| 摘要 |
PROBLEM TO BE SOLVED: To provide a guide system for a missile with favorable space stability in radio guidance. SOLUTION: In the guiding system for a missile, guidance to a target is carried out on the basis of an attitude angle of the missile determined by inertial navigation, and an error angle of the target calculated by using data collected by delivering radio waves to the target at a predetermined transmission period, receiving reflected waves, converting them into digital data, and carrying out fast Fourier transform. A center position of a data acquisition time of the data to be collected with respect to the transmission period is set such that it is substantially the center of a data acquisition setting period. COPYRIGHT: (C)2007,JPO&INPIT
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