DocumentCode
490120
Title
Flight Control Design By Nonlinear Servomechanism Theory
Author
Huang, J. ; Lin, C.F.
Author_Institution
American GNC Corporation, 9131 Mason Ave., Chatsworth, CA 91311
fYear
1993
fDate
2-4 June 1993
Firstpage
410
Lastpage
414
Abstract
A new approach to the high performance missile autopilot design based on the nonlinear servomechanism theory is proposed. This approach coupled with the analytic gain scheduling leads to an effective means to account for the nonlinearity and uncertainty in the missile system.
Keywords
Aerospace control; Control systems; Couplings; Missiles; Performance gain; Robustness; Scheduling; Servomechanisms; State feedback; Uncertainty;
fLanguage
English
Publisher
ieee
Conference_Titel
American Control Conference, 1993
Conference_Location
San Francisco, CA, USA
Print_ISBN
0-7803-0860-3
Type
conf
Filename
4792885
Link To Document