Abstract: An air input structure includes an air input lip and a front reinforcement frame placed inside the air input lip. The front part of the air input lip has a plurality of segments distributed angularly along the leading edge of the air input lip, two adjacent segments being separated by an intermediate part having an excess thickness. Each segment has four edges, each having an excess thickness relative to the rest of the segment. Thus, the air input lip has a lighter structure.

Abstract: An aircraft nacelle comprising a lip extended by an inner conduit forming an air intake, a front frame delimiting with said lip an annular channel within which hot air flows and a panel for acoustic treatment having, from outside inwardly, an acoustic resistive layer, at least one honeycomb structure and a reflective layer as well as ducts for channeling hot air, each including one inlet communicating with the annular channel and one outlet communicating with the inner conduit, wherein the panel for acoustic treatment comprises at least a stabilization chamber in the form of an annular channel with a cross-section larger than that of the ducts which extends over at least a portion of the nacelle circumference and which communicates with a plurality of ducts, the inlets and outlets not being aligned in the longitudinal direction.

Abstract: An aircraft nacelle comprising a lip extended by an inner conduit forming an air intake, a front frame delimiting with said lip an annular channel wherein hot air circulates, as well as a panel for acoustic treatment comprising, from outside inwardly, an acoustic resistive layer, at least one honeycomb structure, and a reflective layer, as well as ducts for channeling hot air with each one inlet communicating with the annular channel and one outlet communicating with the inner conduit, wherein the panel for acoustic treatment comprises, upstream from the ducts, an annular channel which extends over at least a portion of the nacelle circumference, at least one conduit providing communication between said annular channel and the upstream annular channel, and a plurality of ducts that open into said downstream annular channel, the panel for acoustic treatment being connected to the front frame in regard to the annular channel.

Abstract: A process for the production of an acoustic treatment panel that can be connected at a surface of an aircraft, in particular at a leading edge such as an air intake of an aircraft nacelle, whereby the panel includes an acoustically resistive layer (24), at least one alveolar structure (26), and a reflective layer (28), and channels (30) placed between the alveolar structure and the acoustically resistive layer, each channel being bordered by a wall (32), the process including deforming a layer so as to produce furrows at one of its surfaces, flattening and making integral the deformed layer (34) with the acoustically resistive layer so as to border the channels, and removing material in such a way as to eliminate at least a portion of the thickness of the deformed layer (34) in which the furrows are formed between the channels, prior to the assembly of the alveolar structure.

Abstract: A method for producing an acoustic treatment panel, including: assembling two plates, at least one of which is deformed so as to separate the plates locally in order to form cavities of a cellular structure between the two plates, said cavities being delimited by facets and partitions formed by at least one of the deformed plates, producing at least one opening on the facets of one of the two plates, and pressing an acoustically resistive plate against the surface of the cellular structure including the openings.

Abstract: An aircraft nacelle comprising a lip extended by an inner conduit forming an air intake, a front frame delimiting with said lip an annular channel within which hot air flows and a panel for acoustic treatment having, from outside inwardly, an acoustic resistive layer, at least one honeycomb structure and a reflective layer as well as ducts for channeling hot air, each including one inlet communicating with the annular channel and one outlet communicating with the inner conduit, wherein the panel for acoustic treatment comprises at least a stabilization chamber in the form of an annular channel with a cross-section larger than that of the ducts which extends over at least a portion of the nacelle circumference and which communicates with a plurality of ducts, the inlets and outlets not being aligned in the longitudinal direction.

Abstract: A process for the production of an acoustic treatment panel that can be connected at a surface of an aircraft, in particular at a leading edge such as an air intake of an aircraft nacelle, whereby the panel includes an acoustically resistive layer (24), at least one alveolar structure (26), and a reflective layer (28), and channels (30) placed between the alveolar structure and the acoustically resistive layer, each channel being bordered by a wall (32), the process including deforming a layer so as to produce furrows at one of its surfaces, flattening and making integral the deformed layer (34) with the acoustically resistive layer so as to border the channels, and removing material in such a way as to eliminate at least a portion of the thickness of the deformed layer (34) in which the furrows are formed between the channels, prior to the assembly of the alveolar structure.