Abstract: A sandwich panel for an aircraft turbojet nacelle includes an outer skin in contact with an air flow, an inner skin opposed to the outer skin, and an intermediate system comprising partitions connecting the inner and outer skins so as to form cells, the inner skin of at least one cell having at least one corrugation configured to allow the materials making up the sandwich panel to deform in the event of thermal variation.

Abstract: A structure for the nacelle of an aircraft propulsion unit includes a first skin and stiffeners arranged to hold acoustic treatment modules against the first skin. Each acoustic treatment module includes a honeycomb core and a second skin, such that the honeycomb core is sandwiched between the first skin and the second skin. Such a structure allows the structural reinforcement function provided by the stiffeners to be separated from the acoustic treatment function performed by the acoustic treatment modules which are simply bearing on the first skin.

Abstract: 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.

Abstract: A sandwich panel for an aircraft turbojet nacelle includes an outer skin in contact with an air flow, an inner skin opposed to the outer skin, and an intermediate system comprising partitions connecting the inner and outer skins so as to form cells, the inner skin of at least one cell having at least one corrugation configured to allow the materials making up the sandwich panel to deform in the event of thermal variation.

Abstract: A structure for the nacelle of an aircraft propulsion unit includes a first skin and stiffeners arranged to hold acoustic treatment modules against the first skin. Each acoustic treatment module includes a honeycomb core and a second skin, such that the honeycomb core is sandwiched between the first skin and the second skin. Such a structure allows the structural reinforcement function provided by the stiffeners to be separated from the acoustic treatment function performed by the acoustic treatment modules which are simply bearing on the first skin.

Abstract: A panel for a nacelle of an aircraft propulsion assembly includes two skins and a cell structure provided with transverse partitions defining cells. The cell structure includes folds with at least one central part forming at least one part of at least one transverse partition and at least one peripheral part extending along at least one of the skins. A nacelle with such a panel is provided, as well as a method for manufacturing such a panel.

Abstract: 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.

Abstract: An aircraft nacelle includes: a thrust reverse device having movable cowls, and a supporting structure to support the thrust reverser device. The supporting structure includes: a base body extending along a longitudinal direction of the nacelle and made from a composite material, and a wall of the base body forming an unclosed cross section having an open portion to provide access to an inner surface of the supporting structure from outside, and a plurality of reinforcements which is made from a composite material, and attached on the inner surface along the longitudinal direction. In particular, the reinforcements are integrated in the inner surface of the supporting structure.

Abstract: The present disclosure relates to a beam, in particular for a cascade thrust reverser, including a skin made of a composite material and defining a closed section, wherein said beam is filled with a core material.

Abstract: A unit for an aircraft thruster is provided that includes a first ferrule configured to be attached to a second ferrule and a first connection flange configured to be secured to a second corresponding connection flange secured to the second ferrule. The connection flange includes a portion forming a plane extending along a radial direction with respect to the first ferrule. A link between the first ferrule and the corresponding connection flange is offset to a distance from said plane corresponding to a length for damping a shear-generating flexural moment, generated by fluxes of forces passing through the first ferrule.

Abstract: A supporting half-structure for an aircraft engine nacelle is provided that includes at least one longitudinal beam and a front half-frame, the beam and the half-frame being formed of composite materials. The half frame has an open section, and the half-structure defines a structure selected from the group consisting of: the beam and the front half-frame form a one-piece part; the beam has an extension with an open section, the shape of which matches that of the front half-frame, the extension being attached to the half frame; and the front half-frame has an extension with an open shape, the shape of which matches the beam, wherein the extension is attached to the beam.

Abstract: A stub frame for a cascade vane thrust reverser structure of an aircraft nacelle is attached to one or more cascade vanes. The stub frame includes an integral primary structure with a C-shaped longitudinal section, a secondary structure acting as a cascade edge and attached to the primary structure at one end, and transverse stiffeners connecting the two ends of the primary structure.

Abstract: A method of detecting bubbles during operations for injecting resin for the manufacture of fibre composite components, is noteworthy in that the electrical capacitance or conductivity of at least one part of the medium formed by the fibres and the liquid is measured.

Abstract: A leading edge structure for an air inlet of an aircraft nacelle includes a leading edge and an inner partition defining a longitudinal compartment that is located inside the leading edge and accommodates a de-icing and/or anti-icing mat. The leading edge structure includes a multi-axial composite structure placed on top of a heating element for anti-icing and/or de-icing.

Abstract: The invention relates to a stub frame (121) for a cascade thrust reverser structure of a nacelle (101) of an aircraft, said stub frame (121) being intended for being fastened to one or more cascade vanes (113, 181) and including an integral primary structure (141) with a substantially C-shaped longitudinal section, a secondary structure (143) acting as a cascade edge and attached to said primary structure (141) at one end, and transverse stiffeners (145) connecting the two ends (142, 144) of the primary structure (141). The invention also relates to a cascade thrust reverser structure and a nacelle comprising such a stub frame.

Abstract: The present invention relates to a supporting structure (200) for a nacelle of a jet engine, in particular provided with a thrust reverser device, including at least one base body (201) made of a composite material, characterised in that the base body has a transverse section which is essentially open and provided with at least one reinforcement means.

Abstract: The invention relates to a structure of a leading edge (1), in particular for the air intake of an aircraft nacelle, including a leading edge (2) and an inner partition wall (3) defining a longitudinal compartment (5) inside the leading edge (2). The leading edge (2) and said inner partition wall (3) are made of multiaxial composite materials.

Abstract: The invention relates to a method for making an acoustic absorption panel in particular for the nacelle of an aircraft engine, the panel being of the type comprising a cellular core covered on one side with a so-called outer air-permissive skin and on the other side with a so-called inner perforated skin, the cellular core being formed by the edge-to-edge junction of a plurality of blocks with a cellular core (B1, B2). The method comprises the following steps: a) before the edge-to-edge junction of blocks with a cellular core (B1, B2), opening the cells (A1, A2) located on the edges of the blocks to be joined; and b) edge-to-edge dry joining the blocks (B1, B2) so that the open cells (A1, A2) engage into one another.

Abstract: The present invention relates to a turbofan jet engine nacelle intended to be attached to a structure of an aircraft by an engine strut and comprising a forward air inlet section, a mid-section intended to surround a jet engine fan, and an aft section having an internal structure intended to serve as a casing for an aft portion of the jet engine and, together with an external structure (5), defining a flow duct (7) for a secondary stream, the internal structure having substantially radial extensions (61) passing through the duct and via which it is connected to an inner panel (51) of the external structure by means of at least one corresponding stiffener (110) having a right-angled general shape, characterized in that the stiffener is also fastened in an external panel (52) of the external structure.

Abstract: The invention relates to a method for making an acoustic absorption panel in particular for the nacelle of an aircraft engine, the panel being of the type comprising a cellular core covered on one side with a so-called outer air-permissive skin and on the other side with a so-called inner perforated skin, the cellular core being formed by the edge-to-edge junction of a plurality of blocks with a cellular core (B1, B2). The method comprises the following steps: a) before the edge-to-edge junction of blocks with a cellular core (B1, B2), opening the cells (A1, A2) located on the edges of the blocks to be joined; and b) edge-to-edge dry joining the blocks (B1, B2) so that the open cells (A1, A2) engage into one another.