【発明の名称】飛翔体の誘導方法

Japanese Patent JP2596632

B2

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.

Fukuda Yasuo
Takanobu Matsuura
Eizo Tanaka
Ippei Tanaka
Uji Masaru

JP15609490A

April 02, 1997

June 14, 1990

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Director General, Technical Research Division, Defense Agency
Nissan Motor Co., Ltd

G01S3/786; F41G7/22; G05D1/12; (IPC1-7): F41G7/22

JP1277724A
JP6319575A
JP62201381A
JP6431073A

Fujiya Shiga (2 outside)

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