A method for manufacturing a sound absorption structure comprising a cellular panel, a porous layer positioned on a cellular panel first face, a reflective layer positioned on a cellular panel second face and a plurality of acoustic elements positioned in the cellular panel. The method comprises the steps of producing, for each acoustic element, a recess in the cellular panel opening out onto the first and second faces of the cellular panel, inserting the acoustic elements into their recesses, laying an anchoring layer on the second cellular panel face, curing or polymerization at a first pressure to connect each acoustic element to the cellular panel and/or to the anchoring layer, putting in place the porous layer and the reflective layer, and curing or polymerization at a second pressure to connect the porous layer and the reflective layer to the cellular panel.

An inner barrel may comprise: a perforated top sheet; a backskin; a core disposed between the perforated top sheet and the backskin; and an insulator coupled to the backskin, the insulator comprising a polymeric material.

An aircraft nacelle comprising a first duct secured to an air intake and a second duct secured to a power plant. The two ducts are arranged end-to-end and connected by a connection. The connection comprises a bracket which extends between a first region for connecting to the power plant and a second region for connecting to the air intake, and which comprises a J-shaped profile in longitudinal planes, having at least one curved portion offset towards the outside of the nacelle with respect to the connecting regions.

An acoustic attenuation panel for a turbojet engine nacelle is provided by the present disclosure. The panel includes at least one alveolar core disposed between at least one internal skin and at least one external skin. In one form, the alveolar core includes a plurality of alveoli having a helical-shaped cavity along an axis in a direction normal to at least one internal skin and at least one external skin.

An acoustic panel for an aircraft nacelle includes a cellular layer configured to trap noise, a backplate fixed to one surface of the cellular layer and a facesheet fixed to another, opposite, surface of the cellular layer. The facesheet includes a layer of a preimpregnated woven material containing weft yarns spaced apart from one another and warp yarns spaced apart from one another so that the facesheet exhibits openings between the yarns.

An existing acoustic honeycomb panel having a radius of curvature is cut into segments that have longitudinal and lateral sides that extend between the edges of the honeycomb. The segments are bonded together along their longitudinal or lateral sides to form a segmented acoustic honeycomb in which the radius of curvature is different from the radius of curvature of the original acoustic honeycomb panel. The shape of the longitudinal or lateral sides of the segments and the thickness of the adhesive bond can be controlled to provide segmented acoustic honeycomb panels that are tightly curved and which are suitable for use in demanding noise damping applications, such as jet engine nacelles.

Adjoining edges of adjacent honeycomb core panel sections are mechanically interlocked. In one embodiment, the method includes forming a first edge along a first cellular core panel section. The first edge includes a first plurality of edge cell walls along the first edge. The method further includes forming a second edge along a second cellular core panel section, wherein the second edge includes a second plurality of edge cell walls along the second edge. The first edge is positioned proximate to the second edge. At least a portion of at least one of the first plurality of edge cell walls is mechanically interlocked with at least a portion of at least one of the second plurality of edge cell walls to form a joint therebetween. A composite structure may be at least partially produced by such a method.

An air inlet (3) for a nacelle (2) for an aircraft (1) includes at least one acoustic panel (5), adapted to lower noise generated by the engine (21) to which the air inlet (3) is connected. At least one lip (6) defines the profile upon which an airflow flowing into the air inlet (3) acts. If necessary, at least one engine ring (4) is adapted to allow the air inlet (3) to be connected to an engine (21) of the nacelle (2). If necessary, at least one outer barrel (7) is adapted to define the outer shape of the air inlet (3) upon which an airflow acts. The air inlet (3) is manufactured as one single piece, made of a composite material.

The present disclosure relates to a cell structure for an acoustic attenuation device for a nacelle of an aircraft propulsion assembly. This cell structure includes lateral partitions forming channels that each extend between a first end and a second end and skin elements arranged so that each channel is at least partly closed at the first end thereof by at least one skin element. Each skin element is connected to a respective lateral partition and can move relative to the other lateral partitions. A continuous skin can be assembled on this cell structure so as to at least partly close the channels at the second end thereof and to thus form an acoustic attenuation device.

An air intake structure for an aircraft nacelle is disclosed. The air intake structure delimits a channel and includes a lip having a U-shaped cross section oriented towards the rear, a first sound-absorbing panel fixed behind the lip and delimiting the channel, and a second sound-absorbing panel fixed behind the first sound-absorbing panel and delimiting the channel. Each sound-absorbing panel includes a cellular core which is fixed between an inner skin pierced with holes and oriented towards the channel, and an outer skin oriented in the opposite direction, where the inner skin of the first sound-absorbing panel has a thickness greater than the thickness of the inner skin of the second sound-absorbing panel, and where each of the inner skins includes a heat source which is embedded in the mass of the inner skin.