| 摘要 |
<p>The present invention relates to a structure (7) for a lip (4a) of an air inlet (4) of a turbojet pod (1) comprising an outer skin (12), designed to be oriented towards the outside of the lip, and an inner skin (13), designed to be oriented towards the inside of the lip, characterized in that it comprises at least one electric heating element (14) situated between the inner skin and the outer skin and capable of being connected to electric supply means (15, 16), at least one electric heating element extending at least partly through an acoustic attenuation zone having perforations (11) passing through the structure and associated with an acoustic attenuation structure (30) fitted to the inner skin.</p> |
