Goodrich Actuation Systems Patente

A system (1) for actuating a spoiler (4a-c) of an aircraft (2). The system (1) includes a spoiler (4a-c) and an actuator (8) configured to actuate the spoiler (4a-c) between a closed position and an open position. The actuator (8) includes an output member (12) connected to the spoiler (4a-c), wherein the output member (12) is configured to move between a retracted position, in which the spoiler (4a-c) is in the closed position, and an extended position, in which the spoiler (4a-c) is in the open position. The actuator (8) also includes a motor (10) configured to drive the output member (12) between the retracted position and the extended position and a biasing member (24) configured to bias the output member (12) towards the retracted position.

A motor (2) configured to drive an actuator. Wherein the motor (2) includes a stator (4) and a rotor (6). Wherein the rotor (6) includes an array of permanent magnets (8) in a Halbach arrangement and a support structure (12) configured to support the array of permanent magnets (8). The support structure (12) is non-magnetic.

An actuator for an aircraft control surface, the actuator comprising: first, second and third movable elements, wherein the third movable element is in screw engagement with the first movable element with a first lead , wherein the third movable element is in screw engagement with the second movable element with a second lead, wherein the first lead is different from the second lead to provide a reduction ratio between the first and second movable elements; wherein a motor engaging component of the first, second and third movable elements and third movable element is connectable to a motor such that the motor rotates the first component in use, wherein an aircraft control surface engaging component of the first, second and third moveable elements is connectable to the aircraft control surface to move the aircraft control surface on rotation of the motor engaging component in use.

An aircraft control surface system 101 comprises a control surface 102 and an actuator device 200 for controlling movement of the control surface between a retracted configuration and a deployed configuration. The actuator device comprises an actuator arm 202 coupled to the control surface, a barrel 204, a piston 206 and a pumping apparatus 212. The actuator can perform a deployment operation in which a deploying force causes the control surface to move from the retracted configuration to the deployed configuration and the piston to move so as to cause an increase in the fluid pressure difference between forward 208 and rear 210 chambers of the barrel. The actuator can also perform a retraction operation in which the pumping apparatus causes fluid to flow into the forward chamber of the barrel to further increase the fluid pressure difference and drive the piston to move so that the control surface moves from the deployed configuration to the retracted configuration.

A strain wave drive assembly comprising: an assembly housing (100) containing: a wave generator (110) arranged to rotate about an axis and having an elliptical cross-section; a flex spline (30) mounted around the wave generator; and an output spline (55a, 55b) arranged around the flex spline, the output spline driven by the wave generator via the flex spline, wherein the wave generator, the flex spline and the output spline are assembled to float relative to the assembly housing.

A foldable wing tip actuation system comprising: a plurality of actuators including: a wing tip actuator (10, 10') configured to move a wing tip (1, 1') relative to a fixed wing part (2, 2') of an aircraft about a hinge line (H, H') at which the wing tip is hingedly attached to the fixed wing part; one or more latch actuators (61, 62; 61', 62') configured to operate a latch mechanism for locking the wing tip against movement relative to the fixed wing part; and a common motor drive (20, 120) arranged to drive two or more of the plurality of actuators under control of a single motor control (30, 130).

There is provided a device (100) for aiding in inserting internal magnets into a hollow shaft (600) and / or removing internal magnets from the hollow shaft, the hollow shaft extending along a longitudinal axis (A-A), the device comprising a fixed member (200) configured to support the hollow shaft, a first magnet (330a) mounted such that, when in a use position, the north pole of the first magnet faces the hollow shaft, and a second magnet (330b) mounted such that, when in a use position, the south pole of the second magnet faces the hollow shaft, wherein the first and second magnets are axially moveable relative to the fixed member. There is also provided a method for inserting internal magnets into a hollow shaft, a method for removing internal magnets from a hollow shaft, and a method for assembling an actuator.

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A rotary electromechanical actuator, EMA, comprising: a first EMA part (1) comprising a first electric motor (12) and a first rotary shaft (S1) extending along an axis and arranged to be rotated about the axis by the first electric motor, and a first 1st stage gearbox (10) providing a geared transmission from the first electric motor to the first output shaft, and a first brake assembly (14) for applying a braking force to the first output shaft; the EMA further comprising: a second EMA part (2) comprising a second electric motor (22) and a second rotary shaft (S2) extending along the axis and arranged to be rotated about the axis by the second electric motor, and a second 1st stage gearbox (20) providing a geared transmission from the second electric motor to the second output shaft, and a second brake assembly (24) for applying a braking force to the second output shaft; and the EMA further comprising an output (40) arranged to rotate with rotation of the first shaft and the second shaft; the EMA further comprising a common stage gearbox (30) providing a geared transmission between the first and second shafts and the output (40), the common stage gearbox being located between the first and second 1st stage gearboxes; wherein the common stage gearbox comprises: a first sun gear (32) in engagement with and driven by the first shaft (S1) and a second sun gear (34) in engagement with and driven by the second shaft (S1); a first intermediate gear (33) driven by the first sun gear; a second intermediate gear (35) driven by the second sun gear; and an outer gear structure (36) arranged to engage with the first and the second intermediate gears; wherein the outer gear structure comprises: a first outer gear part (37) that extends across and engages both the first intermediate gear and the second intermediate gear; and a second outer gear part (38) that meshes with the first intermediate gear and is engaged with and drives the output (40).

