Multi-objective transfer to libration-point orbits via the mixed low-thrust and invariant-manifold approach

被引:3
作者
Haijun Peng
Biaosong Chen
Zhigang Wu
机构
[1] Dalian University of Technology,State Key Laboratory of Structural Analysis for Industrial Equipment, Department of Engineering Mechanics
[2] Dalian University of Technology,State Key Laboratory of Structural Analysis for Industrial Equipment, School of Aeronautics and Astronautics
来源
Nonlinear Dynamics | 2014年 / 77卷
关键词
Multi-objective optimization; Nonlinear optimal control; Symplectic algorithm; Circular restricted three-body problem; Low-thrust transfer; Invariant manifold;
D O I
暂无
中图分类号
学科分类号
摘要
The multi-objective optimization of transfer trajectories from an orbit near Earth to a periodic libration-point orbit in the Sun–Earth system using the mixed low-thrust and invariant-manifold approach is investigated in this paper. A two-objective optimization model is proposed based on the mixed low-thrust and invariant-manifold approach. The circular restricted three-body model (CRTBP) is utilized to represent the motion of a spacecraft in the gravitational field of the Sun and Earth. The transfer trajectory is broken down into several segments; both low-thrust propulsion and stable manifolds are utilized based on the CRTBP in different segments. The fuel cost, which is generated only by the low-thrust trajectory for transferring the spacecraft from an orbit near Earth to a stable manifold, is minimized. The total flight time, which includes the time during which the spacecraft is controlled by the low-thrust trajectory and the time during which the spacecraft is moving on the stable manifold, is also minimized. Using the nondominated sorting genetic algorithm for the resulting multi-objective optimization problem, highly promising Pareto-optimal solutions for the transfer of the spacecraft are found. Via numerical simulations, it is shown that tradeoffs between time of flight and fuel cost can be quickly evaluated using this approach. Furthermore, for the same time of flight, transfer trajectories based on the mixed-transfer method can save a larger amount of fuel than the low-thrust method alone.
引用
收藏
页码:321 / 338
页数:17
相关论文
共 83 条
[1]  
Peng HJ(2013)Surrogate-based parameter optimization and optimal control for optimal trajectory of Halo orbit rendezvous Aerosp. Sci. Technol. 26 176-184
[2]  
Yang CF(2011)Optimal periodic controller for formation flying on libration point orbits Acta. Astronaut. 69 537-550
[3]  
Li YP(2010)The use of invariant manifolds for transfers between unstable periodic orbits of different energies Celest. Mech. Dyn. Astron. 107 471-485
[4]  
Zhang S(2010)Chaining periodic three-body orbits in the Earth–Moon system Acta. Astronaut. 67 623-638
[5]  
Chen BS(2007)Transfer to distant retrograde orbits using manifold theory J. Guid. Control. Dyn. 30 1261-1267
[6]  
Peng HJ(1980)Trajectories and orbital maneuvers for the first Libration-point satellite J. Guid. Control. Dyn. 3 549-554
[7]  
Zhao J(1994)Transfers between libration-point orbits in the elliptic restricted problem Celest. Mech. Dyn. Astron. 58 317-337
[8]  
Wu ZG(2013)Optimal guidance based on receding horizon control for low-thrust transfer to libration point orbits Adv. Space. Res 51 2093-2111
[9]  
Zhong WX(2010)Low-thrust transfers in the Earth–Moon system, including applications to libration point orbits J. Guid. Control. Dyn. 33 533-549
[10]  
Davis KE(2005)Trajectory correction manoeuvres in the transfer to libration point orbits Acta. Astronaut. 56 652-669