Research On Guidance And Control For Missile With Lateral Jets And Aerodynamic Surfaces

To cope with threatens of high-speed reentry of ballistic missiles and other modern air weapons, it is necessary for intercept missiles to have guidance and control ability of high precision, up to hit-to-kill. Dynamic responses of traditional aerodynamic control deteriorate significantly in high altitude as a result of efficiency decline in control fins. Instead, dual attitude control of intercept missiles, consisting of attitude-control-type lateral jets and aerodynamic control fins, can significantly improve the dynamic responses, based on which, precise interception can be attained against high-altitude, high-speed and large maneuvering targets. According to the characteristics of guidance and control systems of missiles with dual control, researches on suitable guidance and control methods are of great importance in both theory and engineering. In this context, the dissertation focuses intensively on the guidance and control problems of endo-atmospheric missiles with dual control.First, mathematical model is established according to the configuration of lateral pulse jets in the attitude control system. Kinematic and dynamic equations of the missile with dual control of lateral jets and fins are constructed based on the mathematical description of turbulent effects on lateral jet interactions. These provide the foundations for the analysis and the design in the sequel.Second, through the analysis of characteristics of a lateral pulse jet, basic principles for the operation of pulse jets array are given. Through the analysis of dynamic responses of missile attitude while lateral jets are applied, an algorithm for calculating pulse jets consumption is presented. Dual control characteristics are analyzed based on the characteristics of aerodynamic control.Third, attitude control design methods of missiles with dual control are investigated based on model predictive control and active disturbance rejection control. Based on the control characteristics, control strategy, that combines nonlinear model prediction control with active disturbance rejection control, is presented, and corresponding design frame is constructed. Then operation logic of pulse jets array is designed. By the analysis of finiteness of constraint set, attitude control system design method of the dual control is given, and the stability of the closed-loop system is analyzed.Fourth, terminal guidance law of the missiles with dual control is investigated. Descriptions of predicted miss distance and maximum correction distance of terminal guidance are given. By comparing the two distances, switching principle is given, by which time instant can be decided to switch the control from aerodynamic control to dual control. Then, time constants of the attitude control system in different control mode are considered in terminal guidance law design. Finally, by utilizing generalized H2 method in finite time horizon, miss distance analysis is conducted in the presence of control switching. In the analysis, target maneuvering is considered.At last, the obtained results are applied to the design of guidance and control laws of certain type of endo-atmospheric missiles with dual control. the attitude control system and end-game guidance system are designed based on model prediction control and active disturbance rejection control. Simulation is conducted in a 6-degree-of freedom model architecture. The simulation results justify the proposed theories and methods.