Development and Application of an Optimization Procedure for Flutter Suppression Using the Aerodynamic Energy Concept

摘要

An optimization procedure is developed based on the responses of a system to continuous gust inputs. The procedure uses control law transfer functions which have been partially determined by using the relaxed aerodynamic energy approach. The optimization procedure yields a flutter suppression system which minimizes control surface activity in a gust environment. The procedure is applied to wing flutter of a drone aircraft to demonstrate a 44-percent increase in the basic wing flutter dynamic pressure. It is shown that a trailing-edge control system suppresses the flutter instability over a wide range of subsonic Mach numbers and flight altitudes. Results of this study confirm the effectiveness of the relaxed energy approach.