Guidance of e.g. seeking missile, continuously assesses likely target dodges, and steers missile to their computed, most probable end position

摘要

The missile seeking head and guidance computer register the instantaneous path of the target. On the fly, possible target positions reached by maneuvering after a given interval, are predicted recurrently. Transition probabilities as a result of maneuvers, are generated from the instantaneous path. A momentary sweet spot is formed by multiplication of the positions and their probabilities. The missile is guided towards this sweet spot. In a variant application, maneuverable objects are caused to avoid collision by steering away from it.