Patent ID: 8106340

Claim:
A method for guiding a multistage interceptor missile toward a target missile, said method comprising the steps of: tracking a position of said target missile with a sensor; generating a pre-interceptor-missile-launch predicted intercept point and a predicted intercept time, and loading the predicted intercept point and time into an interceptor missile guidance; launching said interceptor missile, and controlling a first-stage guidance in response to target missile bearing and elevation at the predicted intercept point; transitioning to a second stage of propulsion of said interceptor missile; controlling second-stage guidance in response to second-stage acceleration commands; generating said second-stage acceleration commands in response to an elevated predicted intercept point generated by adjusting the predicted intercept point to account for effects of interceptor missile velocity at waypoint, interceptor missile propulsion beyond second stage, and gravity between the waypoint and the predicted intercept point, which predicted intercept point is generated using a Runge-Kutta integration method working on predicted target missile position, velocity, and acceleration; transitioning to a third stage of propulsion of said interceptor missile; guiding said third stage toward said target missile; and transitioning to a fourth stage of interceptor missile flight and guiding interceptor missile to intercept said target missile.