Application Convex Optimization Theory In Trajectory Optimization,Guidance And Control Of Missile

The modern war on the tactical missile weapon in high speed,high precision and long-range strike capabilities have become increasingly demanding,and the missile will become more and more information-based and intelligent because of diversification and complexity of the flight task.The design of missile guidance and control system will face many challenges.Missile flight environment changes dramatically,the flight range span,and attack from a single cooperative task is toward the direction of development,with adaptive flight control and trajectory planning ability has become the common requirements of the next generation of information missile.Therefore,this dissertation focuses on two aspects,that is,adaptive control of missile and rapid trajectory optimization.First of all,the mechanical model of missile is established according to the principle of rigid body kinematics and dynamics,and the model is simplified under certain assumptions.Then the dynamic model of the controlled object and the trajectory kinematics model using by trajectory optimization are established.Based on the robust gain scheduling method,the decoupling controller of missile is designed,and the effectiveness of the controller is verified by the real-time gain calculation of the convex optimization method.It provides a feasible basis for the trajectory optimization of the following tactical missile and the simplified research of multi constraint cooperative guidance.Secondly,in view of the robust and efficient characteristics of convex optimization algorithm,a trajectory optimization algorithm based on convex optimization method is studied.Through the convexity and discretization of the trajectory optimization problem,a sequence trajectory convex optimization algorithm which is equivalent to the original problem and has global optimality is obtained.The numerical results demonstrate the correctness and effectiveness of the algorithm;considering the disturbance in flight trajectory,a new deviation calculation method,on the basis of the design of robust gain scheduling controller of trajectory tracking.Simulation results show the effectiveness of the tracking controller and the superiority of the bias calculation method.Finally,based on the multi-constraint cooperative guidance problem,the distance of line of sight is taken as independent variable,so that the remaining flight time is considered as a new state.The optimization problem of guidance law with angle of fall,front angle and flight time constraint is solved by sequential convex optimization method,at the same time,the cooperative guidance simulation research under the "leader-follower" architecture is carried out.The numerical results show the validity and effectiveness of the proposed algorithm in the optimization of multi constrained cooperative guidance law.