Adaptive output feedback for high-bandwidth flight control

被引:19
作者
Kim, N
Calise, AJ
Hovakimyan, N
Prasad, JVR
Corban, E
机构
[1] Georgia Inst Technol, Sch Aerosp Engn, Atlanta, GA 30332 USA
[2] Guided Syst Technol Inc, McDonough, GA 30253 USA
关键词
D O I
10.2514/2.4985
中图分类号
V [航空、航天];
学科分类号
08 ; 0825 ;
摘要
A novel adaptive output feedback approach for high-bandwidth flight-control system design is introduced. The approach permits adaptation to both parametric uncertainty and unmodeled dynamics. Of particular interest here is the interaction with poorly modeled high-frequency dynamics. An approximate output feedback linearizing controller is augmented with a neural network. Adaptation is achieved using input/output sequences of the uncertain system. Actuation limits and time delays are also addressed. The approach is illustrated by the design of a pitch-angle flight-control system for a linearized model of an R-50 experimental helicopter.
引用
收藏
页码:993 / 1002
页数:10
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