DocumentCode
2976214
Title
Design of a STT missile autopilot using functional inversion and LMI approach
Author
Song, Seong-Ho ; Lee, Sang-Yong ; Jeom-Keun Kim ; Moon, Gyu ; Hyeong Park, Seop ; Yong Kim, Sun
Author_Institution
Dept. of Inf. & Commun. Eng., Hallym Univ., Chunchon, South Korea
Volume
4
fYear
2000
fDate
2000
Firstpage
3596
Abstract
We present a systematic approach for the autopilot design of skid-to-turn (STT) missiles. First, the nonlinear model of a STT missile is partially linearized via functional inversion techniques and then, the additional set-point tracking controller can be designed by the well-known LMI approach. The stabilization conditions are given in terms of LMIs
Keywords
control system synthesis; dynamics; linearisation techniques; matrix algebra; missile control; nonlinear differential equations; LMI approach; autopilot design; functional inversion; linear matrix inequalities; nonlinear model; set-point tracking controller; skid-to-turn missiles; stabilization conditions; Acceleration; Aerodynamics; Communication system control; Linear matrix inequalities; Missiles; Nonlinear control systems; Output feedback; Stability; Sun; Table lookup;
fLanguage
English
Publisher
ieee
Conference_Titel
Decision and Control, 2000. Proceedings of the 39th IEEE Conference on
Conference_Location
Sydney, NSW
ISSN
0191-2216
Print_ISBN
0-7803-6638-7
Type
conf
DOI
10.1109/CDC.2000.912264
Filename
912264
Link To Document