基于部分状态反馈的高速拦截弹制导控制一体化设计 -- 西北工业大学学报,2017,35(6):954-960
论文:2017,Vol:35,Issue(6):954-960
引用本文:
王洋, 周军. 基于部分状态反馈的高速拦截弹制导控制一体化设计[J]. 西北工业大学学报
Yang Wang, Zhou Jun. Partial States Feedback-Based Integrated Guidance and Control Design for Hypersonic Interceptor[J]. Northwestern polytechnical university

基于部分状态反馈的高速拦截弹制导控制一体化设计
王洋, 周军
西北工业大学 精确制导与控制研究所, 陕西 西安 710072
摘要:
针对视线角速率与攻角都无法测量的高速拦截弹制导控制一体化(IGC)系统,提出一种新型基于部分状态反馈的控制器。首先,基于线性扩张状态观测器(LESO)同时观测不可测的中间状态与未知干扰。之后,基于反演控制(BC)设计控制器,反演算法中的虚拟及真实控制量都只使用已知状态与LESO观测的中间状态,避免使用不可测状态。此外,反演中还使用LESO估计的未知干扰进行补偿来提高控制器的鲁棒性。随后,基于lyapunov稳定性理论证明了整个闭环系统的稳定性。最后,将新方法与现有采用全状态反馈的IGC算法进行对比仿真。仿真结果表明,在不使用视线角速率与攻角的情况下,新方法依旧能够保证足够的拦截精度。
关键词:    部分状态反馈    观测器    非匹配干扰    反演法    制导控制一体化   
Partial States Feedback-Based Integrated Guidance and Control Design for Hypersonic Interceptor
Yang Wang, Zhou Jun
Institute of Precision Guidance and Control, Northwestern Polytechnical University, Xi'an 710072, China
Abstract:
For the integrated guidance and control (IGC) system of hypersonic interceptor with unmeasurable LOS angle rate and angle of attack, a novel controller based on partial states feedback is proposed. Firstly, the unmeasurable states and uncertainties are observered by a linear extended state observer (LESO). Then, a back-stepping controller is proposed for the IGC system. The proposed back-stepping controller not only use the estimated state to avoid using unmeasurable LOS angle rate and angle of attack, but also use the estimated uncertainties to enhance the robustness of IGC system. the closed loop system stability is proved by the Lyapunov theory. Simulation results demonstrate the the proposed method still can achieve enough small miss distance even if the LOS angle rate and angle of attack are unmeasurable.
Key words:    partial states feedback    observer    mismatched uncertainties    Back-stepping control    integrated guidance and control    angle of attack    backstepping    closed loop systems    controllers    Lyapunov function    Mach number   
收稿日期: 2017-02-12     修回日期:
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作者简介: 王洋(1989-),西北工业大学博士研究生,主要从事飞行器动力学与控制研究。
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