Design of transition state flight control law for quad tiltrotor
The transition state flight control law of quad tiltrotor was designed and studied.Firstly,a complete control law for tilting transition corridor dynamic flight of a quad tiltrotor aircraft was de-signed by combining the sliding mode theory and disturbance observer,and the robustness of the sliding mode control method was used to achieve the estimation of aerodynamic interference for the whole aircraft,and the precise aerodynamic interference effect in the time domain simulation envi-ronment was simulated.Then,the tilting angle was used as the weight factors of the rotor controller and the fixed wing controller for manoeuverability allocation.The fixed height flight control in transi-tion mode for linear and sinusoidal tilting angle curves was completed,and the state quantity in tran-sition mode of the aircraft for two curves was compared.Finally,the simulation validation was con-ducted.The results show that the designed controller demonstrates a good dynamic performance,a fast response speedand a strong robustness,ensuring a good altitude stability of the quad tiltrotor in transition states.
quad tiltrotortransition statecontrol law designsliding mode controldisturbance ob-server
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