Robust landing control and simulation for flying wing UAV

The object of this paper is to design a robust longitudinal landing controller for a flying wing UAV, taking into account both actual ground effect and some typical atmospheric conditions. In order to track the desired trajectory even when the UAV is under influence of uncertainties and disturbances, a mixed H₂ZH_∞ robust control method is adopted in this paper. The H₂ part is to meet excellent dynamic responds; the H_∞ part is to minimize the affection of the disturbance to the performance output. The feedback control gain involved in the method is derived by linear matrix inequality (LMI) approach. Finally, the robust controller derived from this paper is simulated by a nonlinear numerical flight simulator, the results compared to those of classical PID controller show that, the robust landing controller can meet the performances better.