CONTROL OF ROLL MOMENT BY MEMS

Abstract

In this paper, we will illustrate that the motion of a delta wing can be controlled by actuators fabricated by micromachining technology, if the size of the micro-actuator matches the thickness of the thin boundary layer at the leading edge of the delta wing. This match provides a coupling between the micro actuator and the flow instability which serves as an effective amplifier of the artificial disturbances. The distributed micro-actuators perturb the flow and break the symmetry of the two leading edge separation vortices such that a torque is obtained.