Title :
An LFT approach to autopilot design for missiles
Author :
Huang, Yun ; Lu, Wei-Min
Author_Institution :
Dept. of Electr. Eng., California Inst. of Technol., Pasadena, CA, USA
Abstract :
In this paper, a tailfin-controlled missile system is described in terms of a linear fractional transformation (LFT) on an uncertainty/frequency block. The aerodynamical nonlinearities are taken as deviations to the nominal linear model and are treated as uncertainties. A state feedback robust controller is obtained by solving some linear matrix inequalities. The simulation results show that the designed autopilot is able to track the acceleration command, hence achieving the robust performance requirements
Keywords :
aerodynamics; control system synthesis; matrix algebra; missile guidance; robust control; state feedback; transforms; uncertain systems; acceleration command; aerodynamical nonlinearities; autopilot design; linear fractional transformation; linear matrix inequalities; robust controller; state feedback; tailfin-controlled missile system; uncertainty/frequency block; Control system synthesis; Frequency; Linear feedback control systems; Linear systems; Missiles; Robust control; Robust stability; Rockets; State feedback; Uncertainty;
Conference_Titel :
American Control Conference, Proceedings of the 1995
Conference_Location :
Seattle, WA
Print_ISBN :
0-7803-2445-5
DOI :
10.1109/ACC.1995.532061
