Attitude Maneuvering Trajectory Design and Tracking Control for Flexible Spacecraft

被引：0
|
作者：
Zhang X.-Y. [1 ]
Zong Q. [1 ]
Zhu W.-W. [1 ]
Liu W.-J. [2 ]
机构：
[1] School of Electrical and Information Engineering, Tianjin University, Tianjin
[2] Beijing Institute of Control Engineering, Beijing
来源：
Yuhang Xuebao/Journal of Astronautics | 2019年 / 40卷 / 11期
关键词：
Active vibration suppression; Attitude maneuver control; Fast robust input shaper (FRIS); Flexible spacecraft; Trajectory optimization;
D O I：
10.3873/j.issn.1000-1328.2019.11.009
中图分类号：
学科分类号：
摘要：
For the contradiction between "rapidity" and "stability" of the attitude maneuvering of a flexible spacecraft, an integrated method of optimization and control for the attitude maneuvering trajectory design and tracking control is proposed in this paper. Firstly, considering the rapidity and stability requirements of the flexible spacecraft's attitude maneuvering, the multi-objective and multi-constraint conditions are established, and the attitude trajectory is acquired by optimization, which can maximize the system stability while considering the performance of rapidity. Then, a novel fast robust input shaper(FRIS) is designed. It could suppress the vibration effectively and the action time is shorter than a traditional input shaper, which is beneficial for the rapidity and high precision. Finally, a novel adaptive continuous terminal sliding mode controller(ACTSMC) is proposed, which can avoid gain over-estimation, and guarantee the fast and high-precision tracking control of the desired attitude trajectory. The numerical simulations have demonstrated the effectiveness of the approach proposed. © 2019, Editorial Dept. of JA. All right reserved.
引用
收藏
页码：1332 / 1340
页数：8
相关论文
共 24 条
  • [1] Cao X., Yue C., Liu M., Flexible satellite attitude maneuver via constrained torque distribution and active vibration suppression, Aerospace Science and Technology, 67, pp. 387-397, (2017)
  • [2] Yu Z., Guo Y., Wang L., Et al., Adaptive robust attitude control and active vibration suppression of flexible spacecraft, Proceedings of the Institution of Mechanical Engineers, Part G: Journal of Aerospace Engineering, 231, 6, pp. 1076-1087, (2017)
  • [3] Yao Y.-H., Zhou J., Liu Y.-Y., Research on flexible vibration suppression strategy for variable configuration space station based on input shaping technique, Journal of Astronautics, 34, 5, pp. 665-670, (2013)
  • [4] Singer N.C., Seering W.P., Preshaping command inputs to reduce system vibration, Journal of Dynamic Systems, Measurement and Control, 112, 1, pp. 76-82, (1990)
  • [5] Singhose W., Command shaping for flexible systems: A review of the first 50 years, International Journal of Precision Enginee-ring and Manufacturing, 10, 4, pp. 153-168, (2009)
  • [6] Ma G.-F., Gao H., Lv Y.-Y., Et al., Super-twisting observer based finite-time backstepping attitude control for a combined spacecraft, Journal of Astronautics, 38, 11, pp. 1168-1176, (2017)
  • [7] Yavuz H., Mlstlkoglu S., Kapucu S., Hybrid input shaping to suppress residual vibration of flexible systems, Journal of Vibration and Control, 18, 1, pp. 132-140, (2012)
  • [8] Mar R., Goyal A., Nguyen V., Et al., Combined input shaping and feedback control for double-pendulum systems, Mechanical Systems and Signal Processing, 85, 15, pp. 267-277, (2017)
  • [9] Singhose W., Eloundou R., Lawrence J., Command generation for flexible systems by input shaping and command smoothing, Journal of Guidance Control and Dynamics, 33, 6, pp. 1697-1707, (2012)
  • [10] Pai M.C., Discrete-time dynamic output feedback input shaping control of vibration in uncertain time-delay flexible structures, Applied Mathematics and Computation, 250, pp. 675-688, (2015)
123