发明名称 |
COMPOSITE WING EDGE ATTACHMENT AND METHOD |
摘要 |
A composite edge of an aircraft wing includes a composite wing box skin panel, attached to an outward wing spar in an attachment region, and a composite ramp, upon an outer surface of, and co-cured with, the composite wing box skin panel. The composite wing box skin panel has a proximal end and a distal end, with an overhanging edge, with substantially constant thickness and ply count in the attachment region. The composite ramp has a maximum ramp thickness at the distal end, is the distal end being set back from the overhanging edge, defining a shoulder on the overhanging edge. A composite wing edge skin panel, having a thickness substantially equal to the maximum ramp thickness, is attached to the composite wing box skin panel at the shoulder and adjacent to the distal end of the ramp. |
申请公布号 |
US2016244143(A1) |
申请公布日期 |
2016.08.25 |
申请号 |
US201414488987 |
申请日期 |
2014.09.17 |
申请人 |
The Boeing Company |
发明人 |
Foster Chris J.;Santini Gregory M.;Dovey John V. |
分类号 |
B64C3/28;B64F5/00;B64C3/26 |
主分类号 |
B64C3/28 |
代理机构 |
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代理人 |
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主权项 |
1. A composite fixed edge of an aircraft wing, comprising:
a composite wing box skin panel, attached to an outward wing spar in an attachment region, with an overhanging edge, having
substantially constant thickness and ply count in the attachment region; anda composite ramp, upon an outer surface of, and co-cured with, the composite wing box skin panel, having a proximal end and a distal end, with a maximum ramp thickness at the distal end, the distal end being set back from the overhanging edge, defining a shoulder on the overhanging edge; and a composite wing edge skin panel, having a thickness substantially equal to the maximum ramp thickness, attached to the composite wing box skin panel at the shoulder and adjacent to the distal end of the ramp. |
地址 |
Huntington Beach CA US |