Goodrich Actuation Systems Sas

Rohr, Inc.

Goodrich Actuation Systems Limited

Karl Potier

Raphael Medina

Maxime Serrand

Corentin Boitard

Sebastien Vandevoir

Jennifer Davis

Quentin Ricard

Jerome Socheleau

Arnauld Hervieux

Arnaud De La Chevasnerie

Sébastien Vandevoir

An epicyclic gear assembly includes: a sun gear rotatable about an axis (A); a plurality of planetary gears arranged around and in meshing engagement with the sun gear such that rotation of the sun gear about its axis causes corresponding rotation of each of the planetary gears about their own axes; and an outer ring gear arranged around and in meshing engagement with the plurality of planetary gears such that rotation of the planetary gears causes rotation of the outer ring gear about the axis A and relative to the fixed outer rings. The assembly also includes a backlash reduction mechanism between the planetary gears and the outer ring gear. The backlash reduction mechanism includes a planetary gear carrier with a plurality of carrier segments each carrying a respective one of the planetary gears, the segments together defining an annular carrier having a bore therethrough.

Backlash reduction in epicyclic gears

A rotary actuator includes an actuator body having a first end and a second end defining an interior of the actuator body therebetween, an axis X of the body being between the first and second ends. Each end is provided with a port arranged to receive hydraulic fluid. The actuator also includes: mounting parts extending from the ends into the interior of the actuator body a screw mounted to the mounting parts within the actuator body between the first and second ends, the screw mounted to the mounting parts via splines to allow linear axial translation of the screw relative to the mounting parts. The screw having one or two walls extending across an inner diameter d of the screw.

Rotary actuator

An aircraft spoiler system includes a spoiler, a motor arranged to drive movement of the spoiler between a retracted and a deployed position, a power supply connector for connection to an external power supply, and a movement limiting portion. The movement limiting portion is selectively engageable. It is arranged, when engaged, to enable movement of the spoiler towards the retracted position and to prevent movement towards the deployed position. The movement limiting portion comprises a mechanical actuator actuatable to move between a first position and a second position. Actuation of the mechanical actuator to the second position disengages the movement limiting portion. In the second position, the mechanical actuator obstructs the power supply connector such that the mechanical actuator cannot be actuated to the second position.

Aircraft spoiler system

An asymmetric torque limiter having an axis of rotation including a first annular friction disk, a second annular friction disk a skewed roller disk a first resilient member and a second resilient member. The second annular friction disk is concentrically arranged with the first annular friction disk. The skewed roller disk is in contact with the second annular friction disk. The skewed roller disk includes a plurality of skewed rollers mounted in an annular retainer. The plurality of skewed rollers are about a respective roller axis, each roller axis being skewed to a radial direction passing through the skewed roller from the axis of rotation. The first resilient member is attached to the first annular friction disk and is configured to bias the first annular friction disk toward an input shaft. The second resilient member is configured to bias the skewed roller disk toward the second annular friction disk.

Asymmetric mechanical torque limiter

A gear device for a gear system for an aircraft includes: an input stage epicyclic gear comprising an input stage sun, an input stage carrier and an input stage ring; and an output stage epicyclic gear comprising an output stage sun, an output stage carrier and an output stage ring. A first input stage component of the input stage sun, the input stage carrier and the input stage ring is fixed to a corresponding first output stage component of the output stage sun, the output stage carrier and the output stage ring, wherein a second input stage component of the input stage sun, the input stage carrier and the input stage ring is fixed to a corresponding second output stage component of the output stage sun, the output stage carrier and the output stage ring. The second input stage component is different from the first input stage component.

Gear device

An electromechanical actuator comprises: a motor; a gearbox; an anti-extension device mounted between the motor and the gearbox. The motor and anti-extension device are mounted on a housing of the actuator. The actuator further comprises a screw shaft; a nut mounted on the screw shaft; an output rod connected to the nut, the output rod having a linear range of motion defined between full extension of the output rod at a first end point (A) and full retraction of the output rod at a second end point (C). The screw shaft, nut, and output rod are located in a cavity of the housing. The output rod and nut are held against rotation relative to the housing, such that rotation of the screw shaft drives the output rod to move linearly within the housing.

Spoiler actuator

A device for selectively transmitting torque between an input shaft and an output shaft includes: a first plurality of friction disks configured to rotate with the input shaft; a second plurality of friction disks configured to rotate with the output shaft and interdigitated with the first plurality of friction disks; a plurality of roller disks wherein each of the plurality of roller disks includes a first disk-to-roller interface with one of the first plurality of friction disks and a second disk-to-roller interface with one of the second plurality of friction disks; a first resilient member configured to provide a force (F) through the first and second plurality of friction disks and roller disks; a solenoid configured to overcome the force (F) from the resilient member when energised. the device may be selectively placed in one of a first mode and a second mode depending on torque requirements.

