Rotary gust rejection for helicopters

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

103

Abstract

For the case of helicopters in straight horizontal flight, the effects of a rotary gust to the forward velocity and the downward velocity of the helicopter are rejected. The rotor commands appear to be independent, i.e. to be enough to control the dynamics of the horizontal and vertical motion. In this case, the rotary gust rejection problem is proved to be always solvable, via a state feedback law. The general analytic expression of the feedback controller, satisfying the disturbance rejection design requirement, is derived. The necessary and sufficient conditions for disturbance rejection and simultaneous stability are established. Simulation results are derived for an SA-330 PUMA helicopter

Keywords

aerodynamics; aircraft control; closed loop systems; helicopters; stability; state feedback; transfer functions; SA-330 PUMA; disturbance rejection; dynamics; helicopters; necessary condition; rotary gust rejection; stability; state feedback; sufficient condition; Aerodynamics; Blades; Computer industry; Helicopters; Motion control; Nonlinear equations; Propulsion; Stability; State feedback; Sufficient conditions;

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.1998.728253

Filename

728253