The motion of homing-missile in case of threedimensional space is analyzed, and effect of spinning of missile which is inevitable in cruciform type missile and have large effect on missile's homing characteristic is investigated. In analyzing this problem, we assume that missile has constant spin velocity and has devices to execute proportional navigation. Spinning of missile, combined with responce lag time of guidance and control system cause to missile's complicated motion. In this paper characteristic of guidance and control system is represented by double, first order linear system

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