Study On Guidance Control System Of Long Range Air To Air Missile

The guidance and control system of missile plays an important role in missile system. So the design of guidance and control system is a meaningful work. The dissertation designs the guidance and control system of long range air to air missile. Main research is listed as follows:Study on mathematical model. The necessary coordination systems are defined and the transformation relations among them are given. The force and moment are analyzed, kinematics, kinetics, quality and maneuvering relation equations are given. So, the mathematical model of missile is completely set up.Design the terminal guidance law. According to the characteristic of the air to air missile, for the accuracy and engineering application, robustness of the sliding-mode variable structure theory is insensitivity to uncertainty, the adaptive sliding-mode guidance law is designed. Five influence factors of proportional navigation guidance law are analyzed and the appended proportional navigation guidance law is proposed for compensating the missile acceleration and gravity acceleration. The simulation results show that high precision can be obtained with the two guidance laws and can achieve performance satisfactorily.Design the controller. Based on the established missile mathematical model, it could be simplified in some circumstances. The control model of air to air missile is proposed. The dissertation chooses switching function and reaching law, and designs variable structure controller with integral term using variable structure control theory. The simulation result indicates that the variable structure controller has excellent robustness to system uncertainties and external disturbance and has good dynamic property which meets the design requirements.At last, 6 DOF simulation experiment is carried on. For overall verifying the capability of the controller and the guidance law when missile flies in large airspace, 6 DOF simulation experiment is carried on in different target maneuvering conditions. The results from simulation prove that the controller and the guidance law can stabilize missile flight attitudes and hit the target.