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公开(公告)号：US20120061512A1
公开(公告)日：2012-03-15
申请号：US13300487
申请日：2011-11-18
IPC分类号： B64C1/06 , B64D11/00 , B64C1/14 , B32B3/24 , B32B3/28 , B32B3/00 , B32B3/12 , B21D53/88 , B32B3/30
CPC分类号： B64C1/069 , B64C1/068 , B64C1/12 , B64C1/1492 , B64C2001/0072 , Y02T50/43 , Y10T29/49616 , Y10T29/49622 , Y10T29/49826 , Y10T428/19 , Y10T428/24331 , Y10T428/24612 , Y10T428/24628 , Y10T428/24661
摘要： Structures and methods for joining composite fuselage sections and other panel assemblies together are disclosed herein. In one embodiment, a shell structure configured in accordance with the present invention includes a first panel portion positioned adjacent to a second panel portion. The first panel portion can include a first stiffener attached to a first composite skin, and the second panel portion can include a second stiffener attached to a second composite skin. The shell structure can further include a fitting extending across a first edge region of the first panel portion and a second edge region of the second panel portion. A first end portion of the fitting can be attached to the first stiffener and the first composite skin, and a second end portion of the fitting can be attached to a second stiffener and a second composite skin, to join the first panel portion to the second panel portion.
摘要翻译： 本文公开了将复合机身部分和其它面板组件连接在一起的结构和方法。 在一个实施例中，根据本发明构造的壳结构包括邻近第二面板部分定位的第一面板部分。 第一面板部分可以包括附接到第一复合皮肤的第一加强件，并且第二面板部分可以包括附接到第二复合皮肤的第二加强件。 外壳结构还可以包括跨过第一面板部分的第一边缘区域延伸的配件和第二面板部分的第二边缘区域。 配件的第一端部可以附接到第一加强件和第一复合表皮，并且配件的第二端部可以附接到第二加强件和第二复合表皮，以将第一面板部分连接到第二加强件 面板部分。
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公开(公告)号：US07325771B2
公开(公告)日：2008-02-05
申请号：US10949848
申请日：2004-09-23
IPC分类号： B64C1/12
CPC分类号： B64C1/069 , B64C1/068 , B64C1/12 , B64C1/1492 , B64C2001/0072 , Y02T50/43 , Y10T29/49616 , Y10T29/49622 , Y10T29/49826 , Y10T428/19 , Y10T428/24331 , Y10T428/24612 , Y10T428/24628 , Y10T428/24661
摘要： Structures and methods for joining composite fuselage sections and other panel assemblies together are disclosed herein. In one embodiment, a shell structure configured in accordance with the present invention includes a first panel portion positioned adjacent to a second panel portion. The first panel portion can include a first stiffener attached to a first composite skin, and the second panel portion can include a second stiffener attached to a second composite skin. The shell structure can further include a fitting extending across a first edge region of the first panel portion and a second edge region of the second panel portion. A first end portion of the fitting can be attached to the first stiffener and the first composite skin, and a second end portion of the fitting can be attached to a second stiffener and a second composite skin, to join the first panel portion to the second panel portion.
摘要翻译： 本文公开了将复合机身部分和其它面板组件连接在一起的结构和方法。 在一个实施例中，根据本发明构造的壳结构包括邻近第二面板部分定位的第一面板部分。 第一面板部分可以包括附接到第一复合皮肤的第一加强件，并且第二面板部分可以包括附接到第二复合皮肤的第二加强件。 外壳结构还可以包括跨过第一面板部分的第一边缘区域延伸的配件和第二面板部分的第二边缘区域。 配件的第一端部可以附接到第一加强件和第一复合表皮，并且配件的第二端部可以附接到第二加强件和第二复合表皮，以将第一面板部分连接到第二加强件 面板部分。
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公开(公告)号：US08882040B2
公开(公告)日：2014-11-11
申请号：US13300487
申请日：2011-11-18
CPC分类号： B64C1/069 , B64C1/068 , B64C1/12 , B64C1/1492 , B64C2001/0072 , Y02T50/43 , Y10T29/49616 , Y10T29/49622 , Y10T29/49826 , Y10T428/19 , Y10T428/24331 , Y10T428/24612 , Y10T428/24628 , Y10T428/24661
摘要： Structures and methods for joining composite fuselage sections and other panel assemblies together. In one embodiment, a shell structure configured in accordance with the present invention includes a first panel portion positioned adjacent to a second panel portion. The first panel portion can include a first stiffener attached to a first composite skin, and the second panel portion can include a second stiffener attached to a second composite skin. The shell structure can further include a fitting extending across a first edge region of the first panel portion and a second edge region of the second panel portion. A first end portion of the fitting can be attached to the first stiffener and the first composite skin, and a second end portion of the fitting can be attached to a second stiffener and a second composite skin, to join the first panel portion to the second panel portion.
