Approximate decoupling flight control design with output feedback

被引：0
|
作者：
Park, S [1 ]
Nagati, MG [1 ]
机构：
[1] WICHITA STATE UNIV, DEPT AEROSP ENGN, WICHITA, KS 67260 USA
来源：
JOURNAL OF GUIDANCE CONTROL AND DYNAMICS | 1997年 / 20卷 / 05期
关键词：
D O I：
10.2514/2.4163
中图分类号：
V [航空、航天];
学科分类号：
08 ; 0825 ;
摘要：
The problem of approximate decoupling of nonlinear systems by output feedback is considered. The structure of the controller is high-gain proportional plus integral. Linearization of the nonIinear closed-loop equations results in the standard singular perturbation form. Based on the singular perturbation concept, a control law is found that accomplishes approximate decoupling with stability for nonlinear systems. Application of the proposed design scheme to the full six-degree-of-freedom nonlinear aircraft dynamics model is presented, demonstrating its validity.
引用
收藏
页码：897 / 902
页数：6
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