GUIDING METHOD OF MISSILE

PURPOSE:To permit the discovery of a target in a short period of time and contrive the cost-down of a missile itself by a method wherein the missile is provided with an attitude control means which controls the attitude of the missile so that a picture element, receiving infrared rays most intensively, is brought to the center of a two-dimensional infrared-ray sensor. CONSTITUTION:An attitude control means 12 is provided with an operating unit 20, consisting of microcomputers, and a steering unit 21, operated by an attitude control signal outputted by the operating unit 20. The operating unit 20 scans the groups of picture elements 10a-10p of a two-dimensional infrared-ray sensor 10 spirally and sequentially from the outside of the groups toward the inside of the same by a preset program when a search starting time has come and processes the informations of respective picture elements 10a-10p to specify a picture element, receiving infrared rays from a target 3 most intensively among the picture elements 10a-10p. Then, the operating unit 20 outputs an attitude control signal, which brings the specified picture element 10c to the center O of the two-dimensional infrared-ray sensor 10, to drive the steering unit 21 and track the target 3 by a missile 2 on a route l2. As a result, a target can be searched in a short period of time and the cost-down of the missile can be contrived by abolishing expensive annexed mechanisms.