Abstract: An aircraft including a rear wing attachment, connecting a primary structure of an aircraft pylon to its wing, and including at least one right-hand link connected to the wing by a first right-hand connecting element and to the primary structure by a second right-hand connecting element and configured to react loads oriented parallel to the vertical direction only, at least one left-hand link connected to the wing by a first left-hand connecting element and to the primary structure by a second left-hand connecting element and configured to react loads oriented parallel to the vertical direction only, a shear pin secured to the primary structure and housed in operation in a housing secured to the wing, the shear pin and the housing being configured to react loads oriented in a plane approximately perpendicular to the vertical direction.

Abstract: A cold regulating valve for a heat exchanger system of an aircraft propulsion system, where the cold regulating valve includes an open frame which delimits an opening, two shutters with an external convex shape slidably mounted on the open frame between a closed position and an open position, a mechanism linked to the shutters and mobile between a first position and a second position, and wherein the mechanism moves the shutters from the closed position to the open position when it moves from the first position to the second position and vice versa, and an actuator acting on the mechanism to move it from the first position to the second position and vice versa. The specific embodiment of the cold regulating valve generates a low drag when the shutters are in a closed position.

Abstract: A bulkhead fitting device configured to sealingly link a conduit and a wall traversed by the conduit. This bulkhead fitting device includes a first ring sealingly linked to the conduit, a second ring having a flat, ring-shaped sealing face configured to be pressed against a contact face of the wall or of an intermediate part linked to the wall, an elastically deformable intermediate annular portion sealingly linking the first and second rings, a holding system configured to press the sealing face against the contact face. This bulkhead fitting device guarantees an optimum seal while enabling the absorption of forces and slight relative movements between the conduit and the wall. The device also helps to limit the propagation of vibration.

Abstract: An assembly for an aircraft, the assembly including a pylon with a lateral wall pierced by a window, a tank with a neck blocked by a film and carrying a first anchoring arrangement, and a fixing arrangement for fixing at least a part of the tank bearing the neck inside the pylon, a discharge pipe, and a discharge head. The head includes an explosive cartridge and a hole with a second anchoring arrangement in which discharges the discharge pipe. The discharge head is fixed inside the pylon facing the window. The explosive cartridge is designed to generate in the hole a shockwave sufficient to rupture the film. An assembly of this kind enables simple and rapid removal of the tank from and installation thereof inside the pylon.

Abstract: A propulsion assembly including a turbomachine attached to a pylon, and a fire-fighting system, the turbomachine including fire zones, the fire-fighting system including two reservoirs of pressurized extinguishing agent in the pylon and a distribution line connecting the reservoirs to nozzles. The distribution line includes connected pipes having a low point between the reservoirs and the nozzles, and, for each low point, a fluid drainage device for evacuating fluid. The drainage device includes a fluid passage for fluid evacuation from the distribution line and a mechanism for shutting off the fluid passage, the mechanism movable under effect of distribution line pressure, between a first position where it opens the fluid passage and a second position where it closes the fluid passage, the second position being reached when the pressure in the distribution line is greater than or equal to a predetermined pressure.

Abstract: An aircraft engine attachment connecting an attachment body and a primary structure of an aircraft pylon, the engine attachment comprising a shear pin immobilized in translation by a first immobilization system that comprises a shoulder and a removable stop that are integral with the primary structure, between which a flange of the shear pin is immobilized, and a second immobilization system that comprises a stop plate, connected by at least one removable link to the primary structure, which closes the first hole, at least in part.

Abstract: A rear engine fastener for an aircraft connecting a primary structure and an engine of an aircraft, the rear engine fastener comprising a support configured to be connected to the primary structure, at least one main shackle connected to the support by first and second support link pins, which are symmetrical relative to a vertical longitudinal plane, and to the engine by a first lateral engine link pin and by a central engine link pin, and at least one secondary shackle connected to the engine by a second lateral engine link pin and to the main shackle by a secondary link pin.

