Disturbance observer based finite-time coordinated attitude tracking control for spacecraft on SO(3)

doi:10.23919/JSEE.2020.000098

Journal of Systems Engineering and Electronics ›› 2020, Vol. 31 ›› Issue (6): 1274-1285.doi: 10.23919/JSEE.2020.000098

• CONTROL THEORY AND APPLICATION • Previous Articles Next Articles

Disturbance observer based finite-time coordinated attitude tracking control for spacecraft on SO(3)

Zhen SHI^1,*(), Yaen XIE²(), Chengchen DENG¹(), Kun ZHAO¹(), Yushan HE¹(), Yong HAO¹()

¹ College of Automation, Harbin Engineering University, Harbin 150001, China
² College of Aerospace and Civil Engineering, Harbin Engineering University, Harbin 150001, China

Received:2019-10-25 Online:2020-12-18 Published:2020-12-29
Contact: Zhen SHI E-mail:shizhen@hrbeu.edu.cn;xieenya@126.com;dengdada86@126.com;345005504@qq.com;heyvshan@163.com;haoyong@hrbeu.edu.cn
About author:|SHI Zhen was born in 1961. He received his B.S. degree in aerospace engineering and M.S. degree in control engineering from Institute of Harbin Shipbuilding Engineering, Harbin, China, in 1982 and 1986, respectively. He received his Ph.D. degree in control engineering from Harbin Engineering University, Harbin, China, in 2001. He is now a professor with Harbin Engineering University, Harbin, China. His research interests include the guidance and control technology for aerocraft, the control theory and its application and the strap-down inertial navigation technology. E-mail: shizhen@hrbeu.edu.cn||XIE Yaen was born in 1990. He received his B.S. degree in information and computing science from Liaoning University, Shenyang, China, in 2013 and M.S. degree in aerospace engineering from Harbin Engineering University, Harbin, China, in 2015. He is currently pursuing his Ph.D. degree in control science and engineering at Harbin Engineering University, Harbin, China. From 2018 to 2019, he was a special research student of the Graduate School of Engineering, Nagoya University. His research interests include the dynamics of the complex spacecraft system, the dynamics and control of spacecraft, and the dynamics and control of the spatial multibody system. E-mail: xieenya@126.com||DENG Chengchen was born in 1986. He received his B.S. degree in electronic information engineering from Nanjing University of Science and Technology, Nanjing, China, in 2007, and M.S. degree in electronic information engineering from Sichuan University, Chengdu, China, in 2013. His research interests include the guidance and control technology for spacecraft, the control theory and its application and the strap-down inertial navigation technology. E-mail: dengdada86@126.com||ZHAO Kun was born in 1989. He received his B.S. degree in Nanjing University of Aeronautics and Astronautics in 2013. From 2014, he has been a Ph.D. candidate of the College of Automation, Harbin Engineering University. His research interests include mission planning, optimal control for agile satellite, and distributed control for spacecraft formation. E-mail: 345005504@qq.com||HE Yushan was born in 1997. He received his B.S. degree in 2019 from Zhengzhou University. He is now studying for his master's degree at the College of Automation, Harbin Engineering University. His research interest is spacecraft formation attitude control. E-mail: heyvshan@163.com||HAO Yong was born in 1979. He received his B.S. degree in 2007, M.S. degree in 2011 and Ph.D. degree in 2016 from Harbin Engineering University. He is currently a lecturer with the College of Automation, Harbin Engineering University. His research interests include mission planning and control for spacecraft. E-mail: haoyong@hrbeu.edu.cn
Supported by:
This work was supported by the National Natural Science Foundation of China (11772185), the Natural Science Foundation of Heilongjiang Province (F2017005), and the Fundamental Research Funds for the Central Universities (HEUCFP201770)

Abstract

Abstract:

To solve the problem of attitude synchronization control for spacecraft formation flying (SFF) suffering from external disturbances under a directed communication topology, a sliding mode disturbance observer (SMDO) based on the finite-time control strategy is developed to observe the time-varying external disturbance via estimating the upper bound of its first derivative. Meanwhile, the rotation matrix is employed to describe the attitude of SFF for the purpose of the avoidance of singularity and unwinding phenomenon. As for the attitude synchronization and the tracking control architecture, a sliding mode surface (SMS) is given such that the control objective can be achieved. The effectiveness and the validity of the proposed method are elaborated via theoretical analysis and numerical simulations.

Key words: coordinated attitude control, disturbance observer, rotation matrix, attitude synchronization control

Zhen SHI, Yaen XIE, Chengchen DENG, Kun ZHAO, Yushan HE, Yong HAO. Disturbance observer based finite-time coordinated attitude tracking control for spacecraft on SO(3)[J]. Journal of Systems Engineering and Electronics, 2020, 31(6): 1274-1285.

Figures/Tables 10

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Disturbance observer based finite-time coordinated attitude tracking control for spacecraft on SO(3)

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