Spacecraft non-singular adaptive terminal sliding mode attitude-orbit coupling control

被引：0

作者：

Pan F. ^{[1
]}

Zhu H. ^{[1
]}

机构：

[1] School of Astronautics, Beihang University, Beijing

来源：

Beijing Hangkong Hangtian Daxue Xuebao/Journal of Beijing University of Aeronautics and Astronautics | 2020年 / 46卷 / 07期

关键词：

Adaptive control; Attitude-orbit coupling control; Dual quaternion; Finite time control; Non-singular terminal sliding mode;

D O I：

10.13700/j.bh.1001-5965.2019.0459

中图分类号：

学科分类号：

摘要：

A non-singular adaptive terminal sliding mode control law is proposed to simultaneously control the attitude and orbit of the spacecraft. Firstly, the attitude-orbit coupling dynamic model of the spacecraft with parameter uncertainty is established based on the dual quaternion. Secondly, based on the integrated model of spacecraft, non-singular terminal sliding mode control law is proposed to track the target. Considering the uncertainty of spacecraft quality characteristics, an adaptive control law is designed to further improve the controller effect. The stability of the above control law is proved by the Lyapunov function. Finally, the simulation example of tracking control around the asteroid shows the effectiveness of the control law. The results show that the controller has higher control precision and can converge in limited time. There is no singularity in the simulation. The controller suppresses the influence of the uncertainty of quality characteristics on the control, and the terminal sliding mode chattering characteristics. © 2020, Editorial Board of JBUAA. All right reserved.

引用

页码：1354 / 1362

页数：8

共 17 条

[1]

ZHU Z X, SHI G F, FAN R S., Dynamic modeling methods of attitude and orbital coupling for spacecraft relative motion, Flight Dynamics, 36, 1, pp. 1-6, (2018)

[2]

WU Y X., Research on dual-quaternion navigation algorithm and nonlinear Gaussian filtering, (2005)

[3]

ZHANG H Z., Integrated dynamics modeling and control for space-craft based on dual quaternion, (2010)

[4]

DANG Q Q, GUI H C, XU M, Et al., Attitude and position tracking control for spacecraft without velocity measurement, Acta Aeronautica et Astronautica Sinica, 39, S1, (2018)

[5]

GUI H C, VUKOVICH G., Dual-quaternion-based adaptive motion tracking of spacecraft with reduced control effort, Nonlinear Dynamics, 83, 1-2, pp. 579-614, (2016)

[6]

ZOU A M, KUMAR K D, HOU Z G., Finite-time attitude tracking control for spacecraft using terminal sliding mode and Chebyshev neural network, IEEE Transactions on Systems, Man, and Cybernetics, Part B: Cybernetics, 41, 4, pp. 950-963, (2011)

[7]

ZOU A M, KUMAR K D, HOU Z G., Corrections to "finite-time attitude tracking control for spacecraft using terminal sliding model and Chebyshev neural network, IEEE Transactions on Systems, Man, and Cybernetics, Part B: Cybernetics, 43, 2, (2013)

[8]

WANG J Y., Research on spacecraft integrated orbit and attitude dynamics, control and navigation, (2013)

[9]

DONG H Y, HU Q L, AKELLA M R., Dual-quaternion-based spacecraft autonomous rendezvous and docking under six-degree-of-freedom motion constraints, Journal of Guidance, Control, and Dynamics, 41, 5, pp. 1150-1162, (2018)

[10]

DONG H, HU Q, MA G., Dual-quaternion based fault-tolerant control for spacecraft formation flying with finite-time convergence, ISA Transactions, 61, pp. 87-94, (2016)

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