Goodrich Actuation Systems

A rotary actuator (100) is provided which comprises: a rotary component (102); a fixed component (104a, 104b), wherein the rotary component is adapted to rotate about a rotational axis (X-X) relative to the fixed component, wherein the fixed component is configured to be mounted to and fixed relative to a first structure; and a mounting arrangement (106) adapted to mount the rotary component to a second structure such that rotation of the rotary component pivots the second structure about the rotational axis relative to the first structure. The mounting arrangement comprises: a rotary output (108) configured to rotate with the rotary component; a first rotary output aperture (120); a second rotary output aperture (122), wherein the first and second rotary output apertures are spaced from each other and extend through the rotary output; a driving component (130a, 130b) configured to be fixed to the second structure to drive rotation thereof; a first driving component aperture (132); a second driving component aperture (134), wherein the first and second driving component apertures are spaced from each other and extend through the driving component; an eccentric bushing (140) at least partly located in at least one of the first rotary output aperture and the first driving component aperture; a first fastener (170) extending along a first fastener axis (F-F), through the eccentric bushing, the first rotary output aperture and the first driving component aperture; and a second fastener (172) extending along a second fastener axis (G-G), through the second rotary output aperture and the second driving component aperture so as to mount the rotary output to the driving component, wherein the distance between the first fastener axis and the second fastener axis is adjusted by rotation of the eccentric bushing.

An aircraft control surface actuation system comprising a reducer and an aircraft control surface, the reducer comprising: a first piston with a first frontal area, the first piston configured to move the aircraft control surface; and a second piston with a second frontal area, the second piston configured for actuation by an actuator. The second piston is in hydraulic communication with the first piston, such that movement of the second piston causes movement of the first piston. The second frontal area is different to the first frontal area to provide a reduction ratio between the actuator and the aircraft control surface.

There is provided a linear actuator (10) comprising: an output rod (20) having a longitudinal axis (22) and a distal end (11); a structure (26) comprising a friction surface (28) radially spaced from the output rod (20), wherein the output rod (20) is configured for extension and retraction in an axial direction relative to the structure (26); an input rod (18) for driving movement of the output rod (20), wherein the input rod (18) is axially moveable relative to the output rod (20); and a locking element (30; 48). The locking element (30; 48) comprises: a brake portion (32; 50) arranged between the friction surface (28) and the output rod (20); and an inclined surface (26; 54). The locking element (30; 48) is axially moveable relative to the output rod (20), wherein when the input rod (18) is moved in a first axial direction (D1; D2) relative to the structure (26), the input rod (18) contacts the locking element (30; 48) so as to drive the output rod (20) in the first axial direction (D1; D2), and wherein when an external load acts on the distal end (11) of the output rod (20) in the first axial direction (D1; D2), an engagement feature (40; 58) of the output rod (20) is pushed against the inclined surface (26; 54) of the locking element (30; 48) so as to wedge the brake portion (32; 50) of the locking element (30; 48) against the friction surface (26), limiting movement of the output rod (20) in the first axial direction (D1; D2).

A locking mechanism (3) for an actuator (1) is provided. The mechanism includes: a rotatable shaft (14) extending along a longitudinal axis (C-C), the shaft comprising a circumferential outer surface (18) and three or more surface features (20a-20f), wherein the three or more surface features are circumferentially spaced from each other; an outer casing (16) comprising an inner surface (56) circumferentially surrounding at least part of the shaft, wherein the outer casing is axially movable between a first axial position and a second axial position relative to the shaft; and three or more balls (32a-32f), wherein each of the three or more balls is received by a respective surface feature and axially retained within the respective surface feature. Each surface feature comprises: a first surface (22) extending from a first surface first end (24) on the circumferential outer surface to a first surface second end (26), wherein the first surface second end is radially inward of the first surface first end; and a contact surface (28) extending from a contact surface first end (30) on the circumferential outer surface to the first surface second end such that at least part of the contact surface extends at an acute angle to the first surface, wherein the contact surface first end is circumferentially spaced from the first surface. Each ball is motivated towards the first surface of the respective surface feature when the shaft rotates in a first direction. Each ball is motivated away from the first surface of the respective surface feature when the shaft rotates in a second, opposite direction. A radial distance of the inner surface from the longitudinal axis varies in the axial direction such that: when the outer casing is in the first axial position, the shaft is free to rotate in the first direction and in the second direction, and when the outer casing is in the second axial position, the shaft is free to rotate in the first direction and each of the balls are wedged between the inner surface of the outer casing and their respective contact features, resisting the rotation of the shaft in the second direction.

A control system for an aircraft comprising: a first left wing control element; a second left wing control element; a left wing hydraulic power pack configured to supply hydraulic fluid to the first and second left wing control elements to actuate the first and second left wing control elements; a first right wing control element; a second right wing control element; and a right wing hydraulic power pack configured to supply hydraulic fluid to the first and second right wing control elements to actuate the first and second right wing control elements.

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 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.

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.