Abstract: A propulsion unit, for an aircraft, comprising a hollow chassis with an opening at the bottom, a propulsion system comprising an electric motor with a propeller, a fuel cell, a tank and a cooling system, and one platform fastened to the chassis through said opening using fasteners and in which at least one element of the propulsion system is fastened to the platform. An aircraft with such a propulsion unit.

Abstract: A propulsion system includes a system for producing electricity that supplies electricity to at least one electric motor to which is mechanically coupled a propeller situated near a first longitudinal end of a nacelle that houses at least the system for producing electricity and the at least one electric motor. An air circulation channel, which receives a heat exchanger provided to allow the system for producing electricity to be cooled, extends inside the nacelle from a first end of the air circulation channel situated at the first longitudinal end of the nacelle. A part of the air circulation channel that is contiguous with its first end is delimited by an outer surface of cylindrical shape that surrounds the longitudinal axis of the nacelle.

Abstract: An aircraft pylon comprising a primary structure and a pipe segment having an internal duct positioned inside at least one structural tube primary structure. This solution makes it possible to reduce the crowding outside the structural tubes of the primary structure, makes it easier to integrate other equipment inside the pylon, and may help to improve the aerodynamic performance of the pylon by reducing its cross section.

Abstract: A propulsion assembly for an aircraft, the propulsion assembly having a pylon configured to be fastened beneath a wing of the aircraft, a turbomachine having a longitudinal direction, a median plane and a transverse plane, and a nacelle surrounding the turbomachine and having a load support disposed in the top part of the nacelle. The load support has a structural part fastened to the pylon and an aerodynamic part capping the structural part. The aerodynamic part has, at the front, a front part fastened to the structural part and, at the rear, a rear part fastened to the pylon. Separating the load support into two parts makes it possible to reduce the movements of the aerodynamic part capping the structural part of the load support.

Abstract: A propulsion system includes a system for producing electricity that supplies electricity to at least one electric motor to which is mechanically coupled a propeller situated near a first longitudinal end of a nacelle that houses at least the system for producing electricity and the at least one electric motor. An air circulation channel, which receives a heat exchanger provided to allow the system for producing electricity to be cooled, extends inside the nacelle from a first end of the air circulation channel situated at the first longitudinal end of the nacelle. A part of the air circulation channel that is contiguous with its first end is delimited by an outer surface of cylindrical shape that surrounds the longitudinal axis of the nacelle.

Abstract: An aircraft pylon comprising a primary structure and a pipe segment having an internal duct positioned inside at least one structural tube primary structure. This solution makes it possible to reduce the crowding outside the structural tubes of the primary structure, makes it easier to integrate other equipment inside the pylon, and may help to improve the aerodynamic performance of the pylon by reducing its cross section.

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: An aircraft nacelle which comprises a structure, an upstream cowl, an upper cowl arranged to the rear of the upstream cowl and having a starboard-side door and a port-side door, each being articulated between a closed position and an open position, each having a front edge, a rear edge, an inner edge and an outer edge. The nacelle comprises, for each door, an articulation and a locking system. Each door is articulated at the level of its outer edge and, in the closed position, the inner edge of one door is contiguous with the inner edge of the other door. Such a nacelle makes the technicians' work easier because the two articulated doors can be opened wide and give easy access under the cowl.

Abstract: A propulsive assembly of an aircraft comprises a junction fairing, ensuring a continuity between a nacelle and a pylon, which comprises a fixed frame, linked to the nacelle and/or to the pylon by a link system configured to absorb any deformations and/or misalignments between the nacelle and the pylon in operation, which has an outer wall comprising an opening, a cowl, mobile between a closed position in which the cowl blocks the opening, and an open position in which the cowl at least partially frees the opening, which has a panel, the outer wall of the fixed frame and the panel of the cowl having outer surfaces which form the aerodynamic surface of the junction fairing. An aircraft is also provided which comprises at least one such propulsive assembly.

Abstract: A turbomachine assembly comprising a nacelle having an air inlet and comprising a structure. A forward hood is fixed to the structure and extends backwards from the air inlet. An articulated hood is arranged in the upper part of the nacelle and at the rear of the forward hood and comprises a front edge arranged at the front of the articulated hood. A rear edge is arranged at the rear of the articulated hood. A joint is disposed at the front edge between the articulated hood and the structure and ensures a displacement of the articulated hood between a closed position and an open position. A locking system is arranged at the rear edge, and is mobile between a locked position and an unlocked position, where in the closed position, the front edge is under the forward hood.

Abstract: A propulsion assembly for an aircraft, the propulsion assembly having a pylon configured to be fastened beneath a wing of the aircraft, a turbomachine having a longitudinal direction, a median plane and a transverse plane, and a nacelle surrounding the turbomachine and having a load support disposed in the top part of the nacelle. The load support has a structural part fastened to the pylon and an aerodynamic part capping the structural part. The aerodynamic part has, at the front, a front part fastened to the structural part and, at the rear, a rear part fastened to the pylon. Separating the load support into two parts makes it possible to reduce the movements of the aerodynamic part capping the structural part of the load support.

