Research Of Trajectory Optimization And Guidance Control Technology Of Hypersonic Gliding Missile

With the networking and integration of the missile defense system,there is a big challenge for missiles to penetrate the defense system.Hypersonic gliding missile is a new type of tactical weapon based on the concept of boost-glide ballistics and hypervelocity technology.It is of good aerodynamic characteristics and precision striking capability with long-range.It has become the key research topics in weaponry development and utilization department.In this paper,the booster-gliding aircraft with hypervelocity is taken as the research object,and some key problems in the optimization of overall parameters,trajectory optimization,H-V trajectory planning and guidance control technology are modeled,designed and simulated.The non-linear motion model of hypersonic gliding missile is established.The trajectory which consists of climbing stage,gliding stage and terminal stage is designed,and the corresponding guidance control system is constructed.The trajectory simulation is conducted based on the aerodynamic parameters and the thrust,then,the range,impact velocity and the maximum flight altitude of the missile is analyzed.Under the aerodynamic,structure and the designated trajectory form of the missile,the optimization problem of the take-off mass with multiple constraints is discussed.Considering the factors that have an important influence on the trajectory of the missile,the trajectory is parameterized.These parameters are regarded as the optimization variables and their ranges are set according to the actual flight situation of the missile.The penalty function method is used to construct the index function that is to minimize take-off mass under the consideration of the range and the final velocity requirement In order to improve the optimization speed,a dynamic proxy model of the missile trajectory is established based on Radial Basis Function neural network.The optimization problem of minimizing take-off mass is solved based on the dynamic proxy model,Maximin latin hypercube sampling method and genetic algorithm,and the optimal trajectory parameters and thrust scheme are obtained.Aiming at the trajectory design problem of the reentry section of the hypersonic gliding missile,considering the heat flux density,dynamic pressure,overload,Quasi equilibrium glide condition and so on,generating the reentry corridor.A glide section H-V trajectory is uniquely determined by the initial height of the gliding section under the premise of the initial velocity、the end velocity and height are given,deriving the roll angle command to realize the trajectory.Considering the requirement that satisfying the restraint of reentry corridor and avoiding singularity for the roll angle,we use the method of stepwise calculation to obtain the feasible area of the initial height of the gliding section and using it as the terminal constraint of the reentry initial stage trajectory design.A certain initial height of the feasible gliding section is obtained by the initial section design,and then the H-V trajectory and the roll angle command are obtained.The simulation results verify the effectiveness of the proposed method.Based on the Linear Quadratic Regulator(LQR)theory,designed a trajectory deviation feedback controller,realized the tracking of the H-V standard trajectory to the actual trajectory under various disturbances...