Parameter Robust Flight Control System for a Flexible Aircraft

Abstract This paper discusses the design of a flight control system for a flexible aircraft, with significant coupling between flight mechanics and structural dynamics modes. Based on a longitudinal model, a normal acceleration control law is designed with a new synthesis technique, which is in fact a mixing of optimal control and eigenstructure assignment by means of constrained optimization. This technique is used to stabilize both rigid and elasic modes in an initial step, and to increase parameter robustness in the second.