发明名称 |
Method of making shaped composite stringers |
摘要 |
A stiffened skin panel of an aircraft that includes an aircraft skin panel of composite material and a composite stringer consolidated with the aircraft skin panel. The stringer has a pair of stringer sides, each extending from a stringer top to a stringer leg. The stringer sides may each extend through a wide radius, smooth continuous curve to a stringer leg. The wide radius, smooth continuous curve may be proximate the base of the stringer side in a region where the stringer side transitions to the stringer leg. |
申请公布号 |
EP2152574(B1) |
申请公布日期 |
2016.12.07 |
申请号 |
EP20080827299 |
申请日期 |
2008.05.21 |
申请人 |
The Boeing Company |
发明人 |
GUZMAN, Juan, C.;MCCARVILLE, Douglas, A.;ROTTER, Daniel, M.;ROBINS, Brian, G. |
分类号 |
B64C1/06;B29C43/10;B29C43/36;B29C70/34;B29L22/00;B29L31/54;B64C1/00;B64C1/12;B64C3/18 |
主分类号 |
B64C1/06 |
代理机构 |
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代理人 |
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主权项 |
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地址 |
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