IPC분류정보
국가/구분 |
United States(US) Patent
등록
|
국제특허분류(IPC7판) |
|
출원번호 |
US-0073646
(2005-03-08)
|
등록번호 |
US-7325770
(2008-02-05)
|
우선권정보 |
FR-04 02387(2004-03-08) |
발명자
/ 주소 |
- Chevalier,Lydie Marie Helene
- Tesniere,Marc Patrick
- Noirclerc,Gabriel
|
출원인 / 주소 |
|
대리인 / 주소 |
Oblon, Spivak, McClelland, Maier & Neustadt, P.C.
|
인용정보 |
피인용 횟수 :
11 인용 특허 :
2 |
초록
▼
The invention pertains to an engine mount onto an aircraft structure comprising at least one connection means between a first and a second element such as an engine case and said structure, characterized by the fact that said connection means comprises an eccentric member housed in a bore of the fir
The invention pertains to an engine mount onto an aircraft structure comprising at least one connection means between a first and a second element such as an engine case and said structure, characterized by the fact that said connection means comprises an eccentric member housed in a bore of the first element, being rotational about a first axis, the eccentric member comprising a trunnion attached to the second element and of axis off-centred with respect to the first axis of rotation, the eccentric member being rotational about said off-centred axis. The solution of the invention has the advantage of allowing a compact assembly.
대표청구항
▼
The invention claimed is: 1. An engine mount for an aircraft structure, comprising at least one connection device configured to connect a first element to a second element, said first and second elements being between an engine case and said aircraft structure, wherein said connection device compri
The invention claimed is: 1. An engine mount for an aircraft structure, comprising at least one connection device configured to connect a first element to a second element, said first and second elements being between an engine case and said aircraft structure, wherein said connection device comprises: a first eccentric member housed in a first bore of the first element, said first eccentric member being rotational about a first eccentric member axis, and a first pivot pin passing through said first eccentric member via a first ball joint, said first pivot pin being attached to the second element, said first pivot pin having a first pivot pin axis offset with respect to the first eccentric member axis, the first eccentric member being rotational about said first pivot pin axis. 2. The engine mount as in claim 1, wherein the first or second element is a beam or any other intermediate part between the engine case and the structure. 3. The engine mount as in claim 1, wherein the first eccentric member is in the form of a disc. 4. The engine mount Mount as in claim 3, wherein the first pivot pin is mounted on the disc. 5. The engine mount as in claim 1 wherein the first eccentric member is mounted in said first bore of said first element via a second ball-joint. 6. The engine mount as in claim 2, wherein the first element is a beam between the engine case and the aircraft structure, and the second element is an annular frame of the engine case, the connection device further comprising a pin distant from said first eccentric member, said pin being configured to swivel between the beam and the annular frame of the engine case. 7. The engine mount as in claim 2 wherein the first element is a beam between the engine case and the aircraft structure, and the second element is an annular frame of the engine case, the connection device further comprising a second eccentric member with a second eccentric member axis, and a second pivot pin passing through said second eccentric member and having a second pivot pin axis offset from said second eccentric member axis and offset from said first pivot pin axis. 8. The engine mount as in claim 2 wherein the first element is a beam between the engine case and the aircraft structure, and the second element is said aircraft structure, the connection device further comprising a a pin distant from said first eccentric member, said pin being configured to swivel between the beam and the aircraft structure. 9. The engine mount as in claim 2 wherein the first element is a beam between the engine case and the aircraft structure, and the second element is the aircraft structure, the connection device further comprising a second eccentric member with a second eccentric member axis, and a second pivot pin passing through said second eccentric member and having a second pivot pin axis offset from said second eccentric member axis and offset from said first pivot pin axis. 10. The engine mount as in claim 2 wherein the first element is an intermediate part arranged crosswise between the engine case and the aircraft structure, and the second element is an annular frame integral with the engine case, wherein said first eccentric member is arranged at a first transverse end of said intermediate part, the connection device further comprising second eccentric member arranged at a second transverse end of said intermediate part, wherein said first and second transverse ends are opposite each other. 11. The engine mount as in claim 6, wherein said distant pin is mounted in its housing by a ball-joint. 12. The engine mount as in claim 1, further comprising at least one standby connection member between said first element and said second element. 13. The engine mount as in claim 12, further comprising a second standby connection member and a third standby connection member, each positioned between the engine case and the aircraft structure and each arranged on either side of a median vertical plane for said engine mount. 14. The engine mount as in claim 12, wherein said at least one standby connection member is formed by a pin housed in a bore with a set clearance. 15. The engine mount as in claim 6, wherein said pin distant from said first eccentric member is mounted in its bearing and is axially mobile. 16. The engine mount as in claim 1, wherein said first ball joint is housed in a bore of said first eccentric member, and wherein said first eccentric member axis does not pass through said bore of said first eccentric member. 17. The engine mount as in claim 1, wherein said first element defines a second bore and said connection device further comprises: a second eccentric member housed in said second bore, said second eccentric member being rotational about a second eccentric member axis; and a second pivot pin passing through said second eccentric member via a second ball joint, said second pivot pin being attached to said aircraft structure, said second pivot pin having a second pivot pin axis offset with respect to the second eccentric member axis, wherein said first pivot pin axis is offset with respect to said second pivot pin axis, and said first eccentric member axis is offset with respect to said second eccentric member axis. 18. The engine mount as in claim 17, wherein: said first ball joint is housed in a bore of said first eccentric member, and said first eccentric member axis does not pass through said bore of said first eccentric member, and said second ball joint is housed in a bore of said second eccentric member, and said second eccentric member axis does not pass through said bore of said second eccentric member. 19. The engine mount as in claim 17, wherein said first and second bores defined by said first element do not overlap with each other. 20. The engine mount as in claim 17, wherein: said first eccentric member axis and said first pivot pin axis do not pass through said second bore defined by said first element, and said second eccentric member axis and said second pivot pin axis do not pass through said first bore defined by said first element. 21. The engine mount as in claim 17, wherein: said first eccentric member axis and said second eccentric member axis are not coincident with each other, and said first pivot pin axis and said second pivot pin axis are not coincident with each other. 22. The engine mount as in claim 17, wherein: the first element is an intermediate part arranged crosswise between the engine case and the aircraft structure, wherein said first eccentric member is arranged at a first transverse end of said intermediate part, said connection device further comprising a pin arranged at a second transverse end of said intermediate part, wherein said first and second transverse ends are opposite each other, said pin being configured to swivel between the intermediate part and the engine case, and said second eccentric member is arranged between said first and second transverse ends of said intermediate part.
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