Trajectory Simulation And Optimization Of The Ballistic Missile

Since the German V-2 Rocket during the Second World War came to the world, as strategic weapons, ballistic missiles are thought much of by many countries for its huge execution and determent, so development, improvement and production of ballistic missiles never stop. The simulation and optimization of trajectories of ballistic missiles are important parts of collectivity design, and appear in every stage of development of ballistic missiles. The same missile with different trajectories will have different flight performance. To carry out sufficient technical performance of ballistic missiles, optimizations of trajectories of ballistic missiles will be needed. This thesis is focused on the simulation and optimization of ballistic missile trajectory. The main tasks include:1) Build submodels for trajectory simulation in the Matlab/Simulink integrated environment. Submodels include: coordinate transform, gravity, engine, standard atmosphere, flight program etc. Present Motion Equations of passive flight phase, free flight phase and reentry flight phase. A two-stage ballistic missile are used for validate correctness of the model and analyze the factor which affect the range.2) Introduce nonlinear parameter optimization methods, include: one dimension search method, unconstrained nonlinear optimization method and constrained nonlinear optimization method. SWIFT, SQP and GA are described more detail. GA has the property of global convergence and less sensitivity on initial values, but elapse much longer time. Write optimization programs, which include Descent, Hooke-Jeeves, Nelder-Mead, BFGS etc. Results of the test of these programs are presented.3) Discuss the way of solving trajectory optimization problem using parameter optimization methods. The problem can transfer to the design of flight pitch angle, which is discussed detail in this thesis. Through select several special parameters of flight program, parameter optimization problem comes out. Considering multiple constrains, mathematical model and simulation model are built.4) SWIFT, SQP, GA are carried on V2 rocket for maximum range optimization. These methods are used for a two-stage ballistic missile for both maximum range optimization and minimum dispersion optimization. Results are presented with figures and tables.5) Summarize main work and contribution and unfinished work.