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US 7,726,602 B2Granted
Arrangement for mounting an engine on the airframe of an aircraft
AssigneeAirbus Espana, S.L.
InventorRaúl Carlos Llamas Sandín
Life of this patent
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AssigneeAirbus Espana, S.L.
InventorRaúl Carlos Llamas Sandín
Estimating the term…
Arrangement for mounting a propulsive system on an aircraft airframe by an external pylon which connects the engine with the airframe, the pylon 4comprising a plurality of spars intruding into the airframe and units for attaching the spars to the internal airframe structure, the cited units being dampers, shock absorbers or active actuators with characteristics chosen so that the units are particularly suited for the efficient reduction of attachment and internal dynamic loads arising mainly but not only from hard landing events and aircraft flight manoeuvres, and for damping sustained vibrations of the propulsive system-airframe assembly, the arrangement allowing the easy removal of the pylon 4 from the rest of the airframe and the interchangeability of the pylon 4 between different aircrafts, being also the cited arrangement tolerant to damage or complete failure of at least one of the spars.
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.
Dependencies are inferred from the claim text.