Flight control system design via static output feedback: LMI-approach

Abstract

A contemporary approach of flight control system design via static output feedback design is proposed. The static output feedback is formulated in terms of linear matrix inequalities. The obtained solution guarantees stabilization of unmanned aerial vehicle (UAV) during flight mission. During flight envelope the unmanned aerial vehicle is subjected to the external stochastic disturbances. The efficiency of the proposed approach is illustrated by a case study of UAV longitudinal motion.