Study On Intelligent Control And Correction Method Of Missiles Precision

The development and application of modern missiles ballistics, dynamics and control theory are reflected in researching the method of improving the firing precision by artificial intelligence control means in the complex environment with random disturbance. And one of the important issues is to study the newer and more practical trajectory correction control methods. For this problem, based on modern missiles ballistics, optimal control theory and random processs, intelligence control and correction means of missiles firing precision are studied in the complex environment with random disturbance in this thesis. The impact of random interference factors on firing dispersion is analyzed. Then sensitivity problem of the trajectory parameters to aerodynamic coefficients is studied. And based on the measured value, trajectory parameters and aerodynamic coefficients are identified in order to obtain the prediction model of missiles and adaptive optimal control theory and methods and to control and correct the ballistic of missile so as to enhance the missile firing precision through the control actuator. The main parts are concluded as follows:Based on 6-DOF motion space flight dynamics model of missiles system and the random wind field model, Monte-Carlo simulation technology is used to forecast the intensity of projectiles impact points. Based on the control system sensitivity theory, the sensitivity function linked to the problems of technical parameters in the control system is established and selected to study the algorithm of the control system sensitivity function. Through calculating sensitivity function, influence of aerodynamic coefficients on trajectory parameters is analyzed.For the problem of identifying the random trajectory parameters under the influence of random factors, based on the control system sensitivity theory and Kalman filtering theory, ballistic parameters and the aerodynamic coefficients are identified. Through identification, the estimated mathematical model with the more precise ballistic parameters is established so as to enhance the accuracy of the launch of the missiles. Method of missiles ballistic optimal control is given according to the estimated model and optimal control generalized work principle. And reasonable control strategy of trajectory characteristic parameters is derived. Using fast calculation method can reduce computational complexity and achieve adaptive control.For the need of correct control of the certain type trajectory correction projectile, the electric control actuator system of the correct executing mechanism is designed for the body structures of the trajectory correction projectile, and the correct executing mechanism is designed too. The small volume, high-performance permanent magnet brushless dc motor is used for the servo motor as executing mechanism of the electric control actuator servo system, so that the many advantages of permanent magnet brushless dc motor combine with trajectory correction technologies. The control actuator system model structure and related parameters are determined, and the controller is designed.Taking Matlab as a computing platform, the mathematical models in the thesis are programmed to form a complete computing software. The comparison of simulation of a certain type and range test results indicates that the optimal control of the estimated model and trajectory correction method presented in this thesis can improve the missile firing precision in design of missiles.