Aircraft turbojet engine nacelle comprise an increased-rigidity air intake

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United States of America Patent

PATENT NO 9845707
SERIAL NO

14575392

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Abstract

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An aircraft turbojet engine nacelle comprising an air intake assembly of substantially annular shape, the air intake assembly comprising an external wall and an internal wall which are connected to one another upstream by an air intake lip and downstream by an annular rear structure. The annular rear structure comprises, arranged concentrically, one or more monolithic panels forming a first annular zone and comprising one or more hollow casings forming at least a second annular zone, and at least one connecting ring which provides the connection with at least one of the external and internal walls. The annular rear structure thus has increased structural mechanical strength.

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Patent Owner(s)

  • AIRBUS OPERATIONS SAS

International Classification(s)

Inventor(s)

Inventor Name Address # of filed Patents Total Citations
Fargues, Matthieu Montauban, FR 8 64
Porte, Alain Colomiers, FR 168 2515

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