Control Of A Folding Wing Aircraft During Deformation

Compared with the fixed aerodynamic characteristics of conventional aircraft,the morphing aircraft can change the wing structure according to the changes of the flight environment and mission objectives,and ensure the excellent flight performance of the aircraft.In recent years,with the deep research on the morphing aircraft,the aerodynamic characteristics and modeling methods of the morphing aircraft have made significant progress.Considering the time-varying characteristics of aerodynamic parameters and the nonlinear characteristics of the system model,the study for the control of the morphing aircraft is not yet thorough.In this paper,the control of a kind of the folding wing aircraft is studied by using the wing deformation to change the aerodynamic performance of the aircraft.First,the aerodynamic parameters modeling and nonlinear dynamic modeling of the folding wing aircraft are studied.The aerodynamic parameters of the aircraft are calculated by the software of aerodynamic simulation DATCOM,and the aerodynamic function model containing the folding deformation parameters is obtained by fitting.The motion characteristics of folding wing aircraft are analyzed,and the nonlinear motion equation including deformation parameters is established.The response characteristics of the folding wing vehicle under no condition are simulated and analyzed.Secondly,a longitudinal linear variable parameter model indicating the motion characteristics with the change of the folding parameters is established for the nonlinear motion equations of the folding wing aircraft.Based on the LPV model of the aircraft,a robust variable gain control method based on the affine parameter dependent Lyapunov function is proposed for the design of a stabilizing controller for a folding wing aircraft with no complex interference,simulation verifies the reliability and superiority of the control method,and analyzes the influence of wing folding on flight performance.Finally,the auxiliary maneuvering problem of folding wing aircraft is studied,a model of folding wing aircraft with folding auxiliary maneuver is established,and a flight controller is designed.A non singular dynamic terminal sliding mode controller(NDTSMC)based on feedback linearization is designed by using the change of folding angle as an additional control input.The attitude tracking simulation results show that the folding assisted maneuverable folding wing aircraft has better maneuverability and anti-interference ability than the traditional aircraft.