Flying-Wing UAV Landing Control and Simulation Based on Mixed H2/H∞

A flying-wing unmanned aerial vehicle (UAV) landing control problem is studied in this paper, considering the influence of both actual ground effect and atmospheric disturbances. The atmospheric disturbances are the major exterior disturbances for the UAV, and the ground effect imposes extra deviations to aerodynamic parameters. A controller obtained from mixed H
₂
/H
_infin
robust control technique is employed to insure the UAV tracks the desired landing trajectory with preferable qualities, even under the influence of uncertainties and disturbances. A conventional controller designed using the classical root locus and bode diagram design method is mentioned either. The two controllers are compared through nonlinear numerical flight simulation. The results indicate that the controller obtained from mixed H
₂
/H
_infin
technique provides excellent performance and robustness characteristics than the classical one, especially under the influence of ground effect and atmospheric disturbances.