| 发明名称 | Beam for suspending a turboshaft engine from an aircraft structure | ||
| 摘要 | A beam for suspending a turboshaft engine from an aircraft structure, including a first attachment mechanism configured to be secured to the aircraft structure and at least one second attachment mechanism configured to be secured to the engine. The beam is at least partially made from a metal-matrix composite material including reinforcing fibers. In one embodiment, the beam takes a form of a circle arc. | ||
| 申请公布号 | US9321537(B2) | 申请公布日期 | 2016.04.26 |
| 申请号 | US201013387534 | 申请日期 | 2010.07.27 |
| 申请人 | SNECMA | 发明人 | Dunleavy Patrick;Lefort Guillaume;Masson Richard;Roux Thibaut Francois;Seize Guilhem |
| 分类号 | B64D27/26;C22C47/04;C22C47/06;C22C47/20;C22C49/11 | 主分类号 | B64D27/26 |
| 代理机构 | Oblon, McClelland, Maier & Neustadt, L.L.P. | 代理人 | Oblon, McClelland, Maier & Neustadt, L.L.P. |
| 主权项 | 1. A beam for suspending a turboshaft engine from a structure of an aircraft, comprising: a first attachment means to be fixed to the aircraft structure; and second and third attachment means to be fixed to the engine, wherein the beam is made at least in part of metal matrix composite incorporating reinforcing fibers, wherein the beam is in a shape of an arc encompassing less than a full circle, the second and third attachment means are arranged at first and second ends of the beam, respectively, and wherein the reinforcing fibers extend only between the second and third attachment means along the arc. | ||
| 地址 | Paris FR | ||