Abstract: 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.

Abstract: A wing panel actuator assembly includes: an actuator housing; an actuator piston arranged in the actuator housing and axially movable relative to the actuator housing; a connecting rod attached, at one end, to an end of the piston extending from the actuator housing; the actuator housing and piston arranged to be accommodated inside a movable panel of an aircraft wing. The connecting rod is arranged to be attached, in use, at its end opposite the one end attached to the piston, to a wing structure of the aircraft wing, the panel being pivotable about a pivot point P relative to the wing structure by means of the actuator piston.

Abstract: 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.

Abstract: 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.

Abstract: A system for controlling a flight control surface includes a first electromagnetic actuator “EMA” and a second EMA, each of which are connected to said flight control surface. Each EMA is configured to be arranged in, and switched between, three modes; said three modes comprising: an active mode, a stand-by mode and a blocked, or anti-extension, mode.

Abstract: An accumulator assembly for providing hydraulic fluid to an actuator. That assembly includes an accumulator for containing a supply of hydraulic fluid, the accumulator having an exit port via which hydraulic fluid can flow, in use, to the actuator. The assembly also includes a coupling comprising a first coupling part configured to be located at an inlet port of the actuator and a second coupling part arranged at the exit port of the accumulator. The first and second coupling parts are configured to matingly engage to form an open passage for flow of the fluid-between the accumulator and the actuator, and to close the first coupling part when the first second coupling parts are not engaged, so as to prevent flow from the actuator and to prevent air and pollution ingress the actuator.

Abstract: A system for controlling an electromechanical actuator of an aircraft includes a locking device configured to mechanically lock said actuator in a first fixed position and to mechanically unlock said actuator from said first fixed position and a controller configured to be in bi-directional communication with both said locking device and said actuator. The controller is configured to monitor a position of said actuator during flight and to detect when said actuator has not moved for a set amount of time, said controller further being configured to instruct said locking device to lock said actuator in said first, locked position when said set time has been reached. In addition, there is provided a method for controlling the thermal properties of an electromechanical actuator of an aircraft.

Abstract: There is provided a method of manufacturing a housing configured to hold an actuator and an electronic control unit for the actuator. The method comprises additively manufacturing the housing as a single piece, wherein the housing comprises a central portion configured to house the actuator, and one or more side portions configured to house components of the electronic control unit.

Abstract: An electrohydrostatic actuator, comprising an actuator for driving a component, a pump configured to pump hydraulic fluid for operation of the actuator, and a control valve for controlling passage of the hydraulic fluid between the actuator and the pump, wherein the control valve is movable between first and second positions. In the first position the control valve is configured to convey hydraulic fluid from the pump through the control valve for operation of the actuator, and in the second position the control valve is configured to fluidly disconnect the pump and the actuator, and circulate hydraulic fluid arriving from the pump back to the pump via a first constriction within the control valve.

Abstract: A system for controlling an electromechanical actuator of an aircraft includes a locking device configured to mechanically lock said actuator in a first fixed position and to mechanically unlock said actuator from said first fixed position and a controller configured to be in bi-directional communication with both said locking device and said actuator. The controller is configured to monitor a position of said actuator during flight and to detect when said actuator has not moved for a set amount of time, said controller further being configured to instruct said locking device to lock said actuator in said first, locked position when said set time has been reached. In addition, there is provided a method for controlling the thermal properties of an electromechanical actuator of an aircraft.

Abstract: The invention provides a stator for an electric motor comprising a plurality of radially inwardly extending teeth and comprising conductive material incorporated in one or more of the teeth.

Abstract: A mode valve includes a spool axially moveable within a sleeve in response to a control (e.g. hydraulic or electro-mechanical) command. The spool includes channels and lands, and the sleeve comprising ports in fluid communication with a hydraulic fluid supply and ports in connection with control chambers of an actuator responsive to the valve. The valve also includes first drive means for moving the spool, relative to the sleeve, between a first position, and a second position in which fluid flow from the fluid supply to the actuator chambers through the valve is blocked and wherein a fluid path with a first pressure drop is defined in the mode valve for fluid flow between actuator chambers; the mode valve comprising second drive means for moving the spool relative to the sleeve to a third position in which fluid flow from the fluid supply to the actuator chambers is blocked.

Abstract: A hydraulic circuit comprising an actuator having an extension chamber and a retraction chamber, a bypass passage provided in the hydraulic circuit between defined between the extension chamber and the retraction chamber, and a damping device. The damping device includes first and second chambers separated by a wall, a first movable element received within the first chamber and a second movable element received within the second chamber. The first moveable element is movable from its closed position against the force of the first spring by entry of fluid into the second chamber, and the second movable member being movable from its closed position against the force of the second spring by entry of fluid into the first chamber.

Abstract: There is provided a method of manufacturing a housing configured to hold an actuator and an electronic control unit for the actuator. The method comprises additively manufacturing the housing as a single piece, wherein the housing comprises a central portion configured to house the actuator, and one or more side portions configured to house components of the electronic control unit.

Abstract: An electrohydrostatic actuator, comprising an actuator for driving a component, a pump configured to pump hydraulic fluid for operation of the actuator, and a control valve for controlling passage of the hydraulic fluid between the actuator and the pump, wherein the control valve is movable between first and second positions. In the first position the control valve is configured to convey hydraulic fluid from the pump through the control valve for operation of the actuator, and in the second position the control valve is configured to fluidly disconnect the pump and the actuator, and circulate hydraulic fluid arriving from the pump back to the pump via a first constriction within the control valve.

Abstract: The invention provides a stator for an electric motor comprising a plurality of radially inwardly extending teeth and comprising conductive material incorporated in one or more of the teeth.

Abstract: A hydraulic circuit comprising an actuator having an extension chamber and a retraction chamber, a bypass passage provided in the hydraulic circuit between defined between the extension chamber and the retraction chamber, and a damping device.