Investigation On Adaptive Roll Control Of A Canard-Controlled Hypersonic Vehicle

Hypersonic vehicle technology is an important research direction of a military power and combines frontier technology of multidisciplinary.This thesis,aiming at reducing the structural complexity and research cost of hypersonic vehicle and the rolling control process of canard configuration vehicle,researches and analysis rolling control method for hypersonic vehicle based on existing condition from engineering application perspective.Considering the uncertainty of the anti-effect of canard configuration aircraft,this thesis gets aerodynamic parameters parameter identification and judges anti-effect state.So this thesis studies parameter identification and controller design.Firstly,roll model of vehicle is built,and roll aerodynamic moment data and controllability of the model are analyzed by using experimental data.The basic law of moment coefficient and its derivative changes are obtained.Then the reason of anti-effect of vehicle are studied in theory.The effect of anti-effect on stability and control of vehicle are analyzed.The motion state of the given trajectory and controllability are analyzed.Results show that roll control can not be achieved in low rudder efficiency.Secondly,identification method of aircraft that has anti-effect and uncertainty are studied.According to roll movement frequency characteristic of vehicle,control input are designed and improves the precision and accuracy of parameter identification.The application and the principle of least square method,Kalman filtering and neural network algorithms in parameter identification are introduced.Based on the ballistic data of the vehicle,aerodynamic parameter identification investigation is carried out and the advantages and disadvantages are analyzed.At last,least square method is chosen to be online parameter identification to ensure the rate and accuracy of identification.Finally,the anti-effect control problem is analyzed and studied.PID controller is widely used in engineering practice.The traditional PID controller is designed and improved to overcome anti-effect state.The vehicle can adapt to different control moment coefficients and flight speed condition during flight.The parameters of PID controller are designed by selecting multiple trajectory characteristic points.The controller automatically adjust control gain of vehicle to meet control requirements of vehicle.The controller are analyzed when aerodynamic characteristics are known and unknown.Simulation results show that the controller can realize the roll control stability.In order to improve the validity of the designed controller further,backstepping controller is proposed and improved.The influence of parameter uncertainty on the performance of the control system are analyzed.Simulation results show that the uncertainty has little influence on vehicle.As a result,the backstepping method can achieve roll stability and has good control effect when the parameters are unknown.