Static Output Feedback Design to Achieve Phase Stabilization of Bending Mode

Abstract

The quadratic optimal output feedback solution is found by iteratively satisfying the equations arising from the necessary condition for optimality. A simple, suboptimal solution is derived from the necessary condition which offers acceptable solution without any iterations. This is applied to design a pitch acceleration tracking autopilot for a flexible missile employing wing and tail as two independent control surfaces. It is shown that a matrix of static gains alone, apart from meeting the other design specifications, phase stabilizes the first bending mode and gain stabilizes higher bending modes.