Study On Guidance And Control For High-altitude Lateral Force Control Interceptor Missile

In recent years, with the continuous development of missile weapon system, to enhance national defense by the efficiency of the missile attack hotspot of current research, missile intercept technology to become one of the key research areas. Easier for conventional ballistic missiles to intercept missiles, but to make the interception unconventional success rate of increase, must increase its mobile defense capability. Interceptor missile guidance to improve the accuracy and precision is important. Lateral force control technology to make up the aerodynamic control of some of the missiles is not enough as the mobility of defects. Higher mobility for the interceptor missile is more effective.This paper studies the lateral force in high-altitude missile interceptor application. Its main contents are: description of the missile intercept technology, illustrates the lateral force control technology in missile interception application. Firstly, the basic coordinate system and each coordinate system transformation matrix, and describe the goals were established and interceptor missiles movement mathematical model, the introduction of the comparative analysis of two guidance law. Given orbit control and attitude control engine thrust model. Size and generated thrust is discussed. Gives a relatively simple micro-engine switch logic, and simulation tests.