DocumentCode
2308217
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
Volume
5
fYear
1995
fDate
21-23 Jun 1995
Firstpage
2990
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;
fLanguage
English
Publisher
ieee
Conference_Titel
American Control Conference, Proceedings of the 1995
Conference_Location
Seattle, WA
Print_ISBN
0-7803-2445-5
Type
conf
DOI
10.1109/ACC.1995.532061
Filename
532061
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