Engine mounting structure under an aircraft wing
원문보기
IPC분류정보
국가/구분
United States(US) Patent
등록
국제특허분류(IPC7판)
B64D-027/00
F16M-013/00
F02C-007/20
출원번호
US-0986791
(2004-11-15)
등록번호
US-7451947
(2008-11-18)
우선권정보
FR-03 50907(2003-11-25)
발명자
/ 주소
Machado,Stephane
Cassagne,Jerome
Del Blanco,Anthony
Martin,Yvon
Chambreuil,Arnaud
출원인 / 주소
Airbus France
대리인 / 주소
Oblon, Spivak, McClelland, Maier & Neustadt, P.C.
인용정보
피인용 횟수 :
8인용 특허 :
11
초록▼
This invention relates to a mounting structure (1) for mounting an engine (2) under an aircraft wing (4), the structure comprising a rigid structure (8) and means (10) of fastening this rigid structure under the wing, the mounting means comprising a forward fastener (14), an intermediate fastener (1
This invention relates to a mounting structure (1) for mounting an engine (2) under an aircraft wing (4), the structure comprising a rigid structure (8) and means (10) of fastening this rigid structure under the wing, the mounting means comprising a forward fastener (14), an intermediate fastener (15) 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 (2), placed in a vertical plane oriented along a longitudinal direction (X) of the aircraft. Furthermore, the intermediate fastener comprises a connecting rod capable of transferring forces applied in a direction (Y) transverse to the aircraft, and the aft fastener comprises at least one shackle oriented along a vertical direction (Z) of the aircraft.
대표청구항▼
The invention claimed is: 1. Mounting structure for mounting an engine under an aircraft wing, said structure comprising: a rigid structure; and a statically determinant fastener arrangement including a forward fastener between said rigid structure and said aircraft wing; an intermediate fastener b
The invention claimed is: 1. Mounting structure for mounting an engine under an aircraft wing, said structure comprising: a rigid structure; and a statically determinant fastener arrangement including a forward fastener between said rigid structure and said aircraft wing; an intermediate 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, placed in a vertical plane oriented along a longitudinal direction X of the aircraft, wherein said forward fastener is configured to transfer all forces between said rigid structure and the wing that are applied in said longitudinal direction X, wherein said intermediate fastener comprises a connecting rod configured to transfer all forces between said rigid structure and said wing that are applied in a direction Y transverse to the aircraft, wherein said aft fastener comprises at least one shackle oriented substantially parallel to a vertical direction Z of the aircraft, and wherein the longitudinal axis of said connecting rod is arranged substantially parallel to the transverse direction Y of the aircraft. 2. Mounting structure according to claim 1 for mounting an engine, wherein said intermediate fastener includes a lower fitting fixed to the rigid structure and an upper fitting fixed to the wing of the aircraft, and wherein a first end of said connecting rod is mounted on the lower fitting and a second end of said connecting rod is mounted on the upper fitting. 3. Mounting structure according to claim 2 for mounting an engine, wherein said first end of said connecting rod is articulately mounted on the lower fitting and said second end is articulately mounted on the upper fitting. 4. Mounting structure according to claim 1 for mounting an engine, wherein said connecting rod is located in a vertical plane oriented substantially parallel to the transverse direction Y of the aircraft. 5. 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, wherein the forward fastener comprises two pairs of triangular shackles, wherein each pair of triangular shackles is located on each side of the vertical plane passing through the longitudinal axis of the engine, and wherein the two pairs of triangular shackles are located in vertical planes oriented substantially parallel to the longitudinal direction X of the aircraft. 6. Mounting structure according to claim 5 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. 7. Mounting structure according to claim 5 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 at least one fastening mechanism oriented substantially parallel to the transverse direction Y of said aircraft. 8. Mounting structure according to claim 5 for mounting an engine, wherein said aft fastener also comprises a 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 also comprises a 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. 