Fast-low energy transfer to Earth-Moon Lagrange point L2
원문보기
IPC분류정보
국가/구분
United States(US) Patent
등록
국제특허분류(IPC7판)
B64G-001/10
B64G-001/24
B64G-001/40
출원번호
US-0247652
(2014-04-08)
등록번호
US-9284068
(2016-03-15)
발명자
/ 주소
Post, Kevin E.
Belbruno, Edward
출원인 / 주소
The Boeing Company
대리인 / 주소
Perman & Green, LLP
인용정보
피인용 횟수 :
0인용 특허 :
30
초록▼
A control system for a hybrid propulsion spacecraft, configured for transfer between low earth parking orbit (LEO) and a Lissajous L2 orbit (L2O), including a first control portion communicably connected to a high thrust (HT) engine portion of the hybrid propulsion spacecraft, a second control porti
A control system for a hybrid propulsion spacecraft, configured for transfer between low earth parking orbit (LEO) and a Lissajous L2 orbit (L2O), including a first control portion communicably connected to a high thrust (HT) engine portion of the hybrid propulsion spacecraft, a second control portion communicably connected to a low thrust high specific impulse (LT-HI) engine portion of the hybrid propulsion spacecraft, the first and second control portions being configured to control both the HT engine portion and the LT-HI engine portion to provide an optimal LEO to L2O transfer trajectory, wherein the optimal LEO to L2O trajectory includes an optimal LT-HI trajectory portion, selected from a stable manifold trajectory, and an optimal HT trajectory portion, and wherein the LT-HI trajectory portion and HT trajectory portion are configured for providing a combined optimal trajectory along the LEO to L2O transfer trajectory, and are optimized substantially simultaneously.
대표청구항▼
1. A control system for a hybrid propulsion spacecraft configured for transfer between low earth parking orbit (LEO) and a Lissajous L2 orbit (L2O), the control system comprising: a first control portion communicably connected to a high thrust (HT) engine portion of the hybrid propulsion spacecraft;
1. A control system for a hybrid propulsion spacecraft configured for transfer between low earth parking orbit (LEO) and a Lissajous L2 orbit (L2O), the control system comprising: a first control portion communicably connected to a high thrust (HT) engine portion of the hybrid propulsion spacecraft;a second control portion communicably connected to a low thrust high specific impulse (LT-HI) engine portion of the hybrid propulsion spacecraft; andthe first and second control portions being configured to control both the HT engine portion and the LT-HI engine portion of the hybrid propulsion spacecraft to provide an optimal LEO to L2O transfer trajectory;wherein the optimal LEO to L2O trajectory includes an optimal LT-HI trajectory portion, selected from a stable manifold trajectory, and an optimal HT trajectory portion, and wherein the LT-HI trajectory portion and HT trajectory portion are configured for providing a combined optimal trajectory along the LEO to L2O transfer trajectory, and are optimized substantially simultaneously. 2. The system of claim 1, wherein the LT-HI trajectory portion is a time optimal trajectory. 3. The system of claim 1, wherein the LT-HI trajectory effects ballistic capture of the spacecraft at L2O. 4. The system of claim 1, wherein the HT trajectory portion is at least one of a time optimal trajectory and a fuel optimal trajectory. 5. The system of claim 1, wherein the HT trajectory portion is selected from a manifold of HT trajectories distributed between a time optimal trajectory and a fuel optimal trajectory. 6. The system of claim 1, wherein the combined optimal trajectory is optimized with a global optimizer (GO) approach that is configured for application of hybrid propulsion in effecting the combined optimal trajectory. 7. The system of claim 6, wherein the first and second control portions command the HT engine portion and the LT-HI engine portion and effect spacecraft transfer with hybrid propulsion along the combined optimal trajectory commencing with an initial impulse change from LEO to initiation of ballistic capture in L2O. 8. The system of claim 1, wherein the HT trajectory portion transits between LEO and an initial point along the LT-HI trajectory portion. 