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
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;
Conference_Titel :
American Control Conference, 1993
Conference_Location :
San Francisco, CA, USA
Print_ISBN :
0-7803-0860-3
