Research On The Midcourse And Terminal Guidance Technologies Of Romote Missiles

With the changes of modern warfare mode,the rotating missile that adapt to high dynamic environment with long range,high precision,high power,low cost,miniaturization and strong anti-interference has been given high priority.In this dissertation,the long-range guided missile is considered as the application background,and centered on the guidance and control technologies of the long-range guided missiles in order to focus on the accurate acquisition of the rolling attitude,convert the trajectory between midcourse and terminal guidance smoothly,the adaptive control methods for nonlinear element of rotating missiles,guidance technologies with high-precision and high efficiency attack with a large impact angle and other issues are focus on.The mathematical models of kinematics and dynamics of the long-range rotating missiles used combined guidance technology are established,and the mathematical models of the trajectory of rotating missiles,the dynamic characteristics of the missiles,the random wind influence model and the guidance control system models are analyzed in details.Three kinds of roll angle extraction algorithms based on MEMS IMU are designed.Six accelerometers,two accelerometers with one gyroscope and three gyroscopes schemes are adopted to solve the problem of high precision acquisition of the roll angle of high dynamic rotating missiles.The mechanism of geomagnetic attitude determination and the geomagnetic attitude determination algorithm are studied.The experimental data show that the geomorphic attitude determination algorithm can obtain high accuracy information.In order to exploit the problem that the accuracy of different sub-filter systems is different in the integrated navigation system,a multi-source information fusion algorithm suitable for satellite /INS/geomagnetic integrated navigation system based on neural network is exhibited.The experimental results show that the algorithm can make up the deficiency of the traditional adaptive algorithm,and enhance the anti-interference ability.The main performance of the integrated navigation are more accurate and have the potential of widely used in engineering practice.A trajectory design method for the mid-terminal guidance trajectory of a rotating missile based on terminal sliding mode control and perturbation extended observer is proposed.The smooth transition of the trajectory between the midcourse and terminal guidance is realized,and the amplitude of the missile attitude is small and the terminal guidance is successfully captured.The midcourse guidance law is designed with consideration of the influence of external disturbance and the dynamics of autopilot.The characteristics of terminal non-singularity,kinetic characteristics after compensation and the characteristics of external disturbance is studied.The results show that the algorithm can meet the requirement that capture the target precise while maintaining the stability of the attitude.The character of the algorithm to resist random wind interference,satellite positioning error and velocity error on the case of adding or not disturbance observer is analyzed.The results show that the mid-terminal guidance transfer technique based on the virtual target point is of great significance to improve the stability of the missiles.This paper presents a technique for observing and controlling non-linear elements of high dynamic rotating aircraft actuators.Firstly,a general model of the effective and ineffective of the actuator is established.A second-order sliding mode controller is designed to accurately observe the efficiency of the actuator using the finite time convergence of the second-order sliding mode control method.At the same time,the adaptive guidance law based on STW(Super-twisting algorithm)designed and analyzed,and the stability was analysed.From simulation,it is observed that the proposed new guidance law is better than that of the FTCG(Finite Time Convergence guidance law)and the ISSG(Input-to-State Stability guidance law).In this paper,a generalized optimal guidance algorithm for high-order strong time-varying objects is proposed,which provides a basis for high-precision and large-angle attack.A general form that described the extended angle control optimal guidance law and the extended proportional guidance law was designed,Which is called generalized optimal guidance law.Analyses were conducted on the guided trajectory,velocity and acceleration command of the generalized optimal guidance law considering the dynamic delay of the non-pilot and the first-order pilot dynamics.The analytic expressions of terminal impact angle error and miss distance caused by terminal impact angle constraint and initial heading error haved been derived,and simulation was realized.The simulation results are in good agreement with the analytical solution.