Abstract: The invention relates to an acoustic skin (22) for an aircraft nacelle acoustic panel, said skin including a plurality of layers (105, 106) stacked with composite planar bands (102) that are each directed by the direction-defining longitudinal axis (107) thereof, the longitudinal axes (107) of the bands (102) of a single layer (105, 106) being parallel therebetween, said bands (102) of said single layer (105, 106) being spaced from each other so as to have acoustic openings within the acoustic skin. The invention relates to a panel including such a skin, to a method for manufacturing said skin, and to a drape-forming head for implementing the method.

Abstract: The invention relates to an acoustic panel (20) for an ejector nozzle (10) comprising the following main components: an external skin (22) containing acoustic holes (29); an internal skin (23); an acoustic structure (21) comprising alveolar-core cells (27) between the internal skin (23) and the external skin (22). At least one main component selected from the external skin (22), the internal skin (23) and the acoustic structure (21) is formed by a composite material and the acoustic structure (21) is held in contact with either or both of the internal (23) and external (22) skins by compression by elastic means and/or by fixing by mechanical fixing means (24). The invention also relates to an injector nozzle (10) and a nacelle (1) comprising such an acoustic panel (20).

Abstract: Process for manufacturing an acoustic panel for an aircraft nacelle. The invention relates to a process for manufacturing an acoustic panel (1) for a nacelle of an aircraft, said panel (1) comprising a metallic acoustic absorption structure (7) and an acoustic skin (3) having a multitude of acoustic openings (5), said process comprising: - a step A in which a layer (21) is formed that contains a polymerizable insulating material around the acoustic openings (5) of the acoustic skin (3), said insulating material being configured to protect the acoustic absorption structure (7) from corrosion; - a step B in which the layer (21) thus obtained is solidified by polymerization.

Abstract: The invention relates to an acoustic skin (22) for an aircraft nacelle acoustic panel, said skin including a plurality of layers (105, 106) stacked with composite planar bands (102) that are each directed by the direction-defining longitudinal axis (107) thereof, the longitudinal axes (107) of the bands (102) of a single layer (105, 106) being parallel therebetween, said bands (102) of said single layer (105, 106) being spaced from each other so as to have acoustic openings within the acoustic skin. The invention relates to a panel including such a skin, to a method for manufacturing said skin, and to a drape-forming head for implementing the method.

Abstract: The invention relates to a cellular-core structure (10) that can be used in an acoustic panel for a turbojet nacelle, comprising at least one cellular unit (12; 14), each cellular unit (12; 14) comprising two end sheets (18; 20), the end sheets (18; 20) being joined together by joining elements (24) that are placed so as to form cellular cells (32). The subject of the invention is also a method of producing such a structure, an acoustic panel comprising such a structure, and a nacelle comprising such an acoustic panel.

Abstract: The invention relates to an acoustic panel (20) for an ejector nozzle (10) comprising the following main components: an external skin (22) containing acoustic holes (29); an internal skin (23); an acoustic structure (21) comprising alveolar-core cells (27) between the internal skin (23) and the external skin (22). At least one main component selected from the external skin (22), the internal skin (23) and the acoustic structure (21) is formed by a composite material and the acoustic structure (21) is held in contact with either or both of the internal (23) and external (22) skins by compression by elastic means and/or by fixing by mechanical fixing means (24). The invention also relates to an injector nozzle (10) and a nacelle (1) comprising such an acoustic panel (20).

Abstract: The invention relates to a cellular-core structure (10) that can be used in an acoustic panel for a turbojet nacelle, comprising at least one cellular unit (12; 14), each cellular unit (12; 14) comprising two end sheets (18; 20), the end sheets (18; 20) being joined together by joining elements (24) that are placed so as to form cellular cells (32). The subject of the invention is also a method of producing such a structure, an acoustic panel comprising such a structure, and a nacelle comprising such an acoustic panel.