Orbit Transfer Optimization for Lunar Relay Satellite with Electric Thrust Based on Q-law
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- 英文论文题名：Orbit Transfer Optimization for Lunar Relay Satellite with Electric Thrust Based on Q-law
- 论文作者：Ran An ; Min Wang ; Xingang Liang ; Yiquan Wang
- 英文论文作者：Ran An ; Min Wang ; Xingang Liang ; Yiquan Wang ; Institute of Telecommunication Satellite ; CAST
- 年：2017
- 作者机构：Institute of Telecommunication Satellite,CAST;
- 英文论文关键词：Q-law ; Lyapunov Feedback Control ; Low-thrust transfer trajectory ; Invariant Manifolds ; Electric thruster
- 会议召开时间：2017-07-26
- 会议录名称：第36届中国控制会议论文集（B）
- 英文会议录名称：Proceedings of the 36th Chinese Control Conference（B）
- 语种：英文
- 分类号：V412.41;V439.4
- 学会代码：KZLL
- 会议名称：第36届中国控制会议
- 会议地点：中国辽宁大连
- 主办单位：中国自动化学会控制理论专业委员会
- 学会名称：中国自动化学会控制理论专业委员会
- 页数：6
- 文件大小：484k
- 原文格式：D
- 会议级别：全国
摘要
Due to the relative position invariance of L2 Libration point in the Earth-moon system, Halo orbits around LL2 adapt to the best mission trajectory for Lunar Relay Satellite, which can offer relay communication for space missions such as deep-space exploration and Moon outpost construction. In order to improve the payload launch capacity of Lunar Relay Satellite, the electric thrusters which have high specific impulse and low thrust can be used as main propulsion. In this paper, the Q-law control theory in optimal control theory is adopted to calculate the optimal transfer orbit of Lunar Relay Satellite using electric thrusters. In addition, the effect of initial orbit of transfer trajectory and invariant manifold has been considerate. The result shows the design rules and the algorithm is of great important engineering meaning.
Due to the relative position invariance of L2 Libration point in the Earth-moon system, Halo orbits around LL2 adapt to the best mission trajectory for Lunar Relay Satellite, which can offer relay communication for space missions such as deep-space exploration and Moon outpost construction. In order to improve the payload launch capacity of Lunar Relay Satellite, the electric thrusters which have high specific impulse and low thrust can be used as main propulsion. In this paper, the Q-law control theory in optimal control theory is adopted to calculate the optimal transfer orbit of Lunar Relay Satellite using electric thrusters. In addition, the effect of initial orbit of transfer trajectory and invariant manifold has been considerate. The result shows the design rules and the algorithm is of great important engineering meaning.
Due to the relative position invariance of L2 Libration point in the Earth-moon system, Halo orbits around LL2 adapt to the best mission trajectory for Lunar Relay Satellite, which can offer relay communication for space missions such as deep-space exploration and Moon outpost construction. In order to improve the payload launch capacity of Lunar Relay Satellite, the electric thrusters which have high specific impulse and low thrust can be used as main propulsion. In this paper, the Q-law control theory in optimal control theory is adopted to calculate the optimal transfer orbit of Lunar Relay Satellite using electric thrusters. In addition, the effect of initial orbit of transfer trajectory and invariant manifold has been considerate. The result shows the design rules and the algorithm is of great important engineering meaning.
引文
[1]Yuan Ren,Jinjun Shan.Low-energy lunar transfers using spatial transit orbits.Communications in Nonlinear Science and Numerical Simulation,19(3):554–569,2014.
[2]Seungwon Lee,Anastassios E.Petropoulos,and Paul von Allmen,Low-thrust orbit transfer optimization with refined Q-law and multi-objective genetic algorithm,AAS/AIAA Astrodynamics Specialists Conference,2005.
[3]J.T.Betts,Survey of numerical methods for trajectory optimization,J.Guidance,Control,and Dynamics,21(2),193-207,1998.
[4]A.E.Petropoulos,Simple Control Laws for Low-thrust orbit transfers,AAS/AIAA Astrodynamics Specialist Conference,Big Sky,Montana,Aug.03-07,2003.
