Acoustically attenuated fuselage for aircraft

Details Acoustically attenuated fuselage for aircraft Acoustically attenuated fuselage for aircraft

B - Operations, Transporting

64

C

B64C 1/40 (2006.01) B64C 11/00 (2006.01)

Patent

CA 2709235

The invention relates to a covering (22) of a fuselage (1) for aircraft comprising propeller engines (3) comprising an opening (12) which is surrounded by a structural frame formed by the ribs (5) and the stringers (6) of the aircraft around the area of maximum acoustic impact of the propeller engines (3), said opening (12) further comprising a non-structural panel (7) joined to the previous structural frame by means of a rather non-rigid joint which considerably attenuates the vibrations through such joint, thus reducing the indirect acoustic noise and the indirect structural noise generated by the propeller engines (3) inside the passenger cabin of the aircraft.

L'invention porte sur un revêtement (22) d'un fuselage (1) pour avion comprenant des moteurs à hélice (3) comprenant une ouverture (12) qui est entourée par un cadre structurel formé par les nervures (5) et les lisses (6) de l'avion autour de la zone d'impact acoustique maximal des moteurs à hélice (3), ladite ouverture (12) comprenant en outre un panneau non structurel (7) réuni au cadre structurel précédent au moyen d'une liaison relativement non rigide, ce qui atténue considérablement les vibrations à travers une telle liaison, réduisant ainsi le bruit acoustique indirect et le bruit structurel indirect générés par les moteurs à hélice (3) dans la cabine de passagers de l'avion.

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