LQR lateral-directional control law design for distributed propulsion layout flying wing

Flying wing layout aircraft has abolished the horizontal tail and vertical tail which use the redundant multi control-surface configuration scheme. Usually, aircrafts that use large angle of the drag rudder to achieve its yaw operation, such as B-2, have a poor handling performance. Moreover, the existence of operational coupling leading to design the hybrid control law should be with the rudder and the aileron. In this paper, we propose a new type of distributed propulsion flyingwing unmanned aerial vehicle (UAV) scheme, and carried out its dynamic modeling and lateral-directional navigation decoupling. We analyzed the stability of the flying wing according to the state equation, and then designed and simulated the linear quadratic regulator (LQR) control law on this vehicle. The simulation results demonstrate that the proposed LQR controller distributed wing improves the control effect and increases the operation quality compared with the common flying wing which relies on cracked drag rudder.