Patent ID: 8181900

Claim:
An acoustic coating for an aircraft, able to cover a leading edge, or an air intake ( 22 ) of a nacelle ( 14 ) of a propulsion unit ( 10 ), said acoustic coating comprising: from an inside to an outside— a reflective layer ( 28 ), at least one alveolar structure ( 30 ), and an acoustically resistive structure ( 32 ) that comprises at least one porous layer ( 34 ) and at least one structural layer ( 36 ) with openings ( 38 ), said at least one structural layer ( 36 ) being arranged outside and constituting an aerodynamic surface; and at least one frost treatment system having at least one heating layer ( 46 ), wherein the openings ( 38 ) of the structural layer are arranged so as to create linear filled zones, said at least one heating layer ( 46 ) is arranged under the structural layer ( 36 ) between the openings of said structural layer and comprises at least one flat linear conductive element ( 48 ) whose width in a plane parallel to the aerodynamic surface is less than or equal to a width of filled zones of the structural layer ( 36 ) so as to not encroach upon the openings ( 38 ) of the structural element ( 36 ) and to not modify an open surface ratio of the acoustically resistive structure ( 32 ).