Y. Okuno, K. Kawachi

Optimal control of tiltrotor aircraft following power failure was theoretically studied using nonlinear optimal control theory. Optimization of the various takeoff procedures, i.e., vertical, running, and oblique takeoffs in either a helicopter or conversion mode showed distinct advantages in increasing the maximum takeoff weight and/or decreasing the minimum takeoff distance, especially when applying variable critical decision speeds according to the takeoff field configuration. Optimal control procedures for landing and continued flight following power failure are also discussed with emphasis on the effects of nacelle angle control. The analytical method proposed in this paper is expected to contribute to more efficient use of tiltrotor aircraft in powered-lift transport category operations, and also considered to markedly reduce the cost, time, and risks involved in certification flight tests.

17th European Rotorcraft Forum 1991, Berlin

Conference Paper

englisch

21,0 x 29,7 cm, 10 Seiten

DGLR-Bericht, 1991, 1991-08, 17th European Rotorcraft Forum Proceedings; S.233-242; 1991; Deutsche Gesellschaft für Luft- und Raumfahrt - Lilienthal-Oberth e.V., Bonn

NA

aircraft control, failure, tilt rotor aircraft

Bestellbar

1991