Adaptive Multi-dimensional Taylor Network Filtering And Control For Launch Vehicle Flight

Launch vehicle is an important vehicle for space exploration,satellite launch and manned space flight in China.Currently,with the development of space exploration and the diversification of space missions,the development of a new generation of launch vehicle is imminent.Compared with the traditional launch vehicle,the new generation of launch vehicle has the advantages of light weight,high carrying capacity,more slender structure,and usually uses multiple booster engines and core engines in parallel,such as strap-on rocket,heavy launch vehicle,which makes the dynamic characteristics of the rocket body more complex and bigger influenced by parameter uncertainties and strong rigid-elastic coupling.Therefore,the conventional PD control has been difficult to meet the requirements of the stability and dynamic performance of our new generation of launch vehicle attitude control.In this thesis,the application of adaptive multi-dimensional Taylor network controller in the attitude control system of launch vehicle is proposed,which provides a way to design new generation of launch vehicle attitude control methods.The main content of this thesis includes:Firstly,the commonly used launch vehicle attitude control methods at home and abroad are introduced,and the trend of the new generation of launch vehicle attitude control methods are analyzed.Then,according to Newton’s second law and moment of momentum theorem,the rigid body motion model of launch vehicle is established,and the six degree of freedom motion equations and elastic vibration equations are established by analyzing the force and moment of launch vehicle.The nonlinear model of launch vehicle is linearized with small disturbance,and the PD correction network control system is designed based on the linearized model,the particle swarm optimization algorithm is used to optimize the PD parameters.Aiming at the problems that PD controller can not solve the parameter uncertainties and aerodynamic parameter perturbation in the flight process of launch vehicle,the model reference adaptive control(MRAC)control scheme are designed,the adaptive gain control algorithm is designed to adjust gain on line,and the adaptive output and PD output are combined to act on the rocket body to improve the robustness of the attitude control system.The simulation results show that MRAC controller can improve the adaptability of the control system to parameter uncertainties and improve the performance of the controller.In order to slove the problems of the large errors of model parameters,large disturbance of external environment and fast time-varying,an adaptive multi-dimension Taylor network control structure based on backstepping is proposed,the dynamic performance,robustness and anti-interference ability of launch vehicle can be improved by using the high order term of adaptive multi-dimensional Taylor network controller,and the Lyapunov function is constructed to prove the stability of controller.In view of the deviation between the actual elastic vibration frequency and the elastic vibration frequency obtained by the test,the correction network cannot effectively filter.Based on Lyapunov theory,an adaptive multi dimension Taylor network filter is designed,and the convergence and stability of the adaptive multi-dimensional Taylor network filter are proved.Finally,Matlab is used to simulate the first stage boost flight of the launch vehicle attitude control.Three controllers are all optimized by particle swarm optimization to get the initial parameters,then by comparing the control effects of three control structures,PD correction network control,model reference adaptive control and adaptive multi-dimensional Taylor network control,under different conditions,the following conclusions are verified:adaptive multidimensional Taylor network controller can effectively suppress the influence of elastic vibration frequency error;adaptive multidimensional Taylor network controller can solve the problem of fast time-varying of linear system,and Compared with PD controller which is designed at fixed point,the workload of adaptive MTN controller is reduced greatly;improving the tracking accuracy of the attitude control system.the influence of parameter deviation such as thrust error and aerodynamic perturbation is restrained,and the robustness of control system is enhanced;the attitude angle stability error is reduced.The simulation results show that the adaptive multi-dimensional Taylor network control structure can achieve the above control effects.