Patent ID: 8684301

Claim:
An aircraft nacelle, that comprises: an air intake ( 40 ) configured to channel an air flow ( 42 ) in a direction of a power plant ( 44 ), said air intake ( 40 ) comprising an inside pipe ( 48 ) that forms an aerodynamic surface ( 52 ) configured to be in contact with the air flow ( 42 ) that extends toward a rear of the nacelle by an aerodynamic surface ( 54 ) of a pipe ( 56 ) of the power plant; a wave attenuation panel ( 66 ) configured to limit or prevent propagation of at least one wave produced during pumping of the power plant, the wave attenuation panel extending over at least one portion of a circumference of the nacelle, the wave attenuation panel comprising: a layer ( 68 ) configured to be in contact with the air flow ( 42 ) and to pass said at least one wave, at least one alveolar structure ( 70 ), and a reflective or impermeable layer ( 72 ), said wave attenuation panel ( 66 ) being inserted between the air intake ( 40 ) and the power plant ( 44 ), and said layer ( 68 ) that is in contact with the air flow ( 42 ) ensuring continuity of the aerodynamic surfaces ( 52 , 54 ) that are arranged downstream and upstream, wherein said wave attenuation panel comprises inserts ( 74 ) that are inserted between an annular collar ( 58 ) forming the rear edge of said air intake ( 40 ) and an annular collar ( 60 ) forming the front edge of the power plant so as to take up compressive forces between the air intake and the power plant so as not to crush said wave attenuation panel ( 66 ), and wherein the inserts ( 74 ) comprise a through hole ( 76 ) that allows the passage of connecting means ( 78 ) that can ensure the connection between the air intake and the power plant, said hole being directed along a longitudinal axis.