초록 ▼

This invention relates to a structure (1) for mounting an engine (2) under an aircraft wing (4), comprising a rigid structure (8) and means (10) of mounting this rigid structure under the wing, the mounting means (10) comprising a forward fastener (14) and an aft fastener (16). According to the inv

This invention relates to a structure (1) for mounting an engine (2) under an aircraft wing (4), comprising a rigid structure (8) and means (10) of mounting this rigid structure under the wing, the mounting means (10) comprising a forward fastener (14) and an aft fastener (16). According to the invention, the forward fastener has at least one triangular shackle on each side of a vertical plane passing through a longitudinal axis (5) of the engine, placed in a vertical plane oriented along a direction inclined with respect to a longitudinal direction (X) and a transverse direction (Y) of the aircraft, and located in a horizontal plane defined by these directions (X) and (Y). Furthermore, the aft fastener comprises at least one shackle oriented along a vertical direction (Z) of the aircraft.

대표청구항 ▼

The invention claimed is: 1. A mounting structure for mounting an engine under an aircraft wing, said structure comprising: a rigid structure; a forward fastener between said rigid structure and said aircraft wing; and an aft fastener between said rigid structure and said aircraft wing, wherein sai

The invention claimed is: 1. A mounting structure for mounting an engine under an aircraft wing, said structure comprising: a rigid structure; a forward fastener between said rigid structure and said aircraft wing; and an aft fastener between said rigid structure and said aircraft wing, wherein said forward fastener includes at least one triangular shackle located on each side of a vertical plane substantially parallel to a longitudinal axis of the engine, wherein said at least one triangular shackle extends in an inclined vertical plane that is inclined with respect to a longitudinal direction (X) and a transverse direction (Y) of the aircraft, wherein a combination of the forward fastener and the aft fastener is configured to transfer all forces applied in the longitudinal direction (X), the transverse direction (Y), and a vertical direction (Z) of the aircraft, wherein said forward fastener is configured to transfer forces applied in said longitudinal direction (X), and wherein said aft fastener comprises at least one shackle oriented substantially parallel to the vertical direction (Z) of the aircraft. 2. A mounting structure according to claim 1 for mounting an engine, wherein each of the triangular shackles of the forward fastener are arranged so that an aft end of each triangular shackle is closer to the longitudinal axis of the engine than a forward end of each triangular shackle, said aft end of each triangular shackle being closer to an aft end of the engine than said forward end of each triangular shackle. 3. A mounting structure according to claim 1 for mounting an engine, wherein said aft fastener comprises a pair of shackles oriented substantially parallel to the vertical direction (Z) of the aircraft, and wherein said forward fastener comprises a pair of triangular shackles on each side of the vertical plane substantially parallel to the longitudinal axis of the engine, each respective triangular shackle extending in a respective vertical plane inclined with respect to the longitudinal direction (X) and the transverse direction (Y) of the aircraft. 4. A mounting structure according to claim 3 for mounting an engine, wherein said pair of shackles of the aft fastener is connected to the rigid structure and to the wing of the aircraft by at least one fastening mechanism oriented substantially parallel to the longitudinal direction (X) of said aircraft. 5. A mounting structure according to claim 3 for mounting an engine, wherein each of the two pairs of triangular shackles of the forward fastener is connected to the rigid structure and to the wing of the aircraft by a plurality of hinge pins oriented substantially perpendicular to each respective pair of triangular shackles. 6. A mounting structure according to claim 3 for mounting an engine, wherein said aft fastener includes a first fitting fixed to the rigid structure and connected to said pair of shackles by at least one fastening mechanism oriented substantially parallel to the longitudinal direction (X) of said aircraft, and wherein said aft fastener includes a second fitting fixed to the wing and connected to said pair of shackles by at least one fastening mechanism oriented substantially parallel to the longitudinal direction (X) of said aircraft. 7. A mounting structure according to claim 3 for mounting an engine, wherein said forward fastener includes two first fittings fixed to the rigid structure, each first fitting being connected to one of the two pairs of triangular shackles by at least one fastening mechanism oriented substantially perpendicular to each respective pair of triangular shackles, and wherein said forward fastener includes two second fittings fixed to the wing, each second fitting being connected to one of the two pairs of triangular shackles by at least one fastening mechanism oriented substantially perpendicular to each respective pair of triangular shackles. 8. A mounting structure according to claim 1 for mounting an engine, wherein each triangular shackle of the forward fastener is connected to the rigid structure and to the aircraft wing by three hinge pins that pass through each triangular shackle close to each of three vertices of each triangular shackle. 9. A mounting structure according to claim 1 for mounting an engine, wherein at least one triangular shackle of the forward fastener is connected to the rigid structure at a base of the at least one triangular shackle, and the at least one triangular shackle is connected to the wing by a vertex of the at least one triangular shackle opposite said base. 10. A mounting structure according to claim 1 for mounting an engine, wherein at least one triangular shackle of the forward fastener is connected to the rigid structure at a vertex of the at least one triangular shackle, and the at least one triangular shackle is connected to the wing at a base of the at least one triangular shackle opposite said vertex. 11. A mounting structure according to claim 1 for mounting an engine, wherein said forward fastener further comprises at least one first fitting fixed to the aircraft wing, at least one second fitting fixed to the rigid structure and at least two triangular shackles; wherein said at least two triangular shackles are removably mounted to the first fitting and the second fitting such that a first one of the at least two triangular shackles is removably mounted on a first side side of the first fitting and the second fitting, and a second one of the at least two triangular shackles is removably mounted on an opposite side of the first fitting and the second fitting. 12. A mounting structure according to claim 11 for mounting an engine, wherein each of said first fitting and said second fitting extend in an oblique direction with respect to both of the longitudinal direction (X) and the transverse direction (Y) of the aircraft. 13. A mounting structure according to claim 1 for mounting an engine, wherein said at least one triangular shackle includes at least three through-holes that are not arranged in a line. 14. A mounting structure according to claim 13 for mounting an engine, wherein said at least three through holes are arranged as vertices of an equilateral triangle. 15. A mounting structure according to claim 1 for mounting an engine, wherein the at least one triangular shackle is not integral with either the aircraft wing or the rigid structure. 16. A mounting structure according to claim 1 for mounting an engine, wherein the mounting structure does not include a spigot fastener that includes a ball joint fixed in the rigid structure and a shear pin fixed under the aircraft wing so that the shear pin projects into the ball joint and that is configured to transfer forces applied in said longitudinal direction (X). 17. A mounting structure according to claim 1 for mounting an engine, wherein said forward fastener is arranged such that a virtual extension of said at least one triangular shackle forms an angle of at least 10 degrees and no more than 50 degrees with the longitudinal direction (X) of said aircraft. 18. A mounting structure according to claim 1 for mounting an engine, wherein said forward fastener is configured to transfer forces applied in said transverse direction (Y) and said vertical direction (Z) of the aircraft. 19. A mounting structure according to claim 1 for mounting an engine, wherein said rigid structure is a pylon configured to suspend an aircraft engine.