A turbomachine assembly comprising a nacelle having an air inlet and comprising a structure. A forward hood is fixed to the structure and extends backwards from the air inlet. An articulated hood is arranged in the upper part of the nacelle and at the rear of the forward hood and comprises a front edge arranged at the front of the articulated hood. A rear edge is arranged at the rear of the articulated hood. A joint is disposed at the front edge between the articulated hood and the structure and ensures a displacement of the articulated hood between a closed position and an open position. A locking system is arranged at the rear edge, and is mobile between a locked position and an unlocked position, where in the closed position, the front edge is under the forward hood.
ENSEMBLE TURBOMACHINE D'AERONEF COMPORTANT UN CAPOT ARTICULE
AIRCRAFT TURBINE ENGINE ASSEMBLY COMPRISING A HINGED COVER
TURBOTRIEBWERK-ANORDNUNG EINES LUFTFAHRZEUGS, DIE EINEN SCHARNIERDECKEL UMFASST
2021-06-16
Patent
Electronic Resource
French
IPC: | B64D Ausrüstung für Flugzeuge , EQUIPMENT FOR FITTING IN OR TO AIRCRAFT |
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