Trajectory Tracking based on Time-Varying Sliding Mode Controller for Hypersonic Vehicle with Aileron Stuck

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• 英文论文题名：Trajectory Tracking based on Time-Varying Sliding Mode Controller for Hypersonic Vehicle with Aileron Stuck
• 论文作者：Haibo Ji ; Lei Wang ; Zhuoyue Song ; Xiangdong Liu ; Zhirong Lei
• 英文论文作者：Haibo Ji ; Lei Wang ; Zhuoyue Song ; Xiangdong Liu ; Zhirong Lei ; State Key Laboratory of Intelligent Control and Decision of Complex Systems and School of Automation ; Beijing Institute of Technology ; School of Automation ; Northwestern Polytechnical University
• 年：2017
• 作者机构：State Key Laboratory of Intelligent Control and Decision of Complex Systems and School of Automation,Beijing Institute of Technology;School of Automation,Northwestern Polytechnical University;
• 英文论文关键词：Trajectory Tracking ; Stuck Aileron ; Time-Varying Sliding Mode
• 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：V249
• 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：5
• 文件大小：248k
• 原文格式：D
• 会议级别：全国

摘要

This paper presents nonlinear robust trajectory tracking strategies for the hypersonic vehicle whose ailerons are stuck at an unknown angular position. Firstly, a time-varying sliding mode control strategy for general second-order systems is introduced, and the chattering of sliding mode controller is alleviated. Secondly, the dynamics of hypersonic vehicle are transformed into two second-order systems. Then, the corresponding guidance law and attitude controller are designed using time-varying sliding mode controller. By the proposed strategies, the hypersonic vehicle can fly along the reference trajectory.Finally, the proposed strategies are applied to a hypersonic platform to verify its validity.
This paper presents nonlinear robust trajectory tracking strategies for the hypersonic vehicle whose ailerons are stuck at an unknown angular position. Firstly, a time-varying sliding mode control strategy for general second-order systems is introduced, and the chattering of sliding mode controller is alleviated. Secondly, the dynamics of hypersonic vehicle are transformed into two second-order systems. Then, the corresponding guidance law and attitude controller are designed using time-varying sliding mode controller. By the proposed strategies, the hypersonic vehicle can fly along the reference trajectory.Finally, the proposed strategies are applied to a hypersonic platform to verify its validity.

引文

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