大落角机动目标逆轨拦截最优滑模制导律设计

doi:10.12305/j.issn.1001-506X.2022.09.23

Abstract

Abstract:

Aiming at the problem that it is difficult to intercept maneuvering targets with large angles of fall in air defense, the optimal control theory is used to design an optimal guidance law with attack angle constraints, and combined with variable structure control theory, an optimal sliding mode guidance law with attack angle constraints is designed. Considering that the target trajectory inclination is usually difficult to measure, the extended states observer is used to estimate the target trajectory inclination. Based on the Lyapunov stability theory, the optimal sliding mode guidance law is analyzed, and the parameter change function that can ensure the stability of the system is designed. The simulation results show that when the target is maneuvering with acceleration, the optimal sliding mode guidance law can hit the target with the expected angle of attack and a small miss distance. The command changes during the guidance process are relatively stable, and it has strong robustness to the acceleration maneuver of the target.

Key words: head-on interception, optimal sliding mode guidance law, extended states observer (ESO), impact angle constraint

CLC Number:

TJ765.3

Mengping ZHOU, Xiuyun MENG, Junhui LIU. Design of optimal sliding mode guidance law for head-on interception of maneuvering targets with large angle of fall[J]. Systems Engineering and Electronics, 2022, 44(9): 2886-2893.

Figures/Tables 12

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References 30

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制导律	脱靶量/m	弹道倾角/(°)
最优滑模制导律	0.209 1	69.619 3
滑模制导律	0.332 4	69.617 1
最优制导律	0.933 7	69.760 7

制导律	脱靶量/m	偏差角/(°)
最优滑模制导律	0.171 0	0.130 9
滑模制导律	0.499 1	0.108 2
最优制导律	1.860 7	-0.959 6

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Design of optimal sliding mode guidance law for head-on interception of maneuvering targets with large angle of fall

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