ADVANCED MISSILE GUIDANCE SYSTEM AGAINST VERY HIGH SPEED TARGET

The advanced missile guidance system of surface-te air missile against very high speed target is studied. The system is characterized by intercepting very high speed targets with relatively low speed missiles. With this system, fairly small missiles are available for the mission and enough navigation time is assured. First, the successful lockon conditions are investigated, in regard to the interception geometries for various target speeds and altitudes. The results show that, in order to achieve small miss distance against the faster target than the interceptor, the aspect angle at lockon should be near 180°. Next, the optimal missile midcourse guidance law, which attains the optimal target aspect angle at lockon, is studied. The advanced guidance system proposed here is the combination of this optimal midcourse guidance and conventional proportional navigation homing guidance. The simulation results show that successful counterattack regions obtained by this system are far wider than the ones obtained by the less sophisticated guidance law.