Abstract: An assembly for an aircraft including a pylon having a lateral wall with a window passing through it, at least one reservoir, each reservoir being in the shape of an elongate ellipsoid with three semi-axes. The dimension of the reservoir along a first semi-axis differs from the dimension of the reservoir along at least one other semi-axis. The reservoir extends parallel to the semi-major axis, between a first end and a second end. The reservoir is equipped with a discharge head at the second end. The reservoir is equipped with a fastening arrangement disposed on the side of the second end and fastening the reservoir to the pylon. The reservoir is positioned through the window with the first end housed in the pylon and the second end outside the pylon.

Abstract: An aircraft engine attachment connecting an attachment body and a primary structure of an aircraft pylon, the engine attachment comprising a shear pin immobilized in translation by a first immobilization system that comprises a shoulder and a removable stop that are integral with the primary structure, between which a flange of the shear pin is immobilized, and a second immobilization system that comprises, first, a groove positioned in an extension of the shear pin and, second, a fork connected to the primary structure via at least one removable link and interacting during operation with the groove in such a manner as to immobilize the shear pin in translation.

Abstract: An aircraft propulsion system, including a turbojet and a heat exchanger system including a main heat exchanger, a hot air supply pipe and regulating valve, a high pressure pipe bleeding high pressure stage hot air through a first valve, an intermediate pressure pipe bleeding intermediate pressure stage hot air through a second valve, a pipe transferring hot air to an air management system, a main supply pipe supplying fan duct cold air including a main regulating valve, an evacuation pipe expelling air to the outside, a sub heat exchanger, wherein the supply pipe from the regulating valve goes through the sub heat exchanger, a sub supply pipe supplying cold air from the main supply pipe, a sub evacuation pipe expelling air to the fan duct, a temperature sensor measuring hot air temperature exiting the main heat exchanger, and a controller controlling the valves according to the measured temperature.

Abstract: A device for grouping together fuel cells, including at least two fuel cells, a support including a casing, at least one feeder configured to supply the fuel cells with fluid, at least one manifold configured to collect a fluid from the fuel cells, the feeder and the manifold being rigidly secured to the casing and positioned between the casing and the fuel cells.

Abstract: A fire-fighting system for an aircraft, the fire-fighting system having a reservoir having an exterior envelope which delimits an interior volume of the reservoir and an interior wall which extends inside the exterior envelope and separates the interior volume into a first chamber and a second chamber which are separate from one another and are each filled with an extinguishing fluid. A network of pipes, and a valve system are provided which are arranged so as to allow, in succession, the extinguishing fluid to flow from the first chamber to the network of pipes, and then the extinguishing fluid to flow from the second chamber to the network of pipes. Such a fire-fighting system allows simpler installation in the aircraft, the fitting of a single network of pipes and hence a saving in terms of weight and volume.

Abstract: A propulsive assembly for aircraft comprising an engine, a nacelle arranged around the engine and a pylon supporting the engine, the nacelle including two engine cowls and reversing cowls, each cowl having an internal skin, characterized in that at least one of the cowls of the nacelle comprises at least one box arranged in a space situated between the internal skin of the cowl and the engine, the box delimiting a volume of inert material, the inert material being flame retardant foam. This box partially blocks a zone of the engine where a fire is likely to begin, which makes it possible to limit the volume of a fire zone of the engine, and thus reduce the quantity of extinguishing agent which is necessary to extinguish a fire in the zone of the engine concerned.

Abstract: A propulsion assembly including a turbomachine attached to a pylon, and a fire-fighting system, the turbomachine including fire zones, the fire-fighting system including two reservoirs of pressurized extinguishing agent in the pylon and a distribution line connecting the reservoirs to nozzles. The distribution line includes connected pipes having a low point between the reservoirs and the nozzles, and, for each low point, a fluid drainage device for evacuating fluid. The drainage device includes a fluid passage for fluid evacuation from the distribution line and a mechanism for shutting off the fluid passage, the mechanism movable under effect of distribution line pressure, between a first position where it opens the fluid passage and a second position where it closes the fluid passage, the second position being reached when the pressure in the distribution line is greater than or equal to a predetermined pressure.

