Abstract: An aircraft engine assembly has a front engine mount connecting an engine and a primary structure of a pylon comprising at least one front rod having at least three front link points. A first front link point is configured to connect the front rod and the front end of the primary structure. A second front link point is configured to connect the front rod and the core of the engine. A third front link point is configured to connect the front rod and the engine core and is offset relative to the second front link point in a horizontal transverse direction. The first front link point of the front engine mount is separated from the rotation axis of the engine by a distance greater than an exterior radius of the rear casing of the core of the engine at the rear link point of the rear engine mount.

Abstract: To bring a pylon box of an aircraft engine attachment pylon as close as possible to a wing box, two lateral front fasteners are provided. Each of the fasteners comprises a clevis secured to the wing box, the clevis comprising two webs, at least one of which passes through an upper spar of the box, the upper part of one of the two opposite lateral flanges of a lower transverse rib of the box reinforcement, the upper part of an associated lateral panel, and a pin system passing through the clevis and the two upper parts.

Abstract: A fireproof and thermal insulator product, which comprises a material combination of an Earth Silicate material, and alumina, such that the alumina is bonded onto the Earth Silicate material or is diffused inside the Earth Silicate material.

Abstract: To bring a pylon box of an aircraft engine attachment pylon as close as possible to a wing box, two lateral front fasteners are provided. Each of the fasteners comprises a clevis secured to the wing box, the clevis comprising two webs, at least one of which passes through an upper spar of the box, the upper part of one of the two opposite lateral flanges of a lower transverse rib of the box reinforcement, the upper part of an associated lateral panel, and a pin system passing through the clevis and the two upper parts.

Abstract: An aircraft engine assembly has a front engine mount connecting an engine and a primary structure of a pylon comprising at least one front rod having at least three front link points. A first front link point is configured to connect the front rod and the front end of the primary structure. A second front link point is configured to connect the front rod and the core of the engine. A third front link point is configured to connect the front rod and the engine core and is offset relative to the second front link point in a horizontal transverse direction. The first front link point of the front engine mount is separated from the rotation axis of the engine by a distance greater than an exterior radius of the rear casing of the core of the engine at the rear link point of the rear engine mount.

Abstract: An aircraft air conditioning system includes a main air conditioning device which taps air off a turbine engine, and an auxiliary unit with a compressor that taps ambient air and conditions it to send to a distributing device in place of a main device, when the aircraft is in cruising flight or close to cruising flight.

Abstract: According to the invention, on at least one of the faces (1E, 1I) of said leading edge (1), forward of the partition (3), an action is exerted on the fluid flow (EF) so as to cause the latter to switch from the laminar state (EFL) to the turbulent state (EFT) in order to increase the thermal exchanges and minimize the thermal stresses on said leading edge.

Abstract: An aircraft recovers the energy of conditioned air as it passes from a conditioned zone to outside the aircraft and uses the recovered energy to air condition the aircraft.

Abstract: An air exhaust device is equipped with a grid (10) that is connected to an aerodynamic surface of an aircraft, whereby the grid includes a number of openings that are delimited by separating zones that are arranged in the extension of the aerodynamic surface of the aircraft, whereby the device and the grid are characterized by a surface that makes possible the passage of the air called passage surface, characterized in that it includes at least one movable part so as to increase the passage surface of the device, in particular in the case of a malfunction, and in that the grid (10) has a passage surface that is determined as a function of the flow rate of air that is to be evacuated under the most restrictive conditions of a normal flight, in the absence of a malfunction.

Abstract: According to the invention, in addition to a main air conditioning device (4, 5) which taps air off the turbine engine (2), the invention provides an auxiliary unit (16 to 22) with compressor, which taps ambient air and conditions it to send it to the distributing means (24) in place of the main device (4, 5) when the aircraft is in cruising flight or close to cruising flight.

Abstract: According to the invention, on at least one of the faces (1E, 1I) of said leading edge (1), forward of the partition (3), an action is exerted on the fluid flow (EF) so as to cause the latter to switch from the laminar state (EFL) to the turbulent state (EFT) in order to increase the thermal exchanges and minimize the thermal stresses on siad leading edge.

Abstract: According to the invention, means (11) are provided that are able to recover, when said aircraft is in cruising flight phase or in a flight phase close to cruising, the energy of the release of the conditioned air when the latter passes from the conditioned zone (2) to outside the aircraft and to use the recovered energy in the air conditioning of the aircraft.

Abstract: Rapid-opening door. According to the invention, on its face (1.4) immediately adjacent to the pressurized space (4), the door (1) is provided with a projecting lip (10.2) in the vicinity of its free edge (11), accelerating the opening of said door in the event of decompression of the space (5).

Abstract: Rapid-opening door.

Abstract: Air inlet cowl for a jet engine equipped with deicing means. According to the invention, the hollow leading edge (16) of said cowl (9) comprises a mixer (19) for forming, at each moment, a mixture of the stream of hot air (20) being injected and some, previously injected, of the stream of air that is recirculating. This evens out the temperature inside said leading edge (16), eliminating hot spots and optimizing the de-icing.

Abstract: According to the invention, the hollow leading edge (16) of said cowl (9) comprises a mixer (19) for forming, at each moment, a mixture of the stream of hot air (20) being injected and some, previously injected, of the stream of air that is recirculating. This evens out the temperature inside said leading edge (16), eliminating hot spots and optimizing the de-icing.