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A direct parametric approach to spacecraft attitude tracking control

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Abstract

Through the direct parameter approach, a solution for spacecraft attitude tracking is presented. First of all, the spacecraft attitude tracking control model is built up by the error equation of the second-order nonlinear quaternion-based attitude system. Based on the control model, a suitable controller is designed by the direct parameter approach. Compared with other control strategies, the direct parameter approach can offer all degrees of freedom for the controller to satisfy the requirements for system properties and turn the original nonlinear system into closed-loop linear system. Furthermore, this paper optimizes the controller according to the robustness, limitation of controller output and closed-loop eigenvalue sensitivity. Putting the controller into the original system, the state response of the closed-loop system and the output of controller are plotted in Matlab to verify the availability and robustness of the controller. Therefore, the controlled spacecraft can achieve the goal of tracking on the mobile target with the external disturbance torque.

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Acknowledgement

The first author hereby extends her thanks to all the classmates in the Center for Control Theory and Guidance Technology in Harbin Institute of Technology, because of their help in the academic research and daily life. Additionally, the first author thanks professor Bin Zhou for his help of academic paper writing.

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Authors and Affiliations

  1. Center for Control Theory and Guidance Technology, Harbin Institute of Technology, Harbin, 150001, China

    Xiao-Yi Wang & Guang-Ren Duan

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  1. Xiao-Yi Wang
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  2. Guang-Ren Duan
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Corresponding author

Correspondence to Xiao-Yi Wang.

Additional information

This work was supported by National Natural Science Foundation of China (No. 61321062).

Recommended by Associate Editor Chandrasekhar Kambhampati

Xiao-Yi Wang received the B. Sc. degree from Department of Control Science and Engineering, Harbin Institute of Technology, China in 2014. She received the M. Sc. degree in Centre for Control Theory and Guidance Technology, Harbin Institute of technology, China in 2017.

Her research interests include nonlinear robust control and spacecraft attitude control.

Guan-Ren Duan received the B. Sc. degree in applied mathematics from Yanshan University, China in 1983, the M. Sc. degree in control systems theory from Harbin Engineering University, China in 1986, and received the Ph.D. degree in control systems theory from Harbin Institute of Technology, China in 1989. From 1989 to 1991, he was a post-doctoral researcher at Harbin Institute of Technology, where he became a professor of control systems theory in 1991. He visited the University of Hull, UK, and the University of Sheffield, UK from December 1996 to October 1998, and worked at the Queens University of Belfast, UK from October 1998 to October 2002. Since August 2000, he has been elected specially employed professor at Harbin Institute of Technology sponsored by the Cheung Kong Scholars Program of the Chinese government. He is currently the director of the Centre for Control Systems and Guidance Technology at Harbin Institute of Technology. He is the author and co-author of over 300 publications. He is a chartered engineer in the UK, a senior member of IEEE and a fellow of IEE.

His research interests include robust control, eigenstructure assignment, descriptor systems, missile autopilot control and magnetic bearing control.

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Wang, XY., Duan, GR. A direct parametric approach to spacecraft attitude tracking control. Int. J. Autom. Comput. 14, 626–636 (2017). https://doi.org/10.1007/s11633-017-1089-4

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