Strip-form acoustic material having an integrated flange, and internal wall of an aircraft air intake made with this material

1. An internal wall of an aircraft air intake comprising:

a resistive skin configured to allow acoustic waves to pass through, and

a cellular core configured to damp said acoustic waves,

wherein the resistive skin is made up of a succession, in an orbital direction, of strips of acoustic material, each strip having a length in a longitudinal direction, a width in a transverse direction, a thickness and axial ends, each strip of material being folded in a substantially transverse plane at at least one of the axial ends of the strip, in an end portion of the length of the strip, the folded end portions of the strips forming a rear or front flange for fastening the resistive skin of the air intake internal wall to a frame of the air intake, each strip comprising:

a first layer forming a visible frontal face of the air intake internal wall, said first layer being made of a fiber-reinforced polymer, the first layer being perforated or micro-perforated,

a second layer made up of a metal fabric or of a thin metal sheet or a thin sheet made of thermoplastic material disposed on the first layer on a surface of the first layer opposite the visible frontal face of the air intake internal wall and forming a second frontal face of the air intake internal wall opposite the visible frontal face and further forming a portion of the front or rear flange,

a third layer formed of tapes made of a fiber-reinforced polymer disposed on at least one of the first layer and the second layer such that the third layer forms a portion of the second frontal face of the air intake internal wall, said tapes extending mainly in the longitudinal direction of the strip and being spaced apart from one another in the transverse direction of the strip, the tapes thus forming longitudinal reinforcing crenellations, the first layer not having perforations or micro-perforations next to said tapes,

wherein the folded end portion of the strip does not have perforations or micro-perforations in the first layer, and

wherein the third layer terminates such that the third layer does not extend into the rear or front flange.

2. The aircraft air intake internal wall according to claim 1 , wherein the strips of acoustic material making up the resistive skin are folded in a plane transverse to each of their axial ends, the folded end portions of said strips forming both a rear flange for fastening the resistive skin of the internal wall to a rear frame of the air intake and a front flange for fastening the resistive skin of the internal wall to a front frame of the air intake.

3. The aircraft air intake internal wall according to claim 1 , wherein the folded end portion is folded on the opposite side from the first layer.

4. The aircraft air intake internal wall according to claim 1 , wherein the folded end portion is folded on the same side as the first layer.

5. An aircraft nacelle comprising an air intake having an internal wall according to claim 1 .

6. An aircraft propulsion unit comprising a nacelle according to claim 5 .

7. An aircraft comprising at least one propulsion unit according to claim 6 .

8. The aircraft air intake internal wall according to claim 1 , wherein the resistive skin has a frontal face in contact with an aerodynamic flow, wherein each strip of material is folded in a direction away from the aerodynamic flow.