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AssigneeAirbus France
InventorsGilles Chene, Fabrice Gantie, Alain Porte
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The invention relates to acoustic lining for an aircraft, which can cover a leading edge, such as an air inlet in the nacelle of a propulsion unit, said lining comprising: (i) from the inside outwards, a reflective layer (28), at least one cellular structure (30) and an acoustically resistive structure (32) having a pre-determined proportion of open surface; and (ii) at least one frost treatment system in the form of at least one heating layer (46) comprising open zones through which acoustic waves can pass, which co-operate at least partially with the open zones in the acoustically resistive structure. The invention is characterised in that the acoustically resistive structure (32) includes at least one structural layer (36) with openings (38) and in that said at least one heating layer (46) is disposed under the structural layer (36).
Acoustic coating for an aircraft, able to cover a leading edge, such as, for example, an air intake (22) of a nacelle (14) of a propulsion unit (10), said acoustic coating comprising, on the one hand—from the inside to the outside—a reflective layer (28), at least one alveolar structure (30), and an acoustically resistive structure (32) that has a determined open surface ratio, and, on the other hand, at least one frost treatment system in the form of at least one heating layer (46) that comprises open zones that are able to allow the passage of acoustic waves that cooperate at least in part with the open zones of the acoustically resistive structure, characterized in that the acoustically resistive structure (32) comprises at least one structural layer (36) with openings (38) and in that said at least one heating layer (46) is arranged under the structural layer (36).
Air intake (22) of a nacelle (14) of an aircraft propulsion unit (10), covered at least in part by a coating (26) for the acoustic treatment that comprises, on the one hand—from the inside to the outside—a reflective layer (28), at least one alveolar structure (30), and an acoustically resistive structure (32) having a determined open surface ratio, and, on the other hand, at least one frost treatment system in the form of at least one heating layer (46) that comprises open zones that are able to allow the passage of acoustic waves that cooperate at least in part with the open zones of the acoustically resistive structure, wherein the acoustically resistive structure (32) comprises at least one structural layer (36) with openings (38) and wherein said at least one heating layer (46) is arranged under the structural layer (36).
Air intake of a nacelle of an aircraft propulsion unit (10), wherein it is covered in part by an acoustic coating that comprises, on the one hand—from the inside to the outside—a reflective layer (28), at least one alveolar structure (30), and an acoustically resistive structure (32) with at least one structural layer (36) with openings (38), and, on the other hand, at least one frost treatment system in the form of at least one heating layer (46), arranged under the structural layer (36), comprising open zones that are able to allow the passage of the acoustic waves that cooperate at least in part with the open zones of the acoustically resistive structure as well as at least one point-type frost treatment system in the form of at least one vibration emitter (64).
Dependencies are inferred from the claim text.