| 摘要 |
PROBLEM TO BE SOLVED: To provide a nozzle structure capable of easily controlling an attitude of a missile, though the missile performing injection to a side part, often largely changes its aerodynamic characteristic as a separation region of a boundary layer is generated in a wide range of a body surface from a front part to a side part of the nozzle in performing injection. SOLUTION: This side thruster of the missile comprising the injection nozzle performing the injection to the side part, further comprises a recessed portion formed at the periphery of the injection nozzle including an injection tip of the injection nozzle, on a body surface of the missile, the injection tip of the injection nozzle is formed on a bottom surface of the recessed portion, and the recessed portion has difference in level at a front side in the missile advancing direction with respect to the injection tip of the injection nozzle. COPYRIGHT: (C)2008,JPO&INPIT
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