Abstract: A rear engine attachment system for an aircraft engine. The attachment system has an engine pylon with a lower spar having a lower surface, and a rear engine attachment having a beam fixed against the lower surface and to which a pair of rods is fixed. Each rod is fixed to the beam by at least one first connection point and to the engine by at least one second connection point. The beam includes front and rear fittings, and an intermediate fitting with a shoe and an intermediate clevis. The shoe presses against the lower surface. The front fitting presses against the intermediate fitting at the front and the rear fitting presses against the intermediate fitting at the rear. The fixing to the lower spar is ensured by bolts, each passing through the front base or the rear base, the shoe and the lower spar.

Abstract: A propulsive assembly of an aircraft comprises a junction fairing, ensuring a continuity between a nacelle and a pylon, which comprises a fixed frame, linked to the nacelle and/or to the pylon by a link system configured to absorb any deformations and/or misalignments between the nacelle and the pylon in operation, which has an outer wall comprising an opening, a cowl, mobile between a closed position in which the cowl blocks the opening, and an open position in which the cowl at least partially frees the opening, which has a panel, the outer wall of the fixed frame and the panel of the cowl having outer surfaces which form the aerodynamic surface of the junction fairing. An aircraft is also provided which comprises at least one such propulsive assembly.

Abstract: An aircraft nacelle which comprises a structure, an upstream cowl, an upper cowl arranged to the rear of the upstream cowl and having a starboard-side door and a port-side door, each being articulated between a closed position and an open position, each having a front edge, a rear edge, an inner edge and an outer edge. The nacelle comprises, for each door, an articulation and a locking system. Each door is articulated at the level of its outer edge and, in the closed position, the inner edge of one door is contiguous with the inner edge of the other door. Such a nacelle makes the technicians' work easier because the two articulated doors can be opened wide and give easy access under the cowl.

Abstract: A turbomachine assembly comprising a nacelle having an air inlet and comprising a structure. A forward hood is fixed to the structure and extends backwards from the air inlet. An articulated hood is arranged in the upper part of the nacelle and at the rear of the forward hood and comprises a front edge arranged at the front of the articulated hood. A rear edge is arranged at the rear of the articulated hood. A joint is disposed at the front edge between the articulated hood and the structure and ensures a displacement of the articulated hood between a closed position and an open position. A locking system is arranged at the rear edge, and is mobile between a locked position and an unlocked position, where in the closed position, the front edge is under the forward hood.

Abstract: The invention refers to a suspension pylon (4) for an aircraft engine (2), the pylon including a rigid structure (10) forming a box provided with a lower spar (28) and an upper spar (26), and an engine mounting system (11) installed fixed on the structure (10) and in particular including a forward attachment (6) with an attachment body provided with a horizontal fixing surface (40) held in contact with a horizontal fixing surface (38) of the structure (10). According to the invention, the attachment body is arranged such that its horizontal fixing surface (40) is located along a vertical direction (Z) of the pylon, upwards from a forward end (28a) of the lower spar and downwards from a forward end (26a) of the upper spar. Furthermore, the structure (10) includes at least one forward fitting (42a, 42b) making up a forward closing rib (36) of the box, this fitting (42a, 42b) defining said horizontal fixing surface (38).

Abstract: The invention refers to a suspension pylon (4) for an aircraft engine (2), the pylon including a rigid structure (10) forming a box provided with a lower spar (28) and an upper spar (26), and an engine mounting system (11) installed fixed on the structure (10) and in particular including a forward attachment (6) with an attachment body provided with a horizontal fixing surface (40) held in contact with a horizontal fixing surface (38) of the structure (10). According to the invention, the attachment body is arranged such that its horizontal fixing surface (40) is located along a vertical direction (Z) of the pylon, upwards from a forward end (28a) of the lower spar and downwards from a forward end (26a) of the upper spar. Furthermore, the structure (10) includes at least one forward fitting (42a, 42b) making up a forward closing rib (36) of the box, this fitting (42a, 42b) defining said horizontal fixing surface (38).

Abstract: This culture dish comprises an axisymmetric receptacle (1) having a bottom on which is disposed a layer (2) of a culture medium and a movable lid (5), covering the receptacle (1) and having an internal face from which emerges a spreader (9), and structures associated with the receptacle and lid making it possible to transfer the lid (5) from a depositing position in which the spreader (9) is distant from the layer (2) to a spreading position in which it touches the layer (2), and which the structures are arranged such that the transfer requires two movements, in different directions, with respect to the receptacle (1), to be imparted to the lid (5).