Airbus Operations Gmbh

Airbus Operations (s.a.s.)

Nicholas Elliott

Arnaud Didey

Martin Rowlands

Fernando Izquierdo Civera

Simon John Cozens

Daren Payne

John William Griffin

Livier Ben

Julien Decronsonniere

James Cullingham

Christopher Perkins

Martin Griffith Rowlands

Mark Grufferty

An aircraft system for an aircraft, the aircraft system including a controller configured, during a take-off procedure, to determine that a one engine inoperative condition is met and determine that a predetermined take-off criterion is met. The controller is configured, on the basis of a determination that the one engine inoperative condition is met, and prior to receiving a command to retract a landing gear of the aircraft, to initiate automatic opening of a landing gear bay door associated with the landing gear from a closed position towards an open position when the controller determines that the predetermined take-off criterion is met, and inhibit the automatic opening when the controller determines that the predetermined take-off criterion is not met.

Aircraft system

An aircraft system for an aircraft is disclosed having a controller that is configured, during a take-off procedure, to initiate, prior to receiving a command to retract a landing gear, automatic opening of a landing gear bay door associated with the landing gear from a closed position towards an open position, on the basis of a determination, made when a speed of the aircraft is determined by the controller to be equal to or greater than a first threshold speed, that a one engine inoperative condition is met.

An aircraft door controllerincluding a receiverconfigured to receive a commandto move an aircraft door between an open position and a closed position relative to a door frame. The aircraft door controlleris configured to not store the commandwhen power to move the aircraft door between the open position and the closed position relative to the door frame is unavailable.

Aircraft door control

The present invention provides a landing gear assembly for an aircraft landing gear, the assembly comprising a steering mechanism for steering at least one wheel of the landing gear, a deployment mechanism for moving a leg of the landing gear between a stowed position and a deployed position, and an actuator arranged to actuate both the steering mechanism and the deployment mechanism. The invention also provides an aircraft landing gear, an aircraft and methods of operating an aircraft landing gear.

Landing gear assembly

An actuator is arranged to move an aircraft component such as a landing gear leg, flap or aileron between a first position and a second position, net load from external forces acting on the aircraft component tending to drive it towards the first position. The actuator comprises a threaded screw and a threaded nut. A main prime mover is configured to apply torque to the screw or nut acting in opposition to the net load under normal operating conditions. An emergency prime mover is configured to apply torque to the screw or nut acting in the same sense as the net load under emergency operating conditions in which the interface between the nut and the screw has become partially jammed to the extent that the component cannot be moved from the second position to the first position by operation of the net load alone.

Apparatus for use on an aircraft

A linear actuator has a housing, a piston slideable within the housing along a slide axis, a first shaft rotatable about a first axis substantially perpendicular to the slide axis, a second shaft rotatable about a second axis parallel to the slide axis, in which the second shaft and the piston are engaged to convert rotational motion of the second shaft into linear motion of the piston, and in which the first shaft and the second shaft are engaged by a ball-worm gear.

Linear actuator

Actuation apparatus for use on an aircraft

An actuator, comprises a housing, a first prime mover for producing rotary motion, a first gearbox arranged to convert in use the rotary motion from the first prime mover into rotary motion having higher torque and lower speed. The first gearbox comprises a casing mounted for rotation relative to the housing of the actuator and a second gearbox arranged to convert rotary motion of the casing of the first gearbox into rotary motion having lower torque and higher speed. A brake is arranged to act on the rotary motion having lower torque and higher speed from the second gearbox. In use when the first gearbox is not jammed, the brake may be applied to resist relative rotation between the casing of the first gearbox and the housing of the actuator. When the first gearbox is jammed, the brake may be released thereby allowing the casing of the first gearbox to rotate relative to the housing of the actuator. The actuator may thereby be jam-tolerant. A second motor may also be provided.

Jam-tollerant actuator

An actuator includes first and second linear motion devices, each able to extend the actuator and arranged such that jamming of one of the first and second linear motion devices does not preclude operation of the other. The first linear motion device includes a first linear screw, a first nut, and a first prime mover arranged to impart relative linear motion between the screw and nut. Similarly, the second linear motion device includes a second linear screw, a second nut, and a second prime mover arranged to impart relative linear motion between the second screw and nut.

Growing community of inventors

Bristol, United Kingdom

Nicholas Elliott