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公开(公告)号：US08349105B2
公开(公告)日：2013-01-08
申请号：US12776781
申请日：2010-05-10
CPC分类号： B64C1/061 , B29C70/207 , B29C70/30 , B29C70/38 , B29D99/0003 , B29L2031/3082 , B64C1/064 , B64C2001/0072 , Y02T50/43 , Y10T29/49622 , Y10T29/49801 , Y10T29/49826 , Y10T428/24628
摘要： A curved composite aircraft frame comprises a multi-ply composite laminate having a generally Z-shaped cross section. At least certain of the laminate plies include unidirectional reinforcing fibers that are substantially tangent at substantially all points along the curvature of the frame.
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公开(公告)号：US08496206B2
公开(公告)日：2013-07-30
申请号：US12762129
申请日：2010-04-16
申请人： Kent E. Johnson , Mark A. Ulvin
发明人： Kent E. Johnson , Mark A. Ulvin
IPC分类号： B64C1/00
CPC分类号： B61D17/041 , B63B3/28 , B63B3/36 , B64C1/12 , B64C3/182 , B64C3/26 , B64C2001/0072 , B64C2001/0081 , Y02T50/43 , Y10T29/49616 , Y10T29/49622 , Y10T29/53978 , Y10T156/1089 , Y10T428/24033 , Y10T428/24174 , Y10T428/24182 , Y10T428/24198
摘要： Structural panels for use in manufacturing aircraft fuselages and other structures are disclosed herein. In one embodiment, a structural panel configured in accordance with the invention includes a skin and at least first and second stiffeners. The first stiffener can have a first flange portion mated to the skin and a first raised portion projecting away from the skin. The second stiffener can have a second flange portion mated to the skin and a second raised portion projecting away from the skin. At least one of the first flange portion of the first stiffener and the second flange portion of the second stiffener can extend toward the other of the first flange portion and the second flange portion to form an at least approximately continuous support surface to which a frame can be attached.
摘要翻译： 本文公开了用于制造飞机机身和其它结构的结构面板。 在一个实施例中，根据本发明构造的结构面板包括皮肤和至少第一和第二加强筋。 第一加强件可以具有与皮肤配合的第一凸缘部分和远离皮肤突出的第一凸起部分。 第二加强件可以具有与皮肤配合的第二凸缘部分和远离皮肤突出的第二凸起部分。 第一加强件的第一凸缘部分和第二加强件的第二凸缘部分中的至少一个可以朝向第一凸缘部分和第二凸缘部分中的另一个延伸，以形成至少近似连续的支撑表面，框架可向该支撑表面 被附上
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公开(公告)号：US20110097554A1
公开(公告)日：2011-04-28
申请号：US12776781
申请日：2010-05-10
CPC分类号： B64C1/061 , B29C70/207 , B29C70/30 , B29C70/38 , B29D99/0003 , B29L2031/3082 , B64C1/064 , B64C2001/0072 , Y02T50/43 , Y10T29/49622 , Y10T29/49801 , Y10T29/49826 , Y10T428/24628
摘要： A curved composite aircraft frame comprises a multi-ply composite laminate having a generally Z-shaped cross section. At least certain of the laminate plies include unidirectional reinforcing fibers that are substantially tangent at substantially all points along the curvature of the frame.
摘要翻译： 弯曲的复合飞机框架包括具有大致Z形横截面的多层复合层压板。 至少某些层压板包括在沿着框架的曲率的基本上所有点处基本上切线的单向增强纤维。
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公开(公告)号：US07716835B2
公开(公告)日：2010-05-18
申请号：US11522184
申请日：2006-09-14
申请人： Kent E. Johnson , Mark A. Ulvin
发明人： Kent E. Johnson , Mark A. Ulvin
IPC分类号： B21D53/88
CPC分类号： B61D17/041 , B63B3/28 , B63B3/36 , B64C1/12 , B64C3/182 , B64C3/26 , B64C2001/0072 , B64C2001/0081 , Y02T50/43 , Y10T29/49616 , Y10T29/49622 , Y10T29/53978 , Y10T156/1089 , Y10T428/24033 , Y10T428/24174 , Y10T428/24182 , Y10T428/24198
摘要： Methods of manufacturing structural panels for use in manufacturing aircraft fuselages and other structures are disclosed herein. In one embodiment, a structural panel configured in accordance with the invention includes a skin and at least first and second stiffeners. The first stiffener can have a first flange portion mated to the skin and a first raised portion projecting away from the skin. The second stiffener can have a second flange portion mated to the skin and a second raised portion projecting away from the skin. At least one of the first flange portion of the first stiffener and the second flange portion of the second stiffener can extend toward the other of the first flange portion and the second flange portion to form an at least approximately continuous support surface to which a frame can be attached.
摘要翻译： 本文公开了制造用于制造飞机机身和其它结构的结构面板的方法。 在一个实施例中，根据本发明构造的结构面板包括皮肤和至少第一和第二加强筋。 第一加强件可以具有与皮肤配合的第一凸缘部分和远离皮肤突出的第一凸起部分。 第二加强件可以具有与皮肤配合的第二凸缘部分和远离皮肤突出的第二凸起部分。 第一加强件的第一凸缘部分和第二加强件的第二凸缘部分中的至少一个可以朝向第一凸缘部分和第二凸缘部分中的另一个延伸，以形成至少近似连续的支撑表面，框架可向该支撑表面 被附上
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