Airbus Operations (s.a.s.)

Airbus Operations Gmbh

Mathieu Bonnet

Laurent Lafont

Frederic Journade

Eric Renaud

Frédéric Journade

Benoit Valery

Esteban Quiroz-Hernandez

Jean-Michel Saucray

Jerome Antypas

Jean Michel Saucray

Benoît Valery

A link device for safety linking of a first member to a second member includes a first element, a second element, and a fluidic vibration transfer mechanism. The first element includes a first link end adapted to be directly linked to the first member, and a second link end adapted to be directly linked to the second member. The second element has a first link end adapted to be directly linked to the first member, and a second link end adapted to be directly linked to the second member. The fluidic vibration transfer mechanism links the first and second elements of the link device to one another, and includes at least two pressure chambers filled with a pressurized liquid, separated by at least one piston integral with the first or second element.

Safety link device and aircraft equipped with such a safety link device

A structural rod has a primary rod that has an axial cavity and a secondary rod inside the axial cavity so that the secondary rod is able to move inside the axial cavity along the direction of the longitudinal axis of the rod. The primary rod has a bearing for fastening the structural rod at the first end in a rigid manner and is not fastened rigidly to the structure at the second end. Conversely, the secondary rod has a bearing for fastening the structural rod at the second end in a rigid manner and is not fastened rigidly to the structure at the first end. The primary and secondary rods are joined through one or more intermediate linkage elements made of a deformable and elastic material.

Structural rod incorporating a vibration filtration mode

The invention relates to a system for attaching an element () capable of vibrating onto an aircraft structure (), comprising at least one pair of scoops () attached onto the element capable of vibrating, as well as onto the structure, each scoop () of the pair of scoops comprising: an outer rigid element () attached onto the structure; an inner rigid element () mounted inside the outer rigid element and rigidly connected to the element capable of vibrating; and a flexible element () placed along each outer rigid element flank, between the outer rigid element and the inner rigid element.

System for attaching an impeller engine

An assembly for connecting a first body to a second body includes a first element having a connection end to the first body and a first tubular portion, and a second element having a connection end to the second body and a second tubular portion extending along the longitudinal axis. The first tubular portion and the second tubular portion are interlocked by at least one complementary tubular portion nested in the first tubular portion and around the second tubular portion. A rigid piece connects the first body to the second body and is fastened to the first and second bodies. One of the first and second bodies is connected with functional play at one of the two attachment points of the rigid connecting piece, wherein the rigid connecting piece is formed of two flat rigid pieces extending on both sides of the first and second elements along the longitudinal axis.

Linking device for linking a first body to a second body, in particular for an aircraft engine assembly

An attaching system for attaching two components together, such as an aircraft engine and a mounting pylon, includes front trunnions and rear trunnions for supporting the aircraft engine. In this attaching system, at least two of the front or rear trunnions are vibration damping type trunnions that include a suspension assembly with an elastic element and resonant mass. The suspension assembly is shaped as a bent arm carrying the resonant mass on a free end and associated with the elastic element on another end. The vibration damping type trunnions also include a shackle attached between the engine and the suspension assembly so that the vibration damping type trunnions minimize any vibrations and efforts that would otherwise be applied to aircraft structure via the pylon.

System for attaching two components together, such as an aircraft engine and the mounting pylon thereof

A rear part of an aircraft including two connecting rods positioned symmetrically on either side of a median vertical plane, wherein each connecting rod has an end mounted on a support structure of the engines and another end mounted on the fuselage, wherein this part is configured to allow, by rotation of the connecting rods around their axes of rotation, an oscillating movement of limited amplitude of the assembly formed by the support structure and the engines, relative to the fuselage, through the first and second fuselage openings.

Growing community of inventors

Toulouse, France

Mathieu Bonnet