Output feedback-based discrete-time sliding-mode controller design for model aircraft

被引：11
|
作者：
Chaudhuri, A [1 ]
Bhat, MS [1 ]
机构：
[1] Indian Inst Sci, Dept Aerosp Engn, Bangalore 560012, Karnataka, India
来源：
JOURNAL OF GUIDANCE CONTROL AND DYNAMICS | 2005年 / 28卷 / 01期
关键词：
D O I：
10.2514/1.9962
中图分类号：
V [航空、航天];
学科分类号：
08 ; 0825 ;
摘要：
A sliding-mode controller is designed for model aircraft with output feedback and dynamic compensation using a novel sliding function. The control law is derived for discrete-time implementation using the equivalent control approach for existence of a quasi-sliding mode. The matrices characterizing the switching surfaces are user-chosen and conditions are imposed on the system matrices. The algorithm is applied to design a pitch controller for an aircraft having controllable elevator and thrust deflections.
引用
收藏
页码：177 / 181
页数：5
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