基于终端角度约束的二阶滑模制导律设计

doi:10.7527/S1000-6893.2016.0162

电子电器工程与控制

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基于终端角度约束的二阶滑模制导律设计

郭建国¹, 韩拓¹, 周军¹, 王国庆²

1. 西北工业大学精确制导与控制研究所, 西安 710072;
2. 中国运载火箭技术研究院研发中心, 北京 100076

收稿日期:2016-03-09 修回日期:2016-05-26 出版日期:2017-02-15 发布日期:2016-06-02
通讯作者: 郭建国,E-mail:guojianguo@nwpu.edu.cn E-mail:guojianguo@nwpu.edu.cn
基金资助:
国家自然科学基金（61473226）

Second-order sliding-mode guidance law with impact angle constraint

GUO Jianguo¹, HAN Tuo¹, ZHOU Jun¹, WANG Guoqing²

1. Institute for Precise Guidance and Control, Northwestern Polytechnical University, Xi'an 710072, China;
2. Research and Development Center, China Academy of Launch Vehicle Technology, Beijing 100076, China

Received:2016-03-09 Revised:2016-05-26 Online:2017-02-15 Published:2016-06-02
Supported by:
National Natural Science Foundation of China (61473226)

摘要/Abstract

摘要：

针对空地导弹具有终端角度约束条件的制导律设计问题，提出了一种在有限时间内稳定的新型二阶滑模制导律。首先，在弹目相对运动学模型基础上，将终端弹道倾角约束转化为终端视线（LOS）角度约束，作为制导系统的终端控制目标。其次，通过选取一种新型二阶滑模面，结合螺旋控制算法的思想，设计了一种二阶滑模变结构制导律，来抑制系统中的不确定性因素，从而满足零化视线角速率和制导系统的终端角度约束条件的要求。采用一种新的Lyapunov函数，基于Lyapunov稳定性理论，严格证明了制导系统在有限时间内的稳定性。最后，对空地导弹制导系统进行数字仿真，通过和一阶传统滑模制导律以及基于超螺旋算法的二阶滑模制导律进行对比分析，验证了所设计的制导律在保证制导精度的同时，更能在有限时间内提高终端约束角度的精度，并且避免了超螺旋算法中参数选取较多的问题。

关键词: 二阶滑模, 制导律, 螺旋控制, 角度约束, 有限时间稳定

Abstract:

A new second-order sliding-mode guidance law with finite time stability is proposed for the design of the guidance law for the air-surface missile with impact angle constraint. Based on the relative motion model of the missile and the target, the terminal trajectory inclination angle constraint is transformed to the terminal line of sight (LOS) angle constraint, which is taken as the terminal control goal of the guidance system. In order to satisfy the annihilation of LOS rate and the terminal angle constraint, a second-order sliding mode guidance law is designed by using a new second-order sliding mode surface with twisting control algorithm, which is used to suppress the uncertainty of guiding system. Based on the Lyapunov stability theory, a new Lyapunov function is adopted to verify the strict stability of the guidance system in finite time. The air-surface missile guidance system is simulated numerically. A comparison with the conventional sliding mode guidance law and a second-order sliding mode guidance law using super twisting algorithm shows that the method proposed in this paper can improve the accuracy of terminal angle constraint in finite time and avoid the problem of too many parameters in the super twisting algorithm, and can guarantee the guidance accuracy at the same time.

Key words: second-order sliding-mode, guidance law, twisting control, angle constraint, finite time stability

中图分类号:

V488.133

郭建国, 韩拓, 周军, 王国庆. 基于终端角度约束的二阶滑模制导律设计[J]. 航空学报, 2017, 38(2): 320208-320217.

GUO Jianguo, HAN Tuo, ZHOU Jun, WANG Guoqing. Second-order sliding-mode guidance law with impact angle constraint[J]. ACTA AERONAUTICAET ASTRONAUTICA SINICA, 2017, 38(2): 320208-320217.

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E-mail：hkxb@buaa.edu.cn

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主管单位：中国科学技术协会主办单位：中国航空学会北京航空航天大学

基于终端角度约束的二阶滑模制导律设计

Second-order sliding-mode guidance law with impact angle constraint

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