An assembly is provided for an aircraft propulsion system. This assembly includes a nacelle inlet structure extending axially along and circumferentially about an axis. The nacelle inlet structure includes an inlet lip skin, an inner barrel, an outer barrel, a foam core and an acoustic structure. The inlet lip skin forms a leading edge of the nacelle inlet structure. The inner barrel projects axially aft from the inlet lip skin. The inner barrel forms a perforated face skin of the acoustic structure. The outer barrel projects axially aft from the inlet lip skin. The outer barrel is radially outboard of the inner barrel. The foam core is radially between the inner barrel and the outer barrel. The foam core axially overlaps the perforated face skin and projects axially to the inlet lip skin.
NACELLE INLET STRUCTURE WITH FOAM CORE
2024-12-05
Patent
Electronic Resource
English
IPC: | B64D Ausrüstung für Flugzeuge , EQUIPMENT FOR FITTING IN OR TO AIRCRAFT |