| 摘要 |
<p><P>PROBLEM TO BE SOLVED: To provide a guiding method and a guiding system for a missile capable of realizing simplification, miniaturization, and cost reduction of an installation structure for a sensor part, and capable of improving certainty and reliability of execution of terminal guidance. <P>SOLUTION: In a composition, the sensor part 16 can be fixed to an airframe 3 of the missile such that an attitude of the sensor part 16 can be adjusted with respect to the airframe 3 of the missile 2. Before firing the missile 2, the attitude of the sensor part 16 with respect to the airframe 3 of the missile 2 is adjusted and fixed such that a target 1 is within a visual field range of the sensor part 16 when the missile 2 reaches a target 1 neighborhood by intermediate guidance. <P>COPYRIGHT: (C)2008,JPO&INPIT</p> |
