The Research Of Launch Prefabricate Angle And Analysis Method Of 3D Guidance Trajectory For Gun-launched Missile

The design of the prefabricate angle and 3D-guidance law for gun-launched missile are studied in this thesis. The development of gun-launched missile provides a way to improve the combat effectiveness of tanks, cannons and shipboard artilleries. In order to solve the problem which the missile would be far from the center of beam field at the start of control when the missile tracking moving target, a method of designing prefabricate angle is studied, the prefabricate angle is relevant to the target motion characteristics and the quadrant of beam field which the missile is expected to enter in. The result shows that this method can decrease the deviation from the center of the beam to make sure the missile can start tracking successfully and the calculation is simple. Nowadays most analysis of guidance trajectory are in the fore-and-aft plane, in this thesis, the model of 3D-guidance law is built to get the requirement of characteristic variables of system, such as required normal overload, balanced angle of attack and balanced angle of slip. The traditional method to solve the required overload is using the kinematics equations of mass center, in this thesis, a novel method for the solution of required overload is studied by analyzing the absolute motion, relative motion and transport motion as the missile moving towards to the target.