Airbus Operations

Disclosed is an enclosure device configured to enclose a concave surface portion of an aerodynamic component of an aircraft wing. Disclosed also is, an aerodynamic component comprising an enclosure device, and an aircraft wing and aircraft comprising one or more enclosure devices. Also disclosed is a method of counteracting unwanted airflow circulation in a concave surface portion of an aerodynamic component of an aircraft wing.

A fuel mixing assembly comprising, a fuel vessel, such as a pipe 15 for conveying flow of a first fuel; and a second-fuel conduit 17 for conveying flow of, for example an additive, into the fuel vessel 15. The fuel mixing assembly further comprises a vortex generator 21, the vortex generator 21 being configured to generate vortices to mix the first fuel and the additive. The additive may be released from an outlet in the vortex generator 21.

An aircraft maintenance system, method, and computer-readable storage medium are provided. The aircraft maintenance system comprises a processor and storage comprising a digital twin of at least part of an aircraft and a machine learning classifier. The aircraft maintenance system is configured to obtain aircraft operational data, update the digital twin based on the aircraft operational data, identify an altered operation of the aircraft based on the aircraft operational data, and determine a set of conditions responsible for the altered operation using the machine learning classifier to evaluate the digital twin. Output data indicative of the set of conditions responsible for the altered operation is generated.

A composite part for a vehicle is provided. The composite part has a first surface (22a) and an opposing second surface (22b), wherein at least part of the first surface forms an outer aerodynamic surface of a vehicle. A region of the part has a curvature in two orthogonal directions. The part has an undulation (40) defining a channel (60) in one of the first surface or the second surface, and a corresponding ridge (50) in the other of the first surface and the second surface.

This slat cove filling device (24) for a slat (18) of an aircraft (10) comprises a sheltering panel (46) extending along a spanwise direction (Y) and comprising a proximal edge (50), configured for being fastened to a slat body (22) of the slat (18), and a distal edge (52), configured for being slidable relative to the slat body (22),the sheltering panel (46) comprising a plurality of guiding passages, each guiding passage being configured for cooperating with a guiding element of the slat body (22) for guiding the distal edge (52) along a sliding direction (S) relative to the slat body (22).

An aircraft wing comprising: a wing structure supporting a wing cover, the wing cover having an outer aerodynamic surface, which forms part of an aerofoil profile of the wing, and a recess stepped back from the wing aerofoil profile; and a spoiler device comprising a spoiler coupled to the wing structure by a spoiler actuation mechanism for moving the spoiler between a retracted position and a deployed position, the spoiler having a surface which follows a contour of the wing aerofoil profile and where the spoiler is housed entirely in the recess when the spoiler is in the retracted position, and wherein the spoiler surface is extended away from the wing cover when the spoiler is in the deployed position.

Disclosed are a panel element, in particular for use as an aircraft interior part, comprising at least one plate component having a front side and a rear side, and a stiffening structure forming enforced areas of the plate component, wherein the stiffening structure comprises at least an edge protection frame surrounding outer edges of the at least one plate component, and local stiffening elements extending over adjacent surface areas of the front side and the rear side, wherein the stiffening structure is visible in a final state of the panel element on both sides, and an aircraft interior part comprising at least one panel element.

A method of monitoring a landing gear shock absorber (4) comprises monitoring a tyre gas pressure of a landing gear tyre; at a first time, when the aircraft is stationary before a flight, recording a first ambient temperature and a first tyre gas pressure; at a second time, when the landing gear is unloaded during the flight, recording a second tyre gas pressure and a shock absorber pressure; calculating a second ambient temperature at the second time; comparing the recorded shock absorber pressure with a predetermined pressure range for the second temperature; and providing an alert if the recorded shock absorber pressure is outside the predetermined pressure range. This allows a health check of the shock absorber (4) to be performed without the need to directly measure the temperature of the shock absorber (4).

Es werden ein Robotersystem (1) mit wenigstens einem Roboter (2) und wenigstens zwei Roboterarmen (5) sowie ein Verfahren zur Ausführung einer Arbeitsaufgabe mit einem Robotersystem (1) mit wenigstens einem Roboter (2) und wenigstens zwei Roboterarmen (5) vorgeschlagen, die dazu eingerichtet sind, mit wenigstens einem Endeffektor (6) eine Arbeitsaufgabe auszuführen, wobei ein adaptives Sockelmodul (4) an einem Untersatz (3) des wenigstens einen Roboters (2) dazu eingerichtet ist, die wenigstens zwei Roboterarme (5) an ihrer jeweiligen Basis (9a) zu halten und wenigstens zwei verschiedene an die jeweilige Arbeitsaufgabe angepasste Betriebszustände (A, B, C, D) anzunehmen.

An inerting system (22) has an inerting apparatus (44) which receives an inlet air flow and separates it into nitrogen enriched air (NEA) and oxygen enriched air (OEA). The inerting system also has an oxygen concentration sensor (46) and a controller (48) connected to the oxygen concentration sensor (46). The controller (48) adjusts operation of the inerting system (22) during use, based at least in part on feedback received from the oxygen concentration sensor (46).