Research On The Attitide Stabilization And Control Of The MIRV Under The Condition Of Large Centroid Shifting Disturbance

As a symbol of the nuclear deterrent,the Multiple Independently Targeted Reentry Vehicle(MIRV)missile,as the main form of the ballistic missiles,has received considerable attention from all over the world.Due to the large centroid shifting disturbance,the MIRV missile has the characteristics of strong coupling and nonlinearity while splitting the sub-warheads.Therefore,the control of the MIRV is of vital importance to the missile.Besides,while the MIRV missile is taking the mission,the PBV would has the possibility of being affected by the internal and external bounded uncertainty and the interference.All these factors would bring tremendous challenges to the control of the MIRV missile's attitude.Taking the MIRV missile as the research object,this dissertation focuses on the attitude control system design,which using the Reaction Control System(RCS)as the control mechanism,mainly based on the nonlinear dynamic inverse control(NDIC)and the neural network control(NNC).The main research and work are as follows:1.The establishment of the MIRV missile's model.Establishing the model of the MIRV missile aiming at the large centroid shifting disturbance problem.Analyzing the effect of the PBV's execution mechanism to the operation of the missile.Derivating the formulas of the MIRV missile's attitude dynamics and kinematics.Analyzing and verifying the neural network's approximation property for the nonlinear function.2.The analysis of the dynamic inverse control of the MIRV missile's PBV.Analyzing the PBV's internal and external uncertainty together with the usage of the dynamic inverse method;Establishing the control circuit suitable for the PBV,Derivate the dynamic inverse control law based on the Euler angle and the quaternion.Aiming at the disturbance cause by the large centroid shifting problem together with the effect of the external disturbance and the noise conditions,use the dynamic inverse method to tackle the control problem of the PBV and conduct the numerical simulation.3.The analysis of the neural network based adaptive dynamic inverse control of the MIRV missile's PBV.Analyzing the method of the neural network based adaptive dynamic inverse control together with the inverse structure of the neural network and its inverse identification.Moreover,derivating the compensated formulas of the neural network based adaptive dynamic inverse errors.Aiming at the MIRV missile's PBV,design the controller take use of the neural network based adaptive dynamic inverse control method,moreover,design the off-line neural network(off-line NN)controller and deduce formulas of the online adaptive neural network(on-line NN).Aiming at the PBV's three-channel attitude controller,conduct the numerical simulation using the off-line neural network(NN1)based dynamic inverse controller(NDI-PWPF),then verify the proposed adaptive neural network(NN2)based dynamic inverse controller(ANDI-PWPF)by another set of numerical simulating and comparing.