Abstract: An aircraft propulsion system including a turbojet and heat exchanger system including a heat exchanger. A supply connection and evacuation connection are forward, and aft are a transfer connection and a scoop connection, a supply pipe connected to the supply connection, and which bleeds hot air from the compression stages. A transfer pipe connected to the transfer connection transfers hot air to an air management system. A scoop connected to a scoop connection bleeds cold air from a fan duct and an evacuation pipe, including an inlet connected to the evacuation connection and an outlet, which emerges on the outside, where hot air through the heat exchanger from the supply pipe to the transfer pipe passes along a first transfer direction and cold air passes through the heat exchanger from each scoop to the inlet along a second transfer direction parallel to the first transfer direction in the opposite direction.

Abstract: An aircraft propulsion system, including a turbojet and a heat exchanger system which includes a main heat exchanger, a hot air supply pipe, a transfer pipe transferring hot air to an air management system, a main supply pipe supplying cold air from the fan duct, an evacuation pipe expelling air to the outside, a sub heat exchanger with a high pressure pipe going therethrough, a sub supply pipe supplying cold air and including a sub regulating valve, a sub evacuation pipe expelling air, a temperature sensor, and a controller controlling the system according to the temperature measured The sub regulating valve comprises a door articulated between closed and open positions, a return spring constraining the door in the open position, and a realizing system, controlled by the controller, mobile between a blocking position and a realizing position in which the door is released to move to the open position.

Abstract: A cold regulating valve for a heat exchanger system of an aircraft propulsion system, where the cold regulating valve includes an open frame which delimits an opening, two shutters with an external convex shape slidably mounted on the open frame between a closed position and an open position, a mechanism linked to the shutters and mobile between a first position and a second position, and wherein the mechanism moves the shutters from the closed position to the open position when it moves from the first position to the second position and vice versa, and an actuator acting on the mechanism to move it from the first position to the second position and vice versa. The specific embodiment of the cold regulating valve generates a low drag when the shutters are in a closed position.

Abstract: An assembly for an aircraft, the assembly including a pylon with a lateral wall pierced by a window, a tank with a neck blocked by a film and carrying a first anchoring arrangement, and a fixing arrangement for fixing at least a part of the tank bearing the neck inside the pylon, a discharge pipe, and a discharge head. The head includes an explosive cartridge and a hole with a second anchoring arrangement in which discharges the discharge pipe. The discharge head is fixed inside the pylon facing the window. The explosive cartridge is designed to generate in the hole a shockwave sufficient to rupture the film An assembly of this kind enables simple and rapid removal of the tank from and installation thereof inside the pylon.

Abstract: An aircraft including a rear wing attachment, connecting a primary structure of an aircraft pylon to its wing, and including at least one right-hand link connected to the wing by a first right-hand connecting element and to the primary structure by a second right-hand connecting element and configured to react loads oriented parallel to the vertical direction only, at least one left-hand link connected to the wing by a first left-hand connecting element and to the primary structure by a second left-hand connecting element and configured to react loads oriented parallel to the vertical direction only, a shear pin secured to the primary structure and housed in operation in a housing secured to the wing, the shear pin and the housing being configured to react loads oriented in a plane approximately perpendicular to the vertical direction.

Abstract: An assembly for an aircraft including a pylon having a lateral wall with a window passing through it, at least one reservoir, each reservoir being in the shape of an elongate ellipsoid with three semi-axes. The dimension of the reservoir along a first semi-axis differs from the dimension of the reservoir along at least one other semi-axis. The reservoir extends parallel to the semi-major axis, between a first end and a second end. The reservoir is equipped with a discharge head at the second end. The reservoir is equipped with a fastening arrangement disposed on the side of the second end and fastening the reservoir to the pylon. The reservoir is positioned through the window with the first end housed in the pylon and the second end outside the pylon.