Goodrich Actuation Systems

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.

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.

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.

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.

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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