초록 ▼

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

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.

대표청구항 ▼

[ I claim:] [1.] A blow-down mechanism for use with an aircraft control surface comprising:a ball screw mechanism adapted to be connected to an aircraft control surface and including an input gear adapted for rotation about an axis;an electrical motor having a rotary output;at least one gear interco

[ I claim:] [1.] A blow-down mechanism for use with an aircraft control surface comprising:a ball screw mechanism adapted to be connected to an aircraft control surface and including an input gear adapted for rotation about an axis;an electrical motor having a rotary output;at least one gear interconnecting said input gear and said rotary output;a pawl mounted for movement between positions engaged with and disengaged from one of said input gear and said one gear;means normally biasing said pawl toward said engaged position;an electrical actuator operable to move said pawl against said biasing means toward said disengaged position;a motion sensor associated with said one of said input gear and said one gear and for sensing the direction of rotation of said one of said input gear and said one gear;a latch for holding said pawl in said disengaged position and responsive to said sensor for holding said pawl in said disengaged position for one direction of rotation of said one of said input gear and said one gear, and for releasing said pawl for the other direction of rotation of said one of said input gear and said one gear.