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Attitude and Orbit Optimal Control of Combined Spacecraft via a Fully-Actuated System Approach

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Abstract

This paper investigates the attitude and orbit control for the combined spacecraft formed after a target spacecraft without the autonomous control ability is captured by a service spacecraft. The optimal controller of fully-actuated system is proposed to realize the attitude and orbit stabilization control of combined spacecraft. The stability of the system is proved by introducing Lyapunov function. Numerical simulation of the combined spacecraft and physical experiment based on the combined spacecraft simulator (CSS) are completed. Both simulation and experiment results demonstrate the effectiveness and practicability of the optimal controller of fully-actuated system.

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Authors and Affiliations

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

    Guangquan Duan & Guo-Ping Liu

  2. Department of Electronic and Electrical Engineering, Southern University of Science and Technology, Shenzhen, 518055, China

    Guo-Ping Liu

Authors
  1. Guangquan Duan
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  2. Guo-Ping Liu
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Corresponding authors

Correspondence to Guangquan Duan or Guo-Ping Liu.

Additional information

This paper was supported in part by the National Natural Science Foundation of China under Grant Nos. 62173255 and 62188101.

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Duan, G., Liu, GP. Attitude and Orbit Optimal Control of Combined Spacecraft via a Fully-Actuated System Approach. J Syst Sci Complex 35, 623–640 (2022). https://doi.org/10.1007/s11424-022-1492-y

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  • DOI: https://doi.org/10.1007/s11424-022-1492-y

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