Spacecraft Attitude Maneuver Using Fast Terminal Sliding Mode Control Based on Variable Exponential Reaching Law

Conference paper
Part of the Lecture Notes in Electrical Engineering book series (LNEE, volume 622)


As a typical multi-input and multi-output nonlinear system, spacecraft faces the challenges of rapid maneuvering at a large angle and can control rapidly as well as stably. However, there are several problems in the sliding mode control method commonly used in the aerospace field, such as slow convergence, singularity, and chattering. Taking the consideration of aforementioned conditions, this paper proposes a non-singular fast terminal sliding mode control based on variable exponential reaching law (NFTSMC-VERL). Firstly, using a continuous hyperbolic tangent function instead of symbolic function, variable exponential reaching law is designed to solve the problem of chattering in exponential reaching law. The reachability and finite time convergence of this method are proved by theory. Secondly, a non-singular fast terminal sliding mode (NFTSM) surface based on satellite attitude dynamics is designed as a sliding mode function. Thirdly, the controller is designed by combining the VERL with the NFTSM function. Finally, not only has the simulation results showed the good tracking performance of the spacecraft attitude control system, but also the chattering and singularity phenomenon of the traditional sliding mode controller is avoided by the designed controller. Besides, the robustness of designed controller is improved, compared with the traditional sliding mode controller.


Rapid attitude maneuver Variable exponential reaching law Fast convergence rate Non-singularity 


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© Springer Nature Singapore Pte Ltd. 2020

Authors and Affiliations

  1. 1.School of Aeronautics and AstronauticsSmall Satellite Technology Center, Shanghai Jiao Tong UniversityShanghaiChina

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