| 应对机动目标的全捷联导弹制导控制一体化设计 |
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| 引用本文： | 赵斌,朱传祥,徐思勇,蒋瑞民,张琳,周军.应对机动目标的全捷联导弹制导控制一体化设计[J].宇航学报,2019,40(3):310-319. |
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| 作者姓名： | 赵斌 朱传祥 徐思勇 蒋瑞民 张琳 周军 |
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| 作者单位： | 1. 西北工业大学精确制导与控制研究所，西安 710072；2. 西北工业大学机电学院，西安 710072；
3. 中国运载火箭研究院首都航天机械公司，北京 100076 |
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| 基金项目： | 国家自然科学基金（61703339） |
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| 摘 要： | 针对全捷联导引头探测器与弹体固连带来的视线(LOS)测量与弹体姿态的耦合问题，基于干扰观测器和动态面控制提出一种考虑全捷联视线角(FOV)约束的制导控制一体化(IGC)设计方法。首先建立起具有严格状态反馈形式的全捷联制导控制一体化设计模型；其次，针对目标机动和气动扰动带来的模型不确定，设计了一种非线性干扰观测器对其进行在线估计，并将其估计信息的平方引入设计过程；第三，针对全捷联模式下有限视场角凸显的状态约束问题，基于积分型障碍Lyapunov函数与动态面控制设计了一体化制导控制规律，并对闭环系统的稳定性和信号的一致有界特性进行了证明。仿真结果表明,在目标进行不同类型机动和气动扰动存在的条件下，所设计方法均能保证制导精度以及视场角满足约束条件。
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| 关 键 词： | 状态约束 干扰观测器 制导控制一体化 全捷联 |
| 收稿时间： | 2018-05-21 |
IGC Design for Missile with Strapdown Seeker Against Maneuvering Target |
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| ZHAO Bin,ZHU Chuan xiang,XU Si yong,JIANG Rui min,ZHANG Lin,ZHOU Jun.IGC Design for Missile with Strapdown Seeker Against Maneuvering Target[J].Journal of Astronautics,2019,40(3):310-319. |
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| Authors: | ZHAO Bin ZHU Chuan xiang XU Si yong JIANG Rui min ZHANG Lin ZHOU Jun |
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| Affiliation: | 1. Institute of Precision Guidance and Control, Northwestern Polytechnical University, Xi’an 710072, China; 2. School of Mechanical Engineering, Northwestern Polytechnical University, Xi’an 710072, China; 3. Capital Aerospace Machinery Company, China Academy of Launch Vehicle Technology, Beijing 100076, China |
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| Abstract: | Aiming at the coupling problem of the line-of-sight (LOS) measurement and missile attitude caused by the connection of the strap-down seeker and the missile body, a novel integrated guidance and control (IGC) method considering the field-of-view (FOV) angle constraint of the strap-down seeker is proposed based on the disturbance observer and the dynamic surface control theory. Firstly, the strict feedback state equation for the IGC design with FOV angle constraint is built. Secondly, a nonlinear disturbance observer is designed to estimate the model uncertainties which include the target maneuvering and the aerodynamic parameter disturbance, and the square of the estimation results are employed to the IGC design. Thirdly, the FOV constraint issue is handled based on the integral barrier Lyapunov function and the dynamic surface control, and the proof of the stability of the closed system and the uniform ultimately boundedness of the signals is also carried out using the Lyapunov theorem. The simulation results imply that the proposed IGC law can not only ensure the interception accuracy, but also satisfy the FOV angle constraint in the presence of different target maneuvering and the aerodynamic parameter disturbance. |
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| Keywords: | State constraint Disturbance observer Integrated guidance and control Strap-down |
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