High-precision Attitude Controller Design for Deep Space Probe via Adaptive Fast Terminal Sliding Mode Control

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• 英文论文题名：High-precision Attitude Controller Design for Deep Space Probe via Adaptive Fast Terminal Sliding Mode Control
• 论文作者：Weiwei Su ; Ruiyun Qi ; Xuelian Yao
• 英文论文作者：Weiwei Su ; Ruiyun Qi ; Xuelian Yao ; College of Automation engineering ; Nanjing University of Aeronautics and Astronautics ; College of Automative and Traffic Engineering ; Jiangsu University of Technology
• 年：2017
• 作者机构：College of Automation engineering,Nanjing University of Aeronautics and Astronautics;College of Automative and Traffic Engineering,Jiangsu University of Technology;
• 英文论文关键词：Deep Space probe ; Attitude control ; Fast terminal sliding mode ; Adaptive estimation
• 会议召开时间：2017-07-26
• 会议录名称：第36届中国控制会议论文集（A）
• 英文会议录名称：Proceedings of the 36th Chinese Control Conference（A）
• 语种：英文
• 分类号：V448.2
• 学会代码：KZLL
• 会议名称：第36届中国控制会议
• 会议地点：中国辽宁大连
• 主办单位：中国自动化学会控制理论专业委员会
• 学会名称：中国自动化学会控制理论专业委员会
• 页数：6
• 文件大小：415k
• 原文格式：D
• 会议级别：全国

摘要

In this paper, a high-precision attitude controller, based on the combination of fast terminal sliding mode control law and adaptive estimation theory, is designed for a class of deep space probes with unknown external disturbances, such as the gradient torque from universal gravitation, the solar radiation pressure because of solar shining. Besides, the variation of moment inertia matrix of the space probes during the whole flying course is also considered. The adaptive control theory and the fast terminal sliding control strategy are employed to estimate the lumped uncertainty and enhance the robustness of the attitude control system. Then, the Lyapunov stability theory is used to fulfill the stability analysis of this system. Finally, simulation results are obtained to validate the effectiveness of the proposed controller, which has a fast convergence rate and high control precision.
In this paper, a high-precision attitude controller, based on the combination of fast terminal sliding mode control law and adaptive estimation theory, is designed for a class of deep space probes with unknown external disturbances, such as the gradient torque from universal gravitation, the solar radiation pressure because of solar shining. Besides, the variation of moment inertia matrix of the space probes during the whole flying course is also considered. The adaptive control theory and the fast terminal sliding control strategy are employed to estimate the lumped uncertainty and enhance the robustness of the attitude control system. Then, the Lyapunov stability theory is used to fulfill the stability analysis of this system. Finally, simulation results are obtained to validate the effectiveness of the proposed controller, which has a fast convergence rate and high control precision.

引文

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