Goodrich Actuation Systems Sas

Rohr, Inc.

Raphael Medina

Karl Potier

Quentin Ricard

Anh-Vu Abdul-Bari

Corentin Boitard

Jennifer Davis

Jerome Socheleau

Maxime Serrand

Gregory Y Meignat

Isabelle Port-Robach

Rui Amaral

Gilles Warrot

Patrice Menanteau

Emmanuel Chavier

Anh Vu Abdul Bari

Patrice Menateau

Quentin Richard

There is provided a lower attachment for a trimmable horizontal stabiliser actuator (THSA) for connecting the THSA to a flight control surface. The attachment includes: a nut assembly for providing a load path through the THSA to the flight control surface when the THSA is connected to the flight control surface. The nut assembly includes a nut for location on a screw shaft of the THSA, a failsafe plate for coupling to the flight control surface, and a transfer plate for transferring load between the failsafe plate and the nut. The nut assembly has a first unloaded configuration in which there is no contact between the nut and the transfer plate, and a second loaded configuration in which there is contact between a first pair of opposed surfaces of the nut and the transfer plate.

Lower attachment for trimmable horizontal stabiliser 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

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

A connector for adjustably connecting an RVDT (rotary variable differential transformer) and a reductor shaft. The connector includes a body defining a bore configured to receive the reductor shaft. The bore has an inner wall and a threaded tightening member which is substantially parallel to a main axis (AA, BB) of the bore. A portion of the body is configured to deform upon tightening of the tightening member such that, when the reductor shaft is received by the bore, the reductor shaft is gripped by at least a portion of the inner wall.

RVDT connector

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.

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.

Aircraft control surface with linear actuator

An assembly for manual control of an HSTA for controlling the position of a moveable surface, the assembly comprising a user-operated manual control element (') e.g. a trim wheel in the cockpit, a first motor and a first resolver connected to the manual control element and a second motor and a second resolver arranged to communicate with the first motor and the first resolver and to cause corresponding movement of the actuator, in use.

Horizontal stabilizer trim actuator assembly

A screw actuator having a screw shaft and a nut arrangement is described herein, the nut arrangement comprising: a primary nut; a first secondary nut having a first thread; a second secondary nut having a second thread; and a first attachment means. The first nut, first secondary nut, and second secondary nut are connected to the first attachment means with a first, initial, axial spacing between the first and second secondary nuts. The first secondary nut is mounted to the first attachment means via bearings that allow the first secondary nut to rotate relative to the first attachment. The first secondary nut is connected to the second secondary nut via a screw thread connection having a pitch lower than a pitch of a screw thread of the screw actuator shaft.

Actuator lower attachment

A trimmable horizontal stabiliser actuator (THSA) control system includes least one main THSA motor for driving the THSA in response to inputs from a flight control computer (FCC), a pilot trim control system for manual control of the THSA by a pilot overriding the FCC. The pilot trim control system comprises a trim control for receiving an input from the pilot, the trim control including a trim control sensor for detecting the input from the pilot and providing a pilot trim control signal; a THSA trim control motor for driving the THSA in response to the pilot trim control signal; and an electronic override system for giving inputs from the pilot priority over inputs from the FCC.

Trim control system

A system for detecting and controlling the position of a spoiler of an aircraft wing is described herein comprising: a hydraulic actuator having a piston rod operably connected to the spoiler, the piston rod being moveable between a retracted position, a neutral position and an extended position; and means for providing power to said hydraulic actuator; and a mechanical device for detecting whether the piston rod is in the retracted position, the neutral position or the extended position; and means, operatively connected to the mechanical device, that is configured to provide a change in a load applied to said hydraulic actuator, wherein said means is configured to change said load based on whether said piston rod is detected as being in said retracted position or said extended position.

Spoiler droop function with mechanical feedback driving hydraulic valve

There is provided an actuator comprising screw shaft and a nut assembly. The nut assembly comprises a primary nut for transmitting load through the actuator along a primary load path, and a secondary nut for transmitting load through the actuator along a secondary load path. The secondary nut comprises first and second portions movable relative to one another. As load is transmitted through the actuator along the primary load path the secondary nut does not transmit load through the actuator, wherein upon failure of the primary load path the first and second portions move relative to each other, such relative movement causing the first and second portions to engage the screw shaft and enable transmittal of load through the secondary nut of the actuator along the secondary load path.

Actuator

An actuator control arrangement includes a hydraulic actuator having a housing and a piston rod axially moveable within the housing, a stop disposed within the housing to limit the extent of movement of the piston rod into the housing, and a solenoid valve arranged between a pressure source and the actuator. The solenoid valve is switchable between a first mode and a second mode in response to an electric control signal, wherein, in the first mode, the solenoid valve creates a fluid flow path from the pressure source to the actuator so as to locate the stop in its neutral position and in the second mode, the solenoid valve creates a fluid flow path to release pressure from the actuator to permit the stop to move to its retracted position. In the event of electrical failure, the stop will set the actuator to its neutral position.

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Ecouen, France

Raphael Medina