9. Mounting structure according to claim 5 for mounting an engine, wherein said forward fastener also comprises two fittings fixed to the rigid structure, each fitting being connected to one of the two pairs of triangular shackles by at least one fastening mechanism oriented substantially parallel to the transverse direction Y of said aircraft, and wherein said forward fastener also comprises two fittings fixed to the wing, each fitting being connected to one of the two pairs of triangular shackles by at least one fastening mechanism oriented substantially parallel to the transverse direction Y of said aircraft. 10. 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 at least three fastening mechanisms that pass through each triangular shackle substantially at each of three vertices of each triangular shackle. 11. 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 to the wing by a vertex of the at least on triangular shackle opposite said base. 12. 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. 13. 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 the at least two triangular shackles are removably mounted substantially parallel to each other on either side of the first fitting and the second fitting and extend substantially parallel to a longitudinal axis of the engine, and extend substantially parallel to a vertical plane oriented along a longitudinal direction X of the aircraft. 14. 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. 15. Mounting structure according to claim 14 for mounting an engine, wherein said at least three through holes are arranged as vertices of an equilateral triangle. 16. 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. 17. Mounting structure according to claim 1 for mounting an engine, wherein the mounting structure does not include a spigot fastener, wherein said spigot fastener 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. 18. Mounting structure according to claim 2 for mounting an engine, wherein said lower fitting is double headed and perforated by two through holes and includes a base that is directly mounted to a stringer of the rigid structure. 19. Mounting structure according to claim 18 for mounting an engine, wherein said base of said lower fitting extends in a horizontal plane oriented substantially parallel to the transverse direction Y and the longitudinal direction X of the aircraft. 20. Mounting structure according to claim 2 for mounting an engine, wherein said upper fitting is double headed and perforated by two through holes and includes a base that is directly mounted to a stringer of the wing of the aircraft. 21. Mounting structure according to claim 20 for mounting an engine, wherein said base of said upper fitting extends in a horizontal plane oriented substantially parallel to the transverse direction Y and the longitudinal direction X of the aircraft. 22. Mounting structure according to claim 2 for mounting an engine, wherein said lower fitting includes a base that is directly mounted to a stringer of the rigid structure, wherein said upper fitting includes a base that is directly mounted to a stringer of the wing of the aircraft, and wherein said base of said lower fitting is substantially parallel to said base of said upper fitting. 23. Mounting structure according to claim 1 for mounting an engine, wherein the combination of said forward fastener and said aft fastener is configured to transfer all forces applied in the vertical direction (Z) of the aircraft. 24. Mounting structure according to claim 1 for mounting an engine, wherein a combination of said forward fastener, said intermediate fastener, and said 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. 25. Mounting structure according to claim 24 for mounting an engine, wherein all moments about an axis substantially parallel to the longitudinal direction (X) is resisted in the vertical direction (Z) by said forward fastener, all moments about an axis substantially parallel to the transverse direction (Y) is resisted in the vertical direction (Z) by a combination of said forward fastener and said aft fastener, and all moments about an axis substantially parallel to the vertical direction (Z) is resisted in the longitudinal direction (X) by said forward fastener. 26. Mounting structure according to claim 1 for mounting an engine, wherein said rigid structure is interposed between the engine and said statically determinant fastener arrangement.
Brodell Robert F. (Marlborough CT) Hovan Edward J. (Manchester CT) Selfors Steven T. (Somerville MA) Loffredo Constantino V. (Newington CT) Duesler Paul W. (Manchester CT), Nacelle and mounting arrangement for an aircraft engine.
Journade, Frederic; Lafont, Laurent; Agostini, Laurent; Renaud, Eric; Jalbert, Delphine, Aircraft assembly including an element for mounting an engine and associated aircraft.
Lafont, Laurent; Journade, Frederic; Renaud, Eric, Aircraft engine attachment pylon comprising two front wing system attachments with orthogonal shearing pins.
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