Noninteracting control for helicopter in straight horizontal flight

Author

Koumboulis, F.N. ; Skarpetis, M.G. ; Griparis, M.K.

Author_Institution

Dept. of Mech. & Ind. Eng., Thessaly Univ., Volos, Greece

Volume

1

fYear

1998

fDate

1-4 Sep 1998

Firstpage

108

Abstract

Pitch angle and forward velocity are decoupled via a static state feedback law for the case of helicopter in straight horizontal flight. The set of stability derivatives for which decoupling is satisfied, is explicitly determined. The general analytic expression of the feedback controller, satisfying the decoupling design requirement, is derived. The necessary and sufficient conditions for decoupling and simultaneous stability are explicitly determined in terms of the stability derivatives of the helicopter. Simulation results are presented for vertical translation manoeuvre

Keywords

aerodynamics; aircraft control; attitude control; closed loop systems; helicopters; stability; state feedback; velocity control; closed loop systems; decoupling; forward velocity control; helicopter; necessary condition; noninteracting control; pitch angle control; stability; state feedback; straight horizontal flight; sufficient condition; Adaptive control; Aerodynamics; Blades; Computer industry; Helicopters; Industrial control; Propulsion; Stability; State feedback; Velocity control;

fLanguage

English

Publisher

ieee

Conference_Titel

Control Applications, 1998. Proceedings of the 1998 IEEE International Conference on

Conference_Location

Trieste

Print_ISBN

0-7803-4104-X

Type

conf

DOI

10.1109/CCA.1998.728254

Filename

728254