Anti-air missile guidance technique

Abstract

A computer implementation processor is provided for directing a missile from a radar towards an interception point of a moving target. The processor includes a missile simulator module; a pre-launch module; a trajectory curvature module; and a guidance module. The missile simulator module determines look angle time to the interception point from the radar. This module determines the look angle time remaining to intercept, at which the angular difference between the line-of-sight to the interceptor and the target are below a threshold value. The pre-launch module provides an initial curvature gain value. The trajectory curvature module updates the curvature gain value from the look angle time. The simulator module receives the gain value in feedback. The guidance module receives the gain value and physical characteristic information for the missile and provides acceleration command to the missile to intercept the target.

Dependencies are inferred from the claim text.