Static output feedback control synthesis for Canard Rotor/Wing Aircraft

A new synthesis of static output feedback(SOR) for Canard Rotor/Wing Aircraft(CRW) is considered in this paper and the controller based on the novel theorems has less conservatism than the normal method. Moreover, the proposed approaches based on linear matrix inequality allow the output matrix of aircraft system not to be full row rank, which mean that the feedback controllers also can be used when the original system has sensor faults. Meanwhile, a synthesis combined with both robust performance and decay rate has been researched. The simulation results for CRW using the robust SOR controllers have illustrate their effectiveness.