75 / 2017-08-31 10:17:14

Modeling and Integrated Control Design for Folding-wing Aircraft during Morphing Process

folding-wing aircraft; robustness; sliding mode control; PID control

The dynamic modeling and the robust control design for the folding-wing aircraft in flight during the morphing process are studied. The multibody dynamic equations of the morphing aircraft derived from Newtonian mechanics clearly demonstrate the effects of wing folding on the aircraft dynamics. Considering that the uncertainty of aerodynamic model exists in the moment parameters of the fast loop, an integrated control method based on sliding mode control and PID control is proposed. Sliding mode control is used to design the fast loop controller that requires strong robustness. In addition, PID control is used to design the slow loop controller whose mathematical models are relatively accurate. Close-loop simulation of the integrated control system of the folding-wing aircraft is carried out and the simulation results show that the integrated control design based on sliding mode control and PID control ensures that the folding-wing aircraft transits smoothly from the unfolded configuration to the folded configuration and satisfy the requirements of the control system for robustness.