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An electromechanical actuator, EMA, assembly operable in a plurality of modes, the EMA assembly comprising: an electrical motor having a motor shaft (201) extending along an axis (A) of the EMA, the motor driving the shaft to rotate about the axis; a gear assembly (401, 402) mounted around, and in geared connection with the shaft, to rotate with the shaft; an EMA output (300) connected to the gear assembly such that rotation of the motor shaft causes rotation of the output via the gear assembly, the output rotating at a speed which is a predetermined fraction of the speed of rotation of the motor shaft based on the gear ratio of the gear assembly; wherein the output is arranged to have a neutral position and to be rotatable away from the neutral position in a first, positive, extension direction to an extension position and away from the neutral position in a second, negative, retraction direction to a retracted position; a torque limiter (900) having a predetermined torque limit, wherein the torque limiter is arranged to limit torque transfer between the gear assembly and the output; an anti-extension mechanism (14, 140, 145) moveable between an engaged position in which it inhibits rotation of the output in the extension direction and a disengaged position wherein it allows rotation of the output in the extension direction, the anti-extension mechanism comprising a solenoid and a ratchet wheel and an anti-extension spring, wherein the anti-extension mechanism is in the disengaged position when the solenoid is energized to move the ratchet against the force of the anti-extension spring and is in the engaged position when the solenoid is not energized; wherein, in an active mode of the plurality of modes, the solenoid is energized and wherein rotation of the output shaft in either direction of rotation drives the output to rotate; wherein in an anti-extension mode, the solenoid is not energized and, when the output is at the neutral position or in the extension position, the output shaft is connected for rotation, via the ratchet, wherein the ratchet is arranged to prevent rotation of the output shaft in the extension direction of rotation; and wherein the torque limiter disengages the anti-extension mechanism in the event that the predetermined torque limit is reached; wherein in the anti-extension mode and when the output is in the retracted position, the torque limiter is adjusted to disengage the anti-extension mechanism at a torque lower than the predetermined torque limit., and/or when the output position is approaching an end stop position the torque limiter is adjusted to disengage the anti-extension mechanism at a torque lower than the predetermined torque limit.

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A mechanical architecture is provided for aircraft distributed flap actuation and includes a shaft (310) and first and second actuation units (320, 330). The first actuation unit (320) includes a motor, a first actuator for translating and rotating a flap and being connected to a first side of the flap, a first gearbox to transfer and increase torque from the motor to the first actuator and a first brake configured to hold the flap in place. The second actuation unit (330) includes a second actuator that receives the torque from the first gearbox via the shaft (310) for translating and rotating the flap and being connected to a second side of the flap, a second gearbox that receives the torque from the first gearbox via the shaft (310) and reduces the torque and a second brake receptive of the torque from the second gearbox and configured to hold the flap in place through the second actuator.

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A threaded fastener comprising a first threaded part (1) defining an axis, A, from a first end (111) to a second end (112) thereof, the threaded part having a radially inwardly extending thread along a portion (11) thereof between the first and the second end and a non-threaded portion (12) between the thread and the second end, and a second threaded part (2) defining an axis from a first end (211) and a second end (212) thereof and having a radially outwardly extending thread (21) along a portion thereof between the first and the second end and a non-threaded portion between the thread and the first end, the fastener further comprising a compressible part (13, 300) arranged to provide an axial load to one of the first and the second threaded parts when the parts are fastened together. The first threaded part is arranged to be fastened around and to the second threaded part by rotating the inwardly extending thread of the first threaded part along the outwardly extending thread of the second threaded part until the inwardly extending thread and the outwardly extending thread no longer engage and the inwardly extending thread lies along the non-threaded portion of the second threaded part, and wherein the compressible part is preloaded such that when the inwardly extending thread and the outwardly extending thread no longer engage and the inwardly extending thread lies along the non-threaded portion of the second threaded part, the compressible part loads the inwardly extending thread axially into abutment with the outwardly extending thread to secure the first and second threaded parts axially together.

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