A rotary wing aircraft with a fuselage that comprises at least one structural stiffened panel, the structural stiffened panel comprising a stressed skin and a stiffening framework that is rigidly attached to the stressed skin, wherein the stressed skin comprises an inner skin, an outer skin and a core element assembly that is arranged between the inner skin and the outer skin, the core element assembly comprising at least one viscoelastic core element and at least one intermediate core element that are tessellated, wherein the at least one viscoelastic core element is provided for noise and vibration damping.
ROTARY WING AIRCRAFT WITH A FUSELAGE THAT COMPRISES AT LEAST ONE STRUCTURAL STIFFENED PANEL
2018-02-15
Patent
Electronic Resource
English
IPC: | B64C AEROPLANES , Flugzeuge |
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