Optimal flight control system design via LMIs

摘要

The problem of optimal state feedback controller design in terms of quadratic performance index is considered. The problem is formulated in the form of linear matrix inequalities (LMIs). The obtained solution guarantees stabilization of the aircraft during flight mission. During flight envelope the aircraft is subjected to the external stochastic disturbances. The efficiency of the proposed approach is illustrated by a case study of airplane longitudinal motion.