| 摘要 |
PROBLEM TO BE SOLVED: To solve a problem on degradation of a flying distance and turning performance as in a conventional side thruster, the attitude is controlled by optionally changing the direction of thrust by moving an injection tip projected to a side face, which causes the increase of resistance by the movable injection tip and the increase of base machine mass by installation of a dedicated driving device. SOLUTION: This guided missile comprises the thruster injecting a gas and controlling the attitude of the guided flying object, a steering wing controlling the flowing direction of the gas injected by the thruster and controlling the attitude during flying, and a guidance control portion for operating the thruster and the steering wing and guiding the flying object to a target, and high attitude controllability can be achieved by deflecting the injected gas injected by the thruster without increasing air resistance and mass. COPYRIGHT: (C)2008,JPO&INPIT
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