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 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 unmanned aerial vehicle longitudinal motion.
The paper examines a problem of observer-based flight control system design. The design procedure allows deriving both the observer and the controller simultaneously. The peculiarity of the proposed approach is that there is no need not need to choose the observer poles. The proposed design procedure is based on linear matrix inequalities technique. To demonstrate the efficiency of the proposed approach a longitudinal motion of unmanned aerial vehicle is used as a case study.
