jet engine prior to the sustainers ignition. 4. The method according to claim 1, wherein separating of the launch vehicle 2 from the carrier aircraft 1 is effected, stabilizing a position of the carrier aircraft in an inertial coordinate system.
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이 특허에 인용된 특허 (8)
Palmer William R. (Melbourne FL), High altitude launch platform payload launching apparatus and method.
Cervisi Richard T. (Irvine CA) Toliver David M. (Hawthorne CA) Greenberg Harry S. (Rancho Santa Margarita CA) Kilgore Timothy R. (Garden Grove CA) Arnold Jack H. (Van Nuys CA) Blake John C. (Woodland, Reusable flyback satellite.
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