9. A spacecraft comprising; a spacecraft bus;a hybrid propulsion system connected to the spacecraft bus, the hybrid propulsion system including a high thrust (HT) engine portion, and a low thrust high specific impulse (LT-HI) engine portion; anda control system connected to the bus and controllably coupled to hybrid propulsion system to effect spacecraft transfer between low earth parking orbit (LEO) and a Lissajous L2 orbit (L2O), the control system being configured for generating an optimal LEO to L2O transfer trajectory employing both the HT engine portion and the LT-HI engine portion of the hybrid propulsion system;wherein the optimal LEO to L2O trajectory includes an optimal LT-HI trajectory portion, selected from a stable manifold trajectory, and an optimal HT trajectory portion, and wherein the LT-HI trajectory portion and HT trajectory portion are configured for providing a combined optimal trajectory along the LEO to L2O transfer trajectory, and are optimized substantially simultaneously. 10. The system of claim 9, wherein the LT-HI trajectory portion is a time optimal trajectory. 11. The system of claim 9, wherein the LT-HI trajectory effects ballistic capture of the spacecraft at L2O. 12. The system of claim 9, wherein the HT trajectory portion is at least one of a time optimal trajectory and a fuel optimal trajectory. 13. The system of claim 9, wherein the HT trajectory portion is selected from a manifold of HT trajectories distributed between a time optimal trajectory and a fuel optimal trajectory. 14. The system of claim 9, wherein the combined optimal trajectory is optimized with a global optimizer (GO) approach that is configured for application of hybrid propulsion in effecting the combined optimal trajectory. 15. The system of claim 14, wherein the first and second control portions command the HT engine portion and the LT-HI engine portion and effect spacecraft transfer with hybrid propulsion along the combined optimal trajectory commencing with an initial impulse change from LEO to initiation of ballistic capture in L2O. 16. The system of claim 9, wherein the HT trajectory portion transits between LEO and an initial point along the LT-HI trajectory portion. 17. A method for generating a thrusting profile for a hybrid propulsion spacecraft for transfer between low earth orbit (LEO) and a Lissajous L2 orbit (L2O), the method comprising the steps of: computing a stable manifold (SM) of trajectories leading to L2O based on thrust generated with a low thrust high specific impulse (LT-HI) engine of the hybrid propulsion spacecraft;generating a high thrust (HT) trajectory between LEO and at least one trajectory of the SM, wherein the HT trajectory is generated based at least in part with an impulse change provided by an HT engine of the hybrid propulsion spacecraft, and wherein the HT trajectory and the at least one SM trajectory form a combined trajectory from LEO to L2O; andoptimizing the combined trajectory over both the HT trajectory and the at least one trajectory of the SM in combination and generating a combined optimal trajectory from LEO to L2O. 18. The method of claim 17, further comprising selecting the HT trajectory from a manifold of HT trajectories distributed between a time optimal trajectory and a fuel optimal trajectory. 19. The method of claim 17, further comprising optimizing the combined optimal trajectory with a global optimizer (GO) approach that is configured for application of hybrid propulsion in effecting the combined optimal trajectory. 20. The method of claim 19, further comprising commanding the HT engine portion and the LT-HI engine portion with a first and second control portion of the hybrid propulsion spacecraft and effecting spacecraft transfer with hybrid propulsion along the combined optimal trajectory commencing with an initial impulse change from LEO to initiation of ballistic capture in L2O.
연구과제 타임라인
LOADING...
LOADING...
LOADING...
LOADING...
LOADING...
이 특허에 인용된 특허 (30)
Oh, David, Electric orbit raising with variable thrust.
Belbruno Edward A., Low energy method for changing the inclinations of orbiting satellites using weak stability boundaries and a computer process for implementing same.
Belbruno Edward A., Low energy method for changing the inclinations of orbiting satellites using weak stability boundaries and a computer process for implementing same.
Edward A. Belbruno, Low energy method for changing the inclinations of orbiting satellites using weak stability boundaries and a computer process for implementing same.
Koppel Christophe,FRX ; Valentian Dominique,FRX, Method and a system for launching satellites on non-coplanar orbits, making the use of gravitational assistance from the moon.
Koppel Christophe,FRX ; Valentian Dominique,FRX, Method and a system for launching satellites simultaneously on non-coplanar orbits by using highly eccentric orbits and.
Achkar Issam-Maurice (Cannes la Bocca FRX) Renaud Pierre-Yves (Mandelieu FRX) Sghedoni Michel (Cannes FRX) Guillermin Pierre (Nice FRX), Rate gyro calibration method and apparatus for a three-axis stabilized satellite.
※ AI-Helper는 부적절한 답변을 할 수 있습니다.