S.M. Yang

This paper emphasizes on the influence of structure modal parameters to the performance of flight vehicle control surface systems. Structure modal parameters of a control surface includes the natural frequency. damping ratio, and mode shape. The control surface, modeled as a unif onn thickness plate, is mounted on a push-pull hydraulic actuator. The transfer function between the command signal and the sensor measurement signal is formulated. The transfer function includes the moment inertia of the control surface when considered rigid, actuator characteristics, and most importantly, a coupling term that governs the control surface rigid body rotation and flexible body vibration. The major advantages of the transfer function fonnulation are: (1) the order of the feedback system is reduced, (2) system identification of the control surf ace and actuator modal parameters from experimental results becomes more efficient, (3) the phase and gain margin of a close loop system can be tuned effectively by selecting the modal parameters of a flexible control surface, interaction of structure vibration and control can be minimized.

International Forum on Aeroelasticity and Structural Dynamics 1991, Aachen

Conference Paper

englisch

21,0 x 29,7 cm, 5 Seiten

DGLR-Bericht, 1991, 1991-06, International Forum on Aeroelasticity and Structural Dynamics 1991 Proceedings; S.524-528; 1991; Deutsche Gesellschaft für Luft- und Raumfahrt - Lilienthal-Oberth e.V., Bonn

NA

aeroelasticity

Bestellbar

1991