| 摘要 |
The invention is a spoiler device for an aircraft having a leading edge slat (50) mounted on at least a portion of the leading edge of the wing of the aircraft. A rear portion (52) of the leading edge slat (50) is rotatably mounted thereto and movable from a retracted position to an extended position (52') so as to act as a spoiler. A latch mechanism comprising links 56, 60, 68 and spring member (76) which yieldably hold the rear portion (52) of the slat (50) in the retracted position. An actuator (80) is provided which is mounted to the wing and which is in detachable contact with the latch mechanism of the slat (50). Upon actuation the rear portion (52) is extended and is returned to the retracted portion by the spring member (76). The actuator (80) can be either mechanical, pneumatic, hydraulic or electrical.
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