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公开(公告)号:US6114050A
公开(公告)日:2000-09-05
申请号:US222371
申请日:1998-12-29
申请人: Willard N. Westre , Heather C. Allen-Lilly , Donald J. Ayers , Samuel E. Cregger , David W. Evans , Donald L. Grande , Daniel J. Hoffman , Mark E. Rogalski , Robert J. Rothschilds
发明人: Willard N. Westre , Heather C. Allen-Lilly , Donald J. Ayers , Samuel E. Cregger , David W. Evans , Donald L. Grande , Daniel J. Hoffman , Mark E. Rogalski , Robert J. Rothschilds
CPC分类号: B64C30/00 , B32B15/08 , B32B15/14 , B32B3/12 , B32B37/146 , B32B5/02 , B32B5/12 , B32B7/005 , B64C1/12 , B64C3/26 , B32B2250/42 , B32B2255/06 , B32B2260/023 , B32B2260/046 , B32B2262/10 , B32B2262/106 , B32B2305/076 , B32B2307/306 , B32B2307/54 , B32B2307/552 , B32B2307/714 , B32B2311/18 , B32B2605/18 , B64C2001/0072 , Y02T50/433 , Y10T428/1234 , Y10T428/12431 , Y10T428/12444 , Y10T428/12569 , Y10T428/12806 , Y10T428/24165 , Y10T428/249942 , Y10T428/26 , Y10T428/31678
摘要: The invention provides a hybrid laminate and skin panels of hybrid laminate structure that are suitable for a supersonic civilian aircraft. The hybrid laminates include layups of layers of titanium alloy foil and composite plies, that are optimally oriented to counteract forces encountered in use, that are bonded to a central core structure, such as titanium alloy honeycomb. The reinforcing fibers of the composite plies are selected from carbon and boron, and the fibers are continuous and parallel oriented within each ply. However, some plies may be oriented at angles to other plies. Nevertheless, in a preferred embodiment of the invention, a substantial majority of, or all of, the fibers of the hybrid laminates are oriented in a common direction. The outer surfaces of the laminates include a layer of titanium foil to protect the underlying composite-containing structure from the environment, and attack by solvents, and the like.
摘要翻译: 本发明提供了一种适用于超音速民用飞机的混合层压板和混合层压结构的蒙皮板。 混合层压板包括钛合金箔层和复合层层的叠层,其被最佳地取向以抵消使用中遇到的力,其结合到中心芯结构,例如钛合金蜂窝体。 复合帘布层的增强纤维选自碳和硼,并且纤维在每个帘布层内连续且平行取向。 然而,一些层可以与其他层相交角度。 然而,在本发明的优选实施方案中,混合层叠体的纤维的绝大多数或全部是在共同的方向上取向的。 层压板的外表面包括一层钛箔,用于保护下面的复合材料结构免受环境侵蚀,并受到溶剂的侵蚀等。
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公开(公告)号:US5866272A
公开(公告)日:1999-02-02
申请号:US585304
申请日:1996-01-11
申请人: Willard N. Westre , Heather C. Allen-Lilly , Donald J. Ayers , Samuel E. Cregger , David W. Evans , Donald L. Grande , Daniel J. Hoffman , Mark E. Rogalski , Robert J. Rothschilds
发明人: Willard N. Westre , Heather C. Allen-Lilly , Donald J. Ayers , Samuel E. Cregger , David W. Evans , Donald L. Grande , Daniel J. Hoffman , Mark E. Rogalski , Robert J. Rothschilds
CPC分类号: B64C30/00 , B32B15/08 , B32B15/14 , B32B3/12 , B32B37/146 , B32B5/02 , B32B5/12 , B32B7/005 , B64C1/12 , B64C3/26 , B32B2250/42 , B32B2255/06 , B32B2260/023 , B32B2260/046 , B32B2262/10 , B32B2262/106 , B32B2305/076 , B32B2307/306 , B32B2307/54 , B32B2307/552 , B32B2307/714 , B32B2311/18 , B32B2605/18 , B64C2001/0072 , Y02T50/433 , Y10T428/1234 , Y10T428/12431 , Y10T428/12444 , Y10T428/12569 , Y10T428/12806 , Y10T428/24165 , Y10T428/249942 , Y10T428/26 , Y10T428/31678
摘要: The invention provides a hybrid laminate and skin panels of hybrid laminate structure that are suitable for a supersonic civilian aircraft. The hybrid laminates include layups of layers of titanium alloy foil and composite plies, that are optimally oriented to counteract forces encountered in use, that are bonded to a central core structure, such as titanium alloy honeycomb. The reinforcing fibers of the composite plies are selected from carbon and boron, and the fibers are continuous and parallel oriented within each ply. However, some plies may be oriented at angles to other plies. Nevertheless, in a preferred embodiment of the invention, a substantial majority of, or all of, the fibers of the hybrid laminates are oriented in a common direction. The outer surfaces of the laminates include a layer of titanium foil to protect the underlying composite-containing structure from the environment, and attack by solvents, and the like.
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