| 发明名称 |
Composite Rib for an Aircraft |
| 摘要 |
A rib is disclosed for use in a torque box of a wing structure provided on an aircraft. The wing structure has a skin panel and a stringer coupled to the skin panel. The rib includes a web defining at least one stringer hole sized to receive the stringer, a shear tie coupled to the web and configured to engage the skin panel, and a clip positioned adjacent the at least one stringer hole. The clip has a base coupled to and aligned with the web, a head extending at an angle relative to the base and configured to engage the stringer, and a transition portion extending between the base and the head. |
| 申请公布号 |
US2016288899(A1) |
申请公布日期 |
2016.10.06 |
| 申请号 |
US201514676271 |
申请日期 |
2015.04.01 |
| 申请人 |
The Boeing Company |
发明人 |
Dobberfuhl James P.;Uhlman Matt D.;Moon William J. |
| 分类号 |
B64C3/18;B64C3/26 |
主分类号 |
B64C3/18 |
| 代理机构 |
|
代理人 |
|
| 主权项 |
1. A rib for a wing structure of an aircraft, the wing structure including a skin panel and a stringer coupled to the skin panel, the rib comprising:
a web defining at least one stringer hole sized to receive the stringer; a shear tie coupled to the web and configured to engage the skin panel; and a clip positioned adjacent the at least one stringer hole, the clip having a base coupled to and aligned with the web, a head extending at an angle relative to the base and configured to engage the stringer, and a transition portion extending between the base and the head. |
| 地址 |
Chicago IL US |
