The invention is related to rotary wing aircraft with a fuselage that comprises at least one structural stiffened panel 6, the structural stiffened panel 6 comprising a stressed skin 7 and a stiffening framework 8 that is rigidly attached to the stressed skin 7, wherein the stressed skin 7 comprises an inner skin 7a, an outer skin 7b and a core element assembly 17 that is arranged between the inner skin 7a and the outer skin 7b, the core element assembly 17 comprising at least one viscoelastic core element 14 and at least one intermediate core element 15 that are tessellated, wherein the at least one viscoelastic core element 14 is provided for noise and vibration damping.
A ROTARY WING AIRCRAFT WITH A FUSELAGE THAT COMPRISES AT LEAST ONE STRUCTURAL STIFFENED PANEL
DREHFLÜGLER MIT EINEM RUMPF MIT MINDESTENS EINEM STRUKTURELL VERSTEIFTEN PANEEL
AÉRONEF À VOILURE TOURNANTE ÉQUIPÉ D'UN FUSELAGE QUI COMPREND AU MOINS UN PANNEAU DURCI STRUCTUREL
02.10.2019
Patent
Elektronische Ressource
Englisch
IPC: | B64C AEROPLANES , Flugzeuge |
ROTARY WING AIRCRAFT WITH A FUSELAGE THAT COMPRISES AT LEAST ONE STRUCTURAL STIFFENED PANEL
Europäisches Patentamt | 2018
|Rotary wing aircraft with a fuselage that comprises at least one structural stiffened panel
Europäisches Patentamt | 2020
|A ROTARY WING AIRCRAFT WITH A FUSELAGE THAT COMPRISES AT LEAST ONE STRUCTURAL STIFFENED PANEL
Europäisches Patentamt | 2019
A ROTARY WING AIRCRAFT WITH A FUSELAGE THAT COMPRISES AT LEAST ONE STRUCTURAL STIFFENED PANEL
Europäisches Patentamt | 2018
|Aircraft with a fuselage that comprises at least one hollow beam element
Europäisches Patentamt | 2022
|