Torque transmission device

An electromechanical actuator, EMA, having a plurality of modes. The EMA includes a housing, a motor fixed relative to the housing, the motor having an output shaft, the output shaft defining an axis (X) of the EMA and a first sun gear connected for rotation with the output shaft. The system includes an output arranged to be driven by rotation of the first sun gear, wherein the output is arranged to have a neutral position and to be movable away from the neutral position within a positive quadrant and away from the neutral position within a negative quadrant and a ratchet comprising a ratchet wheel and a pawl. The system also has a torque limiter having a predetermined torque limit and arranged to limit torque transfer between the first sun gear and the output.

Electromechanical actuator

An electromechanical actuator (EMA) assembly. The assembly includes: an electric motor; a drive shaft in engagement with the motor to be rotated about a shaft axis by operation of the motor; an output ring around the drive shaft, the output ring caused to rotate with rotation of the drive shaft, the output ring configured to be connected, in use, to a load to be driven by the EMA; a gear assembly between the drive shaft and the output ring to transmit rotation of the drive shaft to rotation of the output ring at a gear ratio. The gear assembly comprises a sun gear in engagement with the drive shaft, an outer gear in engagement with the outer ring, and planetary gears rotating between and transmitting rotation between the sun gear and the outer gear; and a planet carrier plate mounted to the planetary gears to rotate with the planetary gears.

Rotary EMA

A system includes an electrically-actuated clutch arranged to selectively connect a shaft to a motor shaft. Ratchets brake the shaft against rotation in either direction when the output is not within either of the predetermined ranges. Thus, when the motor shaft is connected, via the clutch, to the shaft, the ratchets may act as a brake on the motor shaft.

Runaway emergency actuator brake

An assembly is provided for an aircraft. This aircraft assembly includes an aircraft control surface and a hydraulic actuator. The hydraulic actuator includes a housing and a piston within the housing. The housing is formed integral with the aircraft control surface.

Aircraft control surface with integrated hydraulic actuator

An electromechanical actuator (EMA) includes a plurality of modes and includes an electrical motor having a motor shaft extending along an axis (A) and that drives the shaft to rotate about the axis and a gear assembly mounted around, and in geared connection with the shaft, to rotate with the shaft. The EMA output is 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. The EMA also includes a synchroniser comprising a first conical portion connected to an end of the motor shaft, and a second conical portion connected to a ratchet. The synchroniser has an engaged position and a disengaged position.

A strain wave gear mechanism includes: a casing; an elliptical drive shaft; an outer ring arranged coaxially around the elliptical drive shaft and rotationally fixed to the casing, the outer ring having a toothed inner circumference; a flexible ring mounted around the elliptical drive shaft radially inwards of the outer ring, the flexible ring having a toothed outer circumference. Rotation of the elliptical drive shaft causes elliptical rotation of the flexible ring relative to the outer ring such that teeth of the flexible ring engage with teeth of the outer ring at points corresponding to the major axis of the ellipse of the drive shaft to cause movement of the flexible ring in a direction opposite to rotation of the drive shaft. The outer ring is rotationally fixed to the casing via a solenoid operated disconnect gear configured to selectively disconnect the outer ring from the casing.

Strain wave gearing

An actuator system includes a motor and an actuator positioning member to be driven by the motor from a start position to an actuated position. The system also includes a harmonic drive assembly between the motor and the actuator positioning member arranged to transfer torque from the motor to the actuator positioning member at a gear ratio of greater than 1:1. The system further includes means for disconnecting the harmonic drive assembly in response to failure of the motor and/or torque transfer such as to allow the positioning member to return to the start position.

Actuator assembly

An assembly is provided for an aircraft. This aircraft assembly includes an aircraft control surface. The aircraft control surface includes a first skin, a second skin and a support structure laterally between and connected to the first skin and the second skin. The support structure includes a spar, a first stiffener and a second stiffener. The spar extends spanwise within the aircraft control surface. The first stiffener extends longitudinally within the aircraft control surface to the spar. The second stiffener extends longitudinally within the aircraft control surface to the spar. An actuator receptacle projects longitudinally into the aircraft control surface from a base of the aircraft control surface to the spar. The actuator receptacle extends spanwise within the aircraft control surface between the first stiffener and the second stiffener.

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Paris, France

Karl Potier