Patent ID: 7726602
Filing Date: 2010-06-01
Classification: B64D

Abstract:
1. A structural configuration for the assembly of the supporting structure ( 4 ) of an aircraft engine ( 1 ) on the fuselage ( 12 ) of an aircraft, wherein the supporting structure ( 4 ) of the engine ( 1 ) comprises a closed structure part ( 6 ) outside the fuselage ( 12 ) and at least two spars ( 8 ) penetrating the fuselage ( 12 ) and connected to the internal structure ( 10 ) of said fuselage ( 12 ) through first and second connecting members ( 9 , 11 ), said first members ( 9 ) connecting the end of the spars ( 8 ) to the internal structure ( 10 ) of the fuselage ( 12 ) and said second members ( 11 ) connecting the mentioned spars ( 8 ) to the internal structure ( 10 ) at the points of said spars ( 8 ) closest to the engine ( 1 ) thereby forming a lever arm such that the internal dynamic loads and the loads from the coupling of the supporting structure ( 4 ) to the engine ( 1 ), generated in cases of dynamic landings and in-flight aircraft maneuvers, are efficiently reduced, and the continuous vibrations in the engine assembly ( 1 ) and aircraft are further dampened.