IPC분류정보
국가/구분 |
United States(US) Patent
등록
|
국제특허분류(IPC7판) |
|
출원번호 |
US-0619281
(2000-07-19)
|
우선권정보 |
FR0004330 (1996-04-05) |
발명자
/ 주소 |
|
출원인 / 주소 |
- Societe Nationale d'Etude et de Construction de Moteurs d'Aviation, FRX
|
대리인 / 주소 |
Weingarten, Schurgin, Gagnebin & Hayes LLP
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인용정보 |
피인용 횟수 :
14 인용 특허 :
5 |
초록
▼
The method serves to place a space vehicle, such as a satellite, on a target orbit such as the orbit adapted to normal operation of the space vehicle and starting from an elliptical initial orbit that is significantly different from, and in particular more eccentric than the target orbit. The space
The method serves to place a space vehicle, such as a satellite, on a target orbit such as the orbit adapted to normal operation of the space vehicle and starting from an elliptical initial orbit that is significantly different from, and in particular more eccentric than the target orbit. The space vehicle is caused to describe a spiral trajectory made up of a plurality of intermediate orbits while a set of high specific impulse thrusters mounted on the space vehicle are fired continuously and without interruption, thereby causing the spiral trajectory to vary so that on each successive revolution, at least during a first stage of the maneuver, perigee altitude increases, apogee altitude varies in a desired direction, and any difference in inclination between the intermediate orbit and the target orbit is decreased, after which, at least during a second stage of the maneuver, changes in perigee altitude and in apogee altitude are controlled individually in predetermined constant directions, while any difference in inclination between the intermediate orbit and the target orbit continues to be reduced until the apogee altitude, the perigee altitude, and the orbital inclination of an intermediate orbit of the space vehicle have substantially the values of the target orbit.
대표청구항
▼
[ What is claim is:] [1.]1. A system for placing a space vehicle, such as a satellite, on a target orbit such as that adapted to normal operation of the space vehicle and starting from an elliptical initial orbit that differs substantially from the target orbit, and in particular that has eccentrici
[ What is claim is:] [1.]1. A system for placing a space vehicle, such as a satellite, on a target orbit such as that adapted to normal operation of the space vehicle and starting from an elliptical initial orbit that differs substantially from the target orbit, and in particular that has eccentricity that is different from that of the target orbit, the system comprising:a set of platforms mounted on the space vehicle;a set of thrusters mounted on said platforms and having high specific impulse, greater than 5000 Ns/kg, and low thrust, less than 10 N, to create a total thrust force applied to the space vehicle;a control device for putting the thrusters into continuous operation after the space vehicle has been placed on its initial orbit so as to enable said space vehicle to reach a target orbit via a completely spiral trajectory, ignoring possible service interruptions, and to stop the thrusters firing when the apogee altitude, the perigee altitude, and the orbital inclination of an intermediate orbit of the space vehicle are substantially equal to the values of the target orbit; anda thrust direction control device comprising at least first means for operating, during a first stage of continuous firing of the set of thrusters, to generate first control signals for aiming total thrust such that on each successive revolution of the space vehicle and in each intermediate orbit, apogee altitude increases, perigee altitude increases to a lesser extent, and any difference in the inclination of the intermediate orbit relative to the target orbit is decreased, and at least second means for operating, during a second stage of the set of thrusters firing, to generate second control signals for aiming total thrust such that on each successive revolution of the space vehicle and in each intermediate orbit, apogee altitude decreases, perigee altitude increases, and any difference of inclination between the intermediate orbits and the target orbit decreases.
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