초록 ▼

This invention relates to a force transmission system (50) between a turboprop and an attachment pylon, comprising: a first and a second force transmission device (52a, 52b) each comprising a first hollow cylinder (54) with an axis (56) that will be made parallel to a first force transmission direct

This invention relates to a force transmission system (50) between a turboprop and an attachment pylon, comprising: a first and a second force transmission device (52a, 52b) each comprising a first hollow cylinder (54) with an axis (56) that will be made parallel to a first force transmission direction, said first cylinder defining a first space (58) full of a fluid (60) and closed off in a sealed manner at its two opposite ends, by a first damping layer (62) that will bear in contact with a bearing element (66) of the turboprop, and by a second damping layer (64) that will bear in contact with a bearing element (68) of the attachment device, said first and second layers possibly being compressed by the pressure of said fluid; andfirst means (70) of fluid communication between the two spaces (58, 58).

대표청구항 ▼

1. A force transmission system between a turboprop and an attachment device of the turboprop on an aircraft, the force transmission system comprising: a first force transmission device and a second force transmission device; andfirst means for fluid communication between the first force transmission

1. A force transmission system between a turboprop and an attachment device of the turboprop on an aircraft, the force transmission system comprising: a first force transmission device and a second force transmission device; andfirst means for fluid communication between the first force transmission device and the second force transmission device,wherein each of the first force transmission device and the second force transmission device includes a first hollow cylinder with an axis that is parallel to a first force transmission directionwherein each of the first hollow cylinders has a first space full of a first fluid and is closed off in a sealed manner at two opposite ends thereof by a first damping layer that bears in contact with a bearing element of the turboprop and by a second damping layer that bears in contact with a bearing element of the attachment device, respectively,wherein said first and second damping layers are positioned so as to be compressed by a pressure of said first fluid, andwherein the first means for fluid communication is disposed between said first spaces. 2. The force transmission system according to claim 1, further comprising second means for fluid communication between the first force transmission device and the second force transmission device, wherein each of the first and second force transmission devices further includes a second hollow cylinder with an axis that is parallel to a second force transmission direction,wherein each of the second hollow cylinders has a second space full of a second fluid and is closed off in a sealed manner at two opposite ends thereof by a third damping layer that bears in contact with a bearing element of the turboprop and by a fourth damping layer that bears in contact with a bearing element of the attachment device, respectively,wherein said third and fourth damping layers are positioned so as to be compressed by a pressure of said second fluid, andwherein the second means for fluid communication is disposed between said second spaces. 3. The force transmission system according to claim 2, further comprising third means for fluid communication between the first force transmission device and the second force transmission device, wherein each of the first and second force transmission devices further includes a third hollow cylinder with an axis that is parallel to a third force transmission direction,wherein each of the third hollow cylinders has a third space full of a third fluid and closed off in a sealed manner at two opposite ends thereof by a fifth damping layer that bears in contact with a bearing element of the turboprop and by a sixth damping layer that bears in contact with a bearing element of the attachment device, respectively,wherein said fifth and sixth damping layers are positioned so as to be compressed by a pressure of said third fluid, andwherein the third means for fluid communication is disposed between said third spaces. 4. The force transmission system according to claim 3, wherein the first, second, and third force transmission directions are orthogonal to each other. 5. The force transmission system according to claim 1, wherein the first and second damping layers include rubber or elastomer. 6. The force transmission system according to claim 1, wherein the first force transmission device further includes a first damping block in which the first hollow cylinder of the first force transmission device is embedded, said first damping block forming said first and second damping layers of the first force transmission device, and wherein the second force transmission device further includes a second damping block in which the first hollow cylinder of the second force transmission device is embedded, said second block forming said third and fourth damping layers of the second force transmission device. 7. The force transmission system according to claim 6, wherein each of the first and second damping blocks is cubic or parallelepiped in shape. 8. An aircraft engine assembly comprising: a turboprop;a device for attachment of said turboprop on an aircraft; andat least one force transmission system according to claim 1, inserted between said turboprop and said attachment device. 9. An engine assembly according to claim 8, wherein said bearing element of the attachment device associated with the first force transmission device, said bearing element of the attachment device associated with the second force transmission device, said bearing element of the turboprop associated with the first force transmission device, and said bearing element of the turboprop associated with the second force transmission device, each have three bearing surfaces approximately orthogonal to each other and forming a corner. 10. An aircraft comprising at least one engine assembly according to claim 9. 11. An aircraft comprising at least one engine assembly according to claim 8. 12. The force transmission system according to claim 1, wherein the first fluid is incompressible. 13. The force transmission system according to claim 1, wherein the first fluid is oil. 14. The force transmission system according to claim 1, wherein the first means for fluid communication includes one of flexible pipes, rigid pipes, and ducts.