| 摘要 |
PROBLEM TO BE SOLVED: To provide a steering vane driver of a missile providing a degree of freedom in the installation position of an actuator mechanism driving a steering vane and having aerodynamically small loss. SOLUTION: The rotation force of a motor 1a of an actuator 1 is converted into a vertical move by a ball screw 1b and a nut 1c, and into rotation in the direction perpendicular to the axis of the missile by a connected oscillating lever 1d. A link bar 1e of the oscillating lever 1d is engaged into a guide groove 5a of a cylindrical frame body 5, which is oscillated by the move of the actuator 2. The link bar 4e of the oscillating lever 4b engaged into the guide groove 5b of the cylindrical frame body 5 is oscillated, the oscillating lever 4b supported on a fixed spindle 4a is oscillated, and a connected steering shaft 4 is steered. The rotation force of a motor 2a of the actuator 2 is converted into a vertical move by a ball screw 2b and a nut 2c, and into rotation in the direction perpendicular to the axis of the missile by a connected oscillating lever 2d, and the steering shaft 3 is steered. COPYRIGHT: (C)2006,JPO&NCIPI
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