| 摘要 |
An electrical mechanical blow-down mechanism for use with an aircraft spoiler avoids possible damage due to high inertial loading when a power failure occurs as the spoiler (10) is moving toward or is at an extended position by means of a structure including a ball screw mechanism (18) adapted to be connected to the spoiler (10) and including an input gear (34) adapted for rotation about an axis (36). The mechanism is ultimately driven by an electrical motor (20) having a rotary output (22) with at least one gear (26, 28) interconnecting the input gear (34) and the rotary output (22). A pawl (36) is mounted for movement between positions engaged with and disengaged from the input gear (34) and a spring (78) is utilized to normally bias the pawl (36) toward the engaged position. A solenoid (50) is operable to move the pawl (36) against the spring (78) toward the disengaged position and a motion sensor (90) is associated with the input gear 34 to determine the direction of rotation thereof. A latch (42, 106) is provided for holding the pawl (36) in the disengaged position for one direction of movement of the input gear (34) and releasing the pawl (36) for the other direction of rotation of the input gear (34). Motion sensor (90) controls movement of latch (42, 106) to prevent pawl (36) engagement after a power failure until such engagement will not damage the spoiler actuator.
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