Design Of Guidance And Control Law For Agile Turning Missile

Over-the-shoulder launch is one of key technologies for the new generation airto-air missiles.The research on the control of initial turning phase of a over-theshoulder launch missile has drawn much attention.In this thesis,a control scheme for the agile turning of a missile via pure aerodynamic control is proposed by analyzing the aerodynamic and control characteristics of the missile turning at large angle.The main contents include the optimization design of the control command in the turning phase,and therefore the design and research of closed-loop tracking control law,design and simulation of guidance law in the terminal guidance phase together with the analysis and design of the handover guidance law in the transition from the turning to the terminal guidance.Firstly,the mathematical model of air-to-air missile turning process is established.Through the research and analysis of the aerodynamic and control characteristics of the missile pitching motion,a control method of trajectory optimization and closed-loop control is proposed,aiming at the uncontrollable area due to large angle-of-attack of the missile.Secondly,based on the mechanism analysis model of the missile turning process,the mathematical model of command optimization problem is established with the turning time to be optimized.The Gauss pseudospectral method is used to discretize the problem,then it is transformed into a quadratic programming problem and then solved.The discrete optimization results are obtained.Through interpolation,the continuous optimal command of the connection is obtained.Then,using the command as the reference signal,the attitude tracking control law is designed using sliding mode control method and the robustness of the control law is tested.Finally,based on the relative motion model of the missile and the target in threedimensional space,the guidance law of terminal guidance phase is designed by using finite time convergence method.At the same time,the possible problems of trajectory transition between turning and terminal guidance are analyzed,and the linear transition guidance law is designed.Then,simulation is conducted for the threedimensional trajectory of the missile from turning phase to terminal guidance.The final simulation results show that the guidance and control scheme designed in the thesis is feasible.