Airbus Corporation

Airbus Operations (s.a.s.)

Richard Wilby

The disclosed embodiments relate to a fuel line valve for an aircraft, that includes a shell capable of rotation inside the valve body and connected to a driving shaft driven by an electric actuator. The valve further includes a torque generation means and position detection means. The torque generation means are connected to the shell and generate a torque that varies based on the position of said shell in the valve body on the driving shaft. The position detection means provide electric signals characterizing the positions of said driving shaft. The disclosed embodiments also relate to a method for diagnosing the operation of such a valve in order to detect a failure during the operation thereof, and to a device for implementing said method.

Device and method for detecting a failure in a powered valve

A device for locking a movable component of an aircraft. The device includes an electronic tag adapted for receiving a polling signal and returning an identification signal. An on-board system allows detection of such locking devices.

Device for locking a movable component of an aircraft

A rear landing gear for an aircraft includes a strut configured to have a variable height at a lowered position. The strut is variable between a maximum height at which the aircraft has a substantially horizontal trim and a minimum height at which the aircraft has a nose-up trim, and includes a barrel and a shock absorber. The shock absorber bears a set of wheels and is slidably mounted in a passage of the barrel, the passage defining a variable-volume internal fluidic chamber. A source of fluidic power connects to the variable-volume internal chamber via a controllable shut-off member and is configured to fill or empty the variable-volume internal chamber with fluid, varying the height of the strut between the maximum height and the minimum height.

Variable stroke rear landing gear strut

A multiple-sensor device for a gauging system including: an insert configured to be inserted along an axis in a capacitive probe so as to assume a predetermined axial position with regard to the probe; a support on which a plurality of sensors are mounted; and a retaining mechanism to maintain the support at a predetermined distance from the insert along the axis.

Multiple-sensor measuring device for on-board gauging probe

Symmetric external parts of a front lower aircraft wing sweep forward such that lift generated by a rear upper wing is greater than lift generated by the front lower wing. The rear upper wing is in direct contact with rear upper parts of fuselages. A propulsion system of the aircraft has a turboprop engine and is carried by an internal part of the rear upper wing, with the propulsion system lying in a longitudinal mid-plane.

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Pibrac, France

Richard Wilby