IPC분류정보
국가/구분 |
United States(US) Patent
등록
|
국제특허분류(IPC7판) |
|
출원번호 |
US-0989589
(2009-05-12)
|
등록번호 |
US-8517305
(2013-08-27)
|
우선권정보 |
FR-08 53116 (2008-05-14) |
국제출원번호 |
PCT/FR2009/050861
(2009-05-12)
|
§371/§102 date |
20101025
(20101025)
|
국제공개번호 |
WO2009/147342
(2009-12-10)
|
발명자
/ 주소 |
- Marche, Jacques Herve
- Raison, Fabien
|
출원인 / 주소 |
|
대리인 / 주소 |
Oblon, Spivak, McClelland, Maier & Neustadt, L.L.P.
|
인용정보 |
피인용 횟수 :
2 인용 특허 :
6 |
초록
An engine attachment pylon for an aircraft, including a rigid structure including a box formed by one or plural hollow segments. The section of at least one hollow segment is circular or elliptical in shape.
대표청구항
▼
1. An engine attachment pylon for an aircraft, the pylon comprising: a rigid structure including a box formed by at least one hollow segment,wherein a section of the at least one hollow segment is elliptical or circular in shape,wherein the at least one hollow segment includes a forward hollow segme
1. An engine attachment pylon for an aircraft, the pylon comprising: a rigid structure including a box formed by at least one hollow segment,wherein a section of the at least one hollow segment is elliptical or circular in shape,wherein the at least one hollow segment includes a forward hollow segment with a tapered and truncated circular cross-section, anda central hollow segment supporting the forward segment, andwherein the central hollow segment is approximately cylindrical in a form of an ellipse with an inclined axis intersecting an axis of the forward segment. 2. The pylon according to claim 1, wherein the forward hollow segment and the central hollow segment are connected to each other at respective forward and aft ends thereof. 3. The pylon according to claim 2, wherein the forward hollow segment and the central hollow segment each include an attachment flange projecting outwards from a space inside the box. 4. The pylon according to claim 3, wherein the forward hollow segment and the central hollow segment are assembled to each other via respective attachment flanges bearing on each other, and wherein the forward hollow segment and the central hollow segment are fixed to each other by attachment means outside the space inside the box. 5. An engine attachment pylon for an aircraft, the pylon comprising: a rigid structure including a box formed by a plurality of hollow segments,wherein a first segment of the plurality of hollow segments is a forward hollow segment, the forward hollow segment having a tapered and truncated profile,wherein a second segment of the plurality of hollow segments is a central hollow segment, the central hollow segment supporting the forward hollow segment, andwherein an entire cross-section of the forward hollow segment is circular, and an entire cross-section of the central hollow segment is elliptical. 6. The pylon according to claim 5, wherein the plurality of hollow segments are connected to each other at respective forward and aft ends thereof. 7. The pylon according to claim 6, wherein the plurality of hollow segments each include at least one attachment flange projecting outwards from a space inside the box. 8. The pylon according to claim 7, wherein the plurality of hollow segments are assembled to each other via the attachment flanges bearing on each other, and wherein the plurality of hollow segments are fixed to each other by attachment means outside the space inside the box. 9. The pylon according to claim 5, further wherein the central hollow segment has a central axis, wherein the central axis intersects a forward axis of the forward hollow segment, andwherein the forward axis is inclined with respect to the central axis. 10. The pylon according to claim 5, wherein a major axis of the elliptical cross-section of the central hollow segment is vertically perpendicular to an engine central axis. 11. The pylon according to claim 5, wherein a third segment of the plurality of hollow segments is an aft hollow segment, and wherein an entire cross-section of the aft hollow segment is elliptical or circular. 12. The pylon according to claim 11, wherein a major axis of the elliptical cross-section of the aft hollow segment is vertically perpendicular to an engine central axis. 13. An engine attachment pylon for an aircraft, the pylon comprising: a rigid structure including a box formed by a plurality of hollow segments,wherein an entire cross-section of each of the plurality of hollow segments is elliptical or circular,wherein each of the plurality of hollow segments has at least one facing attachment flange, andwherein each facing attachment flange projects outwards from a space inside the box and has a corresponding elliptical or circular cross-section. 14. The pylon according to claim 13, wherein the plurality of hollow segments are connected to each other via respective facing attachment flanges, the facing attachment flanges being fixed to each other by attachment means outside an exterior of the plurality of hollow segments. 15. The pylon according to claim 14, wherein the attachment means includes bolts or rivets. 16. The pylon according to claim 13, wherein at least one of the plurality of hollow segments is a tapered and truncated cone. 17. The pylon according to claim 13, wherein the plurality of hollow segments includes: a first hollow segment with a first central axis; anda second hollow segment with a second central axis,wherein the second central axis is parallel to a turbojet central axis, andwherein the first central axis is inclined relative to the second central axis and to the turbojet central axis. 18. The pylon according to claim 17, wherein the second hollow segment has an elliptical cross-section orthogonal to the second central axis. 19. The pylon according to claim 18, wherein a major axis of the elliptical cross-section of the second hollow segment is vertically perpendicular to the turbojet central axis. 20. The pylon according to claim 17, wherein the plurality of hollow segments further includes a third hollow segment with a third central axis and an elliptical cross-section, the elliptical cross-section tapering and reducing in size in an aft direction of the turbojet central axis.
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