Nonlinear H-infinity optimal control for agile missiles

被引：14
|
作者：
Wise, KA [1 ]
Sedwick, JL [1 ]
机构：
[1] SO ILLINOIS UNIV,EDWARDSVILLE,IL 62026
来源：
JOURNAL OF GUIDANCE CONTROL AND DYNAMICS | 1996年 / 19卷 / 01期
关键词：
D O I：
10.2514/3.21593
中图分类号：
V [航空、航天];
学科分类号：
08 ; 0825 ;
摘要：
Nonlinear H-infinity optimal control is used to design a pitch plane flight control system for a high-angle-of-attack agile missile. The nonlinear H-infinity control law is obtained by approximating the solution to the Hamilton-Jacobi-Isaacs equation, The solution to the partial differential equation is formed using the method of characteristics and is numerically approximated using successive approximations, Nonlinear simulation results using the nonlinear control law are presented, Simulation results testing the algorithms demonstrated excellent performance.
引用
收藏
页码：157 / 165
页数：9
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