Nonlinear hoc robust guidance law for homing missiles

Hsin Yuan Chen, Ciann-Dong Yang

研究成果: Conference contribution

3 引文 斯高帕斯(Scopus)

摘要

This paper proposes an H∞ robust guidance law for homing missiles with nonlinear kinematics in the homing phase. Unlike the conventional approaches where the trajectory of the target is often assumed to be known or needs to be estimated in real time, the proposed robust guidance law can achieve performance robustness in the absence of target's information and under the variations of the initial conditions of engagement. The most difficult and challenging task involved in applying the nonlinear H∞ control theory is the solution of the associated Hamilton-Jacobi Partial differential inequality (HJPDI). In this paper we show that the HJPDI of the missile guidance problem can be solved analytically with simple manipulations. The numerical simulations show that the H∞ robust guidance law exhibits strong robustness properties against the disturbances from target's maneuvers and the variations in initial engagement conditions.

原文English
主出版物標題Guidance, Navigation, and Control Conference and Exhibit
發行者American Institute of Aeronautics and Astronautics Inc, AIAA
頁面554-562
頁數9
出版狀態Published - 1998
事件Guidance, Navigation, and Control Conference and Exhibit, 1998 - Boston, United States
持續時間: 1998 8月 101998 8月 12

Other

OtherGuidance, Navigation, and Control Conference and Exhibit, 1998
國家/地區United States
城市Boston
期間98-08-1098-08-12

All Science Journal Classification (ASJC) codes

  • 航空工程
  • 控制與系統工程
  • 電氣與電子工程

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