A Method for Applying Linear Optimal Control Theory to the Design of a Regulator for a Flexible Aircraft

摘要

A hypothetical control system that provides improved rigid body and structural mode damping of a flexible aircraft in order to improve the riding quality and minimize the wing bending moment during flight in turbulence, is considered. The equations of motion are related to a high performance fighter aircraft with external stores. The feedback gains are determined, using linear optimal control theory. A quadratic optimization criterion, taking into account the normal acceleration at the pilot seat and the wing root bending moment, is used. A number of optimal and suboptimal regulators are calculated. The system performance is expressed in terms of pole location, frequency response, and power spectra for both pilot seat acceleration and wing root bending moment. Aircraft response to a deterministic gust disturbance is presented.