Patent ID: 8794572

Claim:
An air intake of an aircraft nacelle comprising: a lip ( 42 ) that is defined by a wall ( 52 ) having a surface that is in contact with aerodynamic flows, the lip being extended on an inside of the nacelle by an inside wall ( 44 ) that borders a pipe that empties out at a power plant; an outside wall ( 46 ); a surface Joule-effect defrosting system ( 58 ); at least a first alveolar structure ( 60 . 1 ) that is made of a material that conducts heat that is flattened against an inside surface of the wall ( 52 ) and inserted between said wall ( 52 ) and the defrosting system ( 58 ); and at least two second alveolar structures ( 60 . 2 ) that are made of composite material, the at least two second alveolar structures being adjacent to the first alveolar structure ( 60 . 1 ), the at least two second alveolar structures ( 60 . 2 ) being flattened against the inside surface of the wall ( 52 ), with the defrosting system ( 58 ) being inserted between the at least two second alveolar structures ( 60 . 2 ) and said wall ( 52 ), wherein the first alveolar structure ( 60 . 1 ) is in a zone Z 1 that corresponds to approximately ⅔ of a height of the air intake that is sized for mechanical strength, and at least of the second alveolar structures ( 60 . 2 ) is in at least one zone Z 2 that is adjacent to the zone Z 1 .