发明名称 |
Method and arrangement for fastening composite aircraft skins |
摘要 |
The present invention provides a method of fastening an outer composite aircraft skin (12) to an inner substructure (14), which may be the wall of a fuel tank. The method includes the steps of incorporating an electrically conductive layer (26) in an outer surface of the outer composite skin (12), inserting a bolt (11) through the electrically conductive layer (26) and the outer composite skin (12) and through the inner substructure (14), securing the bolt (11) by means of a nut (22) directly or indirectly engaging the inner surface of the inner substructure (14), and applying insulating material (34) over the head (16) of the bolt.
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申请公布号 |
US5845872(A) |
申请公布日期 |
1998.12.08 |
申请号 |
US19950460719 |
申请日期 |
1995.06.02 |
申请人 |
BRITISH AEROSPACE PLC |
发明人 |
PRIDHAM, BARRY J;STEPHENS, AUSTYN C;JONES, CHRISTOPHER C.R. |
分类号 |
B64D45/02;(IPC1-7):B64C1/12;H02H1/04 |
主分类号 |
B64D45/02 |
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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