Cooperative rendezvous between two spacecraft under finite thrust

被引：4
作者：
Feng W. [1 ]
Wang B. [1 ]
Yang K. [1 ]
Zhao D. [1 ]
机构：
[1] Department of Engineering Mechanics, Shandong University, 17923 Jingshi Road, Jinan
来源：
CEAS Space Journal | 2017年 / 9卷 / 02期
关键词：
Cooperative rendezvous; Finite thrust; Hybrid algorithm; Optimal control; Sequential quadratic programming;
D O I：
10.1007/s12567-017-0145-9
中图分类号：
学科分类号：
摘要：
Dynamic equations of orbital elements of a modified vernal equinox for a far-distance cooperative rendezvous between two spacecraft were set up in this paper. The process of the far-distance cooperative rendezvous was optimized by a hybrid algorithm combining particle swarm optimization and differential evolution. The convergent costate vectors were obtained and set as the initial values of sequential quadratic programming to search for precise solutions, and the results proved to be stable and convergent. It can be seen from the results that the flight time of the cooperative rendezvous would be largely saved the amplitude of the thrust would be increased if the other conditions are fixed, and the fuel consumption would not be increased. However, the flight time would no longer decrease when the amplitude of the thrust reaches a certain value. In the last section of this paper, cooperative rendezvous and active–passive rendezvous were compared and analyzed, showing the advantages of cooperative rendezvous when the initial conditions are the same. © 2017, CEAS.
引用
收藏
页码：227 / 241
页数：14
相关论文
共 22 条
  • [1] Kechichian J.A., The optimization of continuous constant acceleration transfer trajectories in the presence of the J 2 perturbation, Astrodynamics, 1999, pp. 1627-1648, (2000)
  • [2] Goodson T.D., Fuel-optimal Control and Guidance for Low-and Medium-Thrust Orbit Transfer, (1995)
  • [3] Chien-Hsiung C., Speyer J.L., Periodic optimal hypersonic scramjet cruise, Optim. Control Appl. Methods, 8, 3, pp. 1403-1408, (1985)
  • [4] C-Hgoodson C., Troy D., Ledsinger L., Hanson J., The second variation and neighboring optimal feedback guidance for multiple burn orbit transfers, Guidance, Navigation, and Control Conference, (1995)
  • [5] Betts J.T., Erb S.O., Optimal low thrust trajectories to the moon, SIAM J. Appl. Dyn. Syst., 2, 2, pp. 144-170, (2003)
  • [6] Betts J.T., Very low-thrust trajectory optimization using a direct SQP method, J. Comput. Appl. Math., 120, s 1–s 2, pp. 27-40, (2000)
  • [7] Herman A.L., Spencer D.B., Optimal, low-thrust earth-orbit transfers using higher-order collocation methods, J. Guid. Control Dyn., 25, 1, pp. 40-47, (2002)
  • [8] Armellin R., Topputo F., A sixth-order accurate scheme for solving two-point boundary value problems in astrodynamics, Celest. Mech. Dyn. Astron., 96, 3, pp. 289-309, (2006)
  • [9] Zavoli A., Colasurdo G., Indirect optimization of finite-thrust cooperative rendezvous, J. Guid. Control Dyn., 38, 2, pp. 304-314, (2015)
  • [10] Zhu R.Z., Rendezvous and docking techniques of spacecraft [M], (2007)
123