DocumentCode :
2976144
Title :
A backstepping design for flight path angle control
Author :
Härkegård, Ola ; Glad, S. Torkel
Author_Institution :
Dept. of Electr. Eng., Linkoping Univ., Sweden
Volume :
4
fYear :
2000
fDate :
2000
Firstpage :
3570
Abstract :
A nonlinear approach to flight path angle control is presented. Using backstepping, a globally stabilizing control law is derived. Although the nonlinear nature of the lift force is considered, the pitching moment to be produced is only linear in the measured states. Thus, the resulting control law is much simpler than if feedback linearization had been used. The free parameters that spring from the backstepping design are used to achieve a desired linear behavior around the operating point
Keywords :
aircraft control; control system synthesis; feedback; linearisation techniques; nonlinear control systems; stability; backstepping design; globally stabilizing control law; nonlinear flight path angle control; nonlinear lift force; pitching moment; Aerospace control; Aircraft; Automatic control; Backstepping; Control nonlinearities; Control systems; Force measurement; Linear feedback control systems; Linear systems; Nonlinear dynamical systems;
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.2000.912259
Filename :
912259
Link To Document :
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