Abstract: An aircraft propulsion assembly including an engine unit, a primary structure of the pylon, a nacelle surrounding a rear part of the engine unit, an engine mount system which includes a load-bearing structure positioned between the engine unit and the nacelle, a first connecting system of the rigid type, connecting the front end of the load-bearing structure and the front part of the engine unit, a second connecting system of the rigid type connecting the load-bearing structure and the primary structure, at least one rear damping engine mount interposed between the rear part of the engine unit and the nacelle.

Abstract: An aircraft propulsion assembly including an engine assembly that includes front and rear parts offset along a longitudinal axis, a primary structure of a pylon, at least one supporting structure that extends along the longitudinal axis, separate from the rear part and connected to the front part of the engine assembly, an engine-attachment system that includes at least one front attachment directly connecting the engine assembly and the primary structure, and at least one rear attachment offset toward the rear relative to the front attachment connecting the primary structure and the supporting structure.

Abstract: An aircraft propulsion assembly including: an engine assembly that has front and rear parts offset along a longitudinal axis, a primary structure of the pylon, at least one supporting structure that extends along an axis parallel to the longitudinal axis, connected to the front part of the engine assembly, supporting at least one accessory, an engine-attachment system that includes: at least one front attachment directly connecting the engine assembly and the primary structure, at least one rear attachment offset toward the rear relative to the front attachment connecting the primary structure 42 and the supporting structure.

Abstract: A propulsion system includes an engine, a pylon box, and a structural attachment. The engine includes an engine casing and an engine core. The pylon box has a front part and a rear part. The rear part is configured to attach the engine to an aircraft structure. The structural attachment has a front end configured to attach to the engine casing and a rear end configured to attach to the pylon which allows load transfer to the aircraft structure through the pylon box.

Abstract: An aircraft comprising at least one propulsion assembly and at least one pylon, the propulsion assembly comprising at least one cowl, connected by at least one first articulation to a fixed support, comprising a curved main part and a secondary lateral fairing which is positioned in the extension of a main lateral fairing of the pylon when the cowl is in the closed position. The secondary lateral fairing comprises at least first and second parts movable relative to each other, the first part being connected to the main part of the cowl.

Abstract: An internal fixed structure for a nacelle, comprising end panels, an intermediate panel in the form of a half-cylinder between the end panels, splice plates between the intermediate panel and each end panel, wherein each splice plate is made up of a skin with an inner face fastened to the panels and at least one indentation protruding with respect to an outer face, and a pad fastened to each fastening surface of an indentation, wherein each pad of the upper splice plate bears against a surface of an engine pylon, and wherein each pad of the lower splice plate bears against a pad of a lower splice plate of another internal fixed structure.

Abstract: A method for manufacturing an intermediate resistive membrane, called a “septum”, with tubular guides for a DDOF (double degree of freedom) acoustic treatment panel. The method includes the membrane and the tubular guides being manufactured by the same operation of injecting a resin around a substrate placed between two parts of an injection mold.

Abstract: A method for manufacturing an intermediate resistive membrane called “septum” with tubular guides for an acoustic treatment panel with double degree of freedom. The membrane and the tubular guides are manufactured by hot stamping a substrate placed between two parts of a stamping press and an additional layer taking the form of a thermoplastic film of small thickness and pre-perforations. Hot air intake may be used for the hot stamping.

Abstract: An aircraft comprising at least one propulsion assembly and at least one pylon, the propulsion assembly comprising at least one cowl, connected by at least one first articulation to a fixed support, comprising a curved main part and a secondary lateral fairing which is positioned in the extension of a main lateral fairing of the pylon when the cowl is in the closed position. The secondary lateral fairing comprises at least first and second parts movable relative to each other, the first part being connected to the main part of the cowl.

Abstract: An internal fixed structure for a nacelle, comprising end panels, an intermediate panel in the form of a half-cylinder between the end panels, splice plates between the intermediate panel and each end panel, wherein each splice plate is made up of a skin with an inner face fastened to the panels and at least one indentation protruding with respect to an outer face, and a pad fastened to each fastening surface of an indentation, wherein each pad of the upper splice plate bears against a surface of an engine pylon, and wherein each pad of the lower splice plate bears against a pad of a lower splice plate of another internal fixed structure.