J.V.R. Prasad, D.P. Schrage

This paper considers synthesis of a helicopter full authority flight controller using approximate inversion of the nonlinear model of the vehicle. Based on the natural time scale separation between position and attitude dynamics of the vehicle, the vehicle attitudes are treated as pseudo-command variables. In order to simplify the controller, approximations to the body axes forces are used in the controller calculations. The first approximation involves neglecting the cyclic and pedal control force terms and the second approximation involves neglecting the body x- and y-axis force components in the controller calculations. The adequacy of these approximations and the performance of the resulting controller in executing an elliptical turn maneuver are evaluated through nonlinear simulation.

17th European Rotorcraft Forum 1991, Berlin

Conference Paper

englisch

21,0 x 29,7 cm, 14 Seiten

DGLR-Bericht, 1991, 1991-08, 17th European Rotorcraft Forum Proceedings; 1991; Deutsche Gesellschaft für Luft- und Raumfahrt - Lilienthal-Oberth e.V., Bonn

NA

Dieser Aufsatz ist nicht Teil der Veröffentlichung!

flight control, helicopters

Bestellbar

1991