Airbus France

Airbus Operations (s.a.s.)

Stephane Machado

Jerome Cassagne

Yvon Martin

Anthony Del Blanco

Arnaud Chambreuil

Fabien Raison

Stephane Romani

Julien Cayssials

Nicolas Voyer

An aircraft engine pylon aft aerodynamic fairing includes upper spars, transverse stiffening ribs, lower spars and a trailing edge where the upper spars and lower spars join together. In this fairing, a profiled structure is formed according to a profile open to the outside of the fairing. In a first end portion, the profiled structure comes to be enclosed between an end portion of the lower spars and the ends of at least one transverse stiffening ribs flush with the lower spars. This structure extends between the lower spars and the upper spars over a straight central portion inclined relative to the first end portion, and comes in a second end portion flush against a portion of the upper spars, parallel to the first end.

Aircraft engine pylon AFT aerodynamic fairing

A fire extinguisher device for aircraft has a hanger structure and a reservoir of extinguishing agent, the aforementioned reservoir being hung beneath the aforementioned hanger structure by metal fittings held by fasteners to the aforementioned hanger structure. The aforementioned extinguisher wherein the reservoir has means of suspension and the hanger structure has carriers complementary to the means of suspension, the aforementioned means of suspension and the aforementioned carriers being such that when the fasteners are withdrawn, the reservoir is in a position called the 'intermediate position,' in which the metal fittings are free and the reservoir is suspended by interaction of the means of suspension and the carriers. The disclosed embodiments also relate to a method for fastening such an extinguishing device.

Aircraft fire extinguishing device and mounting method

The present invention relates to a method of manufacture of a group of transverse internal stiffening ribs () for an aerodynamic fairing of an engine mounting device, including:

Method of manufacture by superplastic forming and by fishplating of a rib for an aerodynamic fairing of an aircraft engine mounting pylon

The present invention relates to a method of manufacture of a stiffening transverse internal rib () for an aerodynamic fairing of an engine mounting device, including:

The invention concerns a device for securing an insert in a structure having a first opening, the insert having a principal body () inserted in the first opening, the body () having a second opening having a principal axis, the device including a shaft () designed to pass through the second opening and at least one detachable or non-detachable head (). According to the invention, this device includes at least one roughly planar part () having a third opening, the part being designed to be positioned on an outer face of the structure () so that the third opening is centered on the second opening for the passage of the shaft (), the part () locking the insert in the first opening, a system for blocking the part () from rotating relative to the principal body (), and an element for joining the head onto the part () for locking the head onto the part, the head being designed to be supported against the part () to secure the part against the outer surface.

Device for securing an insert in a structure

This invention relates to a mounting structure () for mounting an engine () under an aircraft wing (), the structure comprising a rigid structure () and means () of fastening this rigid structure under the wing, the mounting means comprising a forward fastener (), an intermediate fastener () and an aft fastener (). According to the invention, the forward fastener has at least one triangular shackle on each side of a vertical plane passing through a longitudinal axis () of the engine (), placed in a vertical plane oriented along a longitudinal direction (X) of the aircraft. Furthermore, the intermediate fastener comprises a connecting rod capable of transferring forces applied in a direction (Y) transverse to the aircraft, and the aft fastener comprises at least one shackle oriented along a vertical direction (Z) of the aircraft.

Engine mounting structure under an aircraft wing

A structure for mounting a turboprop under an aircraft wing includes a rigid structure and a device for fastening the turboprop on the rigid structure. The rigid structure is composed of a box, and the device for fastening includes at least two lateral connecting rods resisting the engine torque generated by the turboprop, the connecting rods being arranged on each side of the box and each having a forward end connected to a gear box of the turboprop, and an aft end connected to the box.

Structure for mounting a turboprop under an aircraft wing

A mounting structure for mounting a turboprop under an aircraft wing includes a rigid structure provided with an aft underwing box, and at least one forward rigid section. Each forward rigid section has two transverse frames at a spacing from each other. At least one forward rigid section of the rigid structure also includes at least one forward upper box connecting a top part of the two transverse frames of the forward rigid section.

Mounting structure for mounting a turboprop under an aircraft wing

The invention relates to a hanging device () connecting an engine () to a wing () of an aircraft, with the device being made up of a rigid structure () and hanging equipment () interposed between the rigid structure () and the wing (), with the hanging equipment () being made up of a forward attachment () and a rear attachment () made up of at leas one triangular shackle placed in a vertical plane aligned in a transverse direction (Y) of the aircraft. According to the invention, the forward attachment () has, on one side and the other of a vertical plane passing through a longitudinal axis () of the engine (), at least one triangular shackle aligned in the longitudinal direction (X) of the aircraft. Furthermore, the hanging equipment is made up exclusively of forward and rear attachments.

Growing community of inventors

Villeneuve-Tolosane, France

Stephane Machado