The Algorithm Research Based on Optimal Quadratic of Launch Control Law Access Time of Folding Wing UAV

Abstract

In order to solve the poor control problem in the launch control section of folding wing UAV, which is caused by the booster rocket step torque disturbance and wing rocket rotation torque disturbance, the optimal state control algorithm based on optimal quadratic is used to calculate the time range of the control law accessing flight control system, united in the simulation test, the precise time of the control law accessing flight control system to control the rudder finally is determined. Under the optimal control scheme, flight control system can overcome the oscillation in the shortest time and resume the steady state. Through the validation of simulation and experimental, the optimization algorithm makes the effects of the double torque disturbance be smaller, successfully solves the control problem of folding wing UAV during emission, and ensures the high quality of launch control and flight control of UAV.