2次元翼のアクティブ・フラッタ・サプレッション(第3報)

前縁操縦翼面制御の効果

抄録

As a method of active flutter suppression, controlling a leading-edge control surface is analytically studied for a two-dimensional wing in the use of the oscillating incompressible aerodynamic force. Four quantities, i.e. rotation and translation of the wing and their velocities, are fedback so as to move the leading-edge control surface. The control law proportional to wing rotation is most effective in flutter suppression independently of the location of the center of gravity. Therefore this feed-back system is only one method of flutter suppression in the case where the center of gravity is behind a certain point, for example, 45% chord. The mechanism of the present flutter suppression is clearly explained by an approximate analysis in the use of the steady aerodynamic force.