Airbus Operations (s.a.s.)

Airbus France

Stephane Levert

Laurent Lafont

Stephane Combes

Jacques Beaufort

Virginie Audart-Noel

The present invention relates to a take-up device for thrust forces () for an aircraft engine attachment pylon (), comprising a first fitting () attached to a rigid structure () of the attachment pylon, and two lateral connecting rods () for take-up of thrust forces. It also comprises an axis system () bearing three first ball joint organs () arranged along the latter and belonging respectively to a primary ball joint () and two secondary ball joints () arranged on either side of the primary ball joint, the first fitting () integrating a second ball joint organ () cooperating with the first organ () of the primary ball joint (), and an end of each of the two connecting rods () integrating a second ball joint organ () cooperating respectively with the first organs () of the two secondary ball joints ().

Take-up device for thrust forces with connecting rods for aircraft engine attachment pylon, integrating three aligned ball joints

A mounting structure for an aircraft engine including a rigid structure and a mechanism to mount the engine on the rigid structure. The mounting mechanism includes a thrust load device including two side thrust links each including an aft end mounted on an evener bar of the device, via a mechanical connection. Each connection is formed by a lug provided on the evener bar and passing through an orifice made in the aft end, the lug being arranged so as to extend substantially laterally relative to the mounting structure.

Aircraft engine mount structure comprising two thrust links with transverse fitting

A nut system including a nut including a main thread with pitch pand arranged along a screwing axis of the nut. A threaded device is coupled in rotation with the nut, the threaded device including a secondary non-screwed thread on the main thread from which it is separated, the secondary thread being arranged along the screwing axis and having a pitch pdifferent from p. Such a nut system may find application with a device for resistance of thrusts generated by an aircraft engine.

Nut system and aircraft engine mounting structure comprising same

A rear suspension () for an aircraft engine assembly comprises a structure comprising two three-point shackles (') and one two-point shackle (). One of the hinge pins in waiting on the two-point shackle (), preferably the hinge pin () fixed to the engine yoke joint, is mounted with clearance and with a damping ring acting as a spring to prevent vibrations of the engines as long as the hinge pin () is not engaged. Each of the suspension connecting pins () is a ball joint connection, the beam () of the suspension () being provided with five aligned orifices (&#x2032;).

Rear suspension for an aircraft engine with shackle in waiting and spring for such a hinge pin in waiting

An engine attachment pylon for an aircraft including an aft engine attachment fitted with an aft attachment body and a first shear pin capable of resisting forces applied along a transverse direction of the pylon. The first pin passes through a lower spar of a rigid structure of the pylon and includes a lower end housed in the aft attachment body. The lower end includes a reaming through which a first pin passes, that also passes through the aft attachment body.

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Toulouse, France

Stephane Levert