Airbus Operations (s.a.s.)

Airbus (Sas)

Airbus Operations Gmbh

Benoît Penven

Frédéric Goupil

Lionel Czapla

Laurent Lafont

Rémi Amargier

Kotaro Fukasaku

Delphine Jalbert

Franck Alvarez

Pascal Pome

Nicolas Jolivet

Jago Pridie

Nicolas Fordos

Milan Tasic

Gautier Destombes

Tanguy Vercamer

Laurent Costagliola

Guillaume Vivien

Hermann Walch

Jean-Victor Lapeyre

Emmanuel Mermoz

A storage tank for a cryogenic fluid including an inner tank that is configured to store the fluid and that is seated in an outer envelope, the inner tank and the outer envelope having a shared longitudinal axis, such that a thermal insulation volume surrounds the inner tank, and wherein the outer envelope surrounds the volume about the inner tank. The tank has at least one damping element made of a deformable material positioned between one end of the inner tank and the outer envelope to wedge the inner tank against the outer envelope. This enables a reliable sliding mechanical link to be formed between at least one end of the inner tank and the outer envelope of the tank, thereby increasing resistance to wear and facilitating assembly of the tank.

Cryogenic tank for an aircraft and aircraft including such a tank

A propulsion unit, and an aircraft, with a propeller and electric motor, including at least one intermediate element interposed between the electric motor and the propeller and configured to transmit at least thrust loads generated by the propeller, a primary structure supporting the propulsion unit, at least one interface having: a first load path, configured to transmit loads perpendicular to the axis of rotation of the propeller, linking the at least one intermediate element to a support linked rigidly to or incorporated in the primary structure, a second load path, configured to transmit loads that are parallel to the axis of rotation of the propeller, linking the at least one intermediate element to a support linked rigidly to or incorporated in the primary structure.

Propulsion unit with propeller and electric motor comprising an adapted primary structure, and aircraft having at least one such propulsion unit

A tank including at least first and second portions connected by a connection ring and weld seams obtained by means of a friction welding method. The connection ring includes at least a first cylindrical portion fitted in the end of the first portion, at least a first shoulder protruding toward the outer zone of the tank relative to the first cylindrical portion and at least a first transverse web positioned approximately in the same transverse plane as the first shoulder. According to this configuration, the first cylindrical portion and the transverse web ensure that the forces generated by a friction welding head during the production of the weld seam which enables the tank to be closed are absorbed.

Tank comprising at least two portions which are connected by means of a connection ring and weld seams which are obtained by means of a friction welding method and production method for the tank

A method for manufacturing structural rods to make it easier to manufacture a structural rod for an aircraft and to improve performance. Each rod includes a rod body and two end portions disposed at either end of the rod body along a longitudinal central rod axis, each end portion comprising at least one mounting lug that protrudes from the rod body along the longitudinal axis. The method includes producing a sandwich panel including two skins gripping a cellular inner body, at least one of the two outer skins having a skin extension for forming a part of the at least one mounting lug of at least one of the two end portions of the rod, and cutting the panel along parallel cutting lines to obtain the structural rods.

Structural rod for an aircraft, comprising a rod body with a sandwich structure

A method for manufacturing a centre wing box which includes inner stiffeners, at least one of which has at least one through-hole is described. For each stiffener having at least one through-hole and having a first leg of a first U-shaped and C-shaped profile and a second leg of a second U-shaped and C-shaped profile, the method includes, for each through-hole, the steps of producing a first section of the through-hole in the first U-shaped or C-shaped profile and of producing a second section of the through-hole in the second U-shaped or C-shaped profile before the first and second U-shaped or C-shaped profiles are positioned on the mould.

Method for manufacturing an aircraft centre wing box including at least one stiffener having at least one through-hole and aircraft centre wing box obtained using said method

Growing community of inventors

Grenade sur Garonne, France

Benoît Penven