Abstract: A sandwich panel made of a composite material with acoustical attenuation for a wall and/or self-supporting covering, more particularly for doubling the bulkheads or cabin walls of aircraft, and including an alveolar structural core (14) especially a honeycomb core, and two skins (12, 16) disposed and rendered integral on both sides of the core, wherein the two skins (12, 16) include holes and wherein the holes of at least one of the two skins are micropores. A method for producing this panel is also disclosed.

Abstract: A method for producing a sandwich-type panel with structural and acoustic properties and formed of a core with an open cellular structure. The method includes the steps of forming first and second skins by superimposing and hot-pressing at least two fabric plies of mineral or synthetic fibers impregnated with a thermoplastic resin, of forming in one of the skins perforations with a diameter of between about 0.5 and 1.5 mm, with a vacuum proportion of empty spaces on the surface of the skin of between about 10 and 25%, of after preparation of the skins applying on one face of the skins an epoxy adhesive coating, of forming a sandwich including the open cellular structure with the two skins on its opposing faces, and then of hot-pressing the sandwich at an appropriate temperature so as to polymerize the adhesive. During hot-pressing the pressure and duration are set so as to avoid any full or partial obstruction of the perforations of the perforated skin.