[5]A.E.Petropoulos,Low-thrust orbit transfer using candidate Lyapunov Functions with a Mechanism for Coasting,AIAA/AAS Astrodynamics Specialist Conference,Providence,Rhode Island,Aug.16-19,2004.
[6]Rodney L.Anderson,Martin W.Lo.Role of Invariant Manifolds in Low-Thrust Trajectory Design,Journal of Guidance Control and Dynamics,32(6),1921-1930,2009.
[7]David C.Folta,Thomas A.Pavlak.Earth–Moon Libration point orbit stationkeeping:Theory,modeling,and operations,Acta Astronautica,94(1),421-433,2014.
[8]Jun Zhou,Li Xue,Fengqi Zhou.Computations of Low Energy Escaping/Capturing Trajectories in Hill's Region via An Extended PoincaréMap,Journal of astronautics,28(3),643-647,2007.
[9]Hanlun Lei,Bo Xu.High-order solutions of invariant manifolds associated with libration point orbits in the elliptic restricted three-body system,Celestial Mechanics and Dynamical Astronomy,117(4),349-384,2013.
[10]Anastassions E.Petropoulos,Refinements to the Q-law for low-thrust orbit transfers,AAS 05-162,AAS/AIAA Space Flight Mechanics Conference,Copper Mountain,Colorado,Jan.23-27,2005.
[11]Battin,R.H.,An Introduction to the Mathematics and Methods of Astrodynamics,AIAA,New York,1987,pp.488-489.
[12]Anastassions E.Petropoulos,Optimization of low-thrust orbit transfers using the Q-law for the initial guess,AAS/AIAA Astrodynamics Specialists Conference,Lake Tahoe,California,August 7-11,2005
[2]Seungwon Lee,Anastassios E.Petropoulos,and Paul von Allmen,Low-thrust orbit transfer optimization with refined Q-law and multi-objective genetic algorithm,AAS/AIAA Astrodynamics Specialists Conference,2005.
[3]J.T.Betts,Survey of numerical methods for trajectory optimization,J.Guidance,Control,and Dynamics,21(2),193-207,1998.
[4]A.E.Petropoulos,Simple Control Laws for Low-thrust orbit transfers,AAS/AIAA Astrodynamics Specialist Conference,Big Sky,Montana,Aug.03-07,2003.
[5]A.E.Petropoulos,Low-thrust orbit transfer using candidate Lyapunov Functions with a Mechanism for Coasting,AIAA/AAS Astrodynamics Specialist Conference,Providence,Rhode Island,Aug.16-19,2004.
[6]Rodney L.Anderson,Martin W.Lo.Role of Invariant Manifolds in Low-Thrust Trajectory Design,Journal of Guidance Control and Dynamics,32(6),1921-1930,2009.
[7]David C.Folta,Thomas A.Pavlak.Earth–Moon Libration point orbit stationkeeping:Theory,modeling,and operations,Acta Astronautica,94(1),421-433,2014.
[8]Jun Zhou,Li Xue,Fengqi Zhou.Computations of Low Energy Escaping/Capturing Trajectories in Hill's Region via An Extended PoincaréMap,Journal of astronautics,28(3),643-647,2007.
[9]Hanlun Lei,Bo Xu.High-order solutions of invariant manifolds associated with libration point orbits in the elliptic restricted three-body system,Celestial Mechanics and Dynamical Astronomy,117(4),349-384,2013.
[10]Anastassions E.Petropoulos,Refinements to the Q-law for low-thrust orbit transfers,AAS 05-162,AAS/AIAA Space Flight Mechanics Conference,Copper Mountain,Colorado,Jan.23-27,2005.
[11]Battin,R.H.,An Introduction to the Mathematics and Methods of Astrodynamics,AIAA,New York,1987,pp.488-489.
[12]Anastassions E.Petropoulos,Optimization of low-thrust orbit transfers using the Q-law for the initial guess,AAS/AIAA Astrodynamics Specialists Conference,Lake Tahoe,California,August 7-11,2005