Studies Of Terminal Guidance Law And Combined Control For Missile Intercepting

The combined control with blended lateral jets and aerodynamic fins for advanced anti-aircraft missiles which stands for the missile future development is a key technique of guidance and control in the terminal phase of interception. The thesis studies terminal guidance law and combined control with blended lateral jets and aerodynamic fins for missile. The main work includes:We use the proportional guidance law to achieve mathematical modeling of missile intercepting and develop simulation environment based on MATLAB, indicating the missile flight path. In addition, the animation effects of missile simulation were completed and the design of graphical user interface (GUI) was achieved.The thesis proposed an improved optimal sliding-mode guidance law On the basis of linearization of the model of the relative motion. The guidance law combines the advantages of optimal control and sliding-mode control and achieved very good control effect, which have valuable non-sensitive while cope with interference and changes in system parameters. At last the numerical simulation results verify the effectiveness of the design.Based on relative motion between missile and object and proportional navigation, one logic-based switching strategy combined control method blended lateral Jets and aerodynamic fins is proposed. In the phase of lateral jets, predictive control, based on Fliess functional expansion, is used to establish a Firing Logic Optimization control model.A H₂ decoupling analytical design under internal model control structure is adapted to a modified model of divert controlled missile so that the controller could handle the system uncertainty and the coupling induced by divert thrusters.Finally, based on the parameters of missile offered by aviation research institute, we give the simulation results of the above algorithms.