摘要翻译： 将复合机身部分和其他面板组件连接在一起的结构和方法。 在一个实施例中，根据本发明构造的壳结构包括邻近第二面板部分定位的第一面板部分。 第一面板部分可以包括附接到第一复合皮肤的第一加强件，并且第二面板部分可以包括附接到第二复合皮肤的第二加强件。 外壳结构还可以包括跨过第一面板部分的第一边缘区域延伸的配件和第二面板部分的第二边缘区域。 配件的第一端部可以附接到第一加强件和第一复合表皮，并且配件的第二端部可以附接到第二加强件和第二复合表皮，以将第一面板部分连接到第二加强件 面板部分。
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公开(公告)号：US08443575B1
公开(公告)日：2013-05-21
申请号：US12606331
申请日：2009-10-27
IPC分类号： E04C2/54
CPC分类号： B64C1/1461 , B64C1/1446 , E04C2/54 , E05D15/00
摘要： A door for an aircraft wing fuel tank access opening includes an outer impact resistant composite door panel, and an inner composite door panel. Double seals on the inner door panel prevent fuel leakage, and a chamfered outer edge on the outer door panel transfers a component of impact loads laterally into the wing skin to increase kinetic energy absorption.
摘要翻译： 用于飞机机翼燃料箱进入开口的门包括外部抗冲击复合门板和内部复合门板。 内门面板上的双重密封防止燃油泄漏，外门板上的倒角外边缘将冲击载荷的一部分侧向转移到机翼皮肤中，以增加动能吸收。
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公开(公告)号：US08061035B2
公开(公告)日：2011-11-22
申请号：US12016258
申请日：2008-01-18
IPC分类号： B21D53/88
CPC分类号： B64C1/069 , B64C1/068 , B64C1/12 , B64C1/1492 , B64C2001/0072 , Y02T50/43 , Y10T29/49616 , Y10T29/49622 , Y10T29/49826 , Y10T428/19 , Y10T428/24331 , Y10T428/24612 , Y10T428/24628 , Y10T428/24661
摘要： Structures and methods for joining composite fuselage sections and other panel assemblies together are disclosed herein. In one embodiment, a shell structure configured in accordance with the present invention includes a first panel portion positioned adjacent to a second panel portion. The first panel portion can include a first stiffener attached to a first composite skin, and the second panel portion can include a second stiffener attached to a second composite skin. The shell structure can further include a fitting extending across a first edge region of the first panel portion and a second edge region of the second panel portion. A first end portion of the fitting can be attached to the first stiffener and the first composite skin, and a second end portion of the fitting can be attached to a second stiffener and a second composite skin, to join the first panel portion to the second panel portion.
摘要翻译： 本文公开了将复合机身部分和其它面板组件连接在一起的结构和方法。 在一个实施例中，根据本发明构造的壳结构包括邻近第二面板部分定位的第一面板部分。 第一面板部分可以包括附接到第一复合皮肤的第一加强件，并且第二面板部分可以包括附接到第二复合皮肤的第二加强件。 外壳结构还可以包括跨过第一面板部分的第一边缘区域延伸的配件和第二面板部分的第二边缘区域。 配件的第一端部可以附接到第一加强件和第一复合表皮，并且配件的第二端部可以附接到第二加强件和第二复合表皮，以将第一面板部分连接到第二加强件 面板部分。
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公开(公告)号：US08869403B2
公开(公告)日：2014-10-28
申请号：US13225057
申请日：2011-09-02
IPC分类号： B21D53/88
CPC分类号： B64C1/069 , B64C1/068 , B64C1/12 , B64C1/1492 , B64C2001/0072 , Y02T50/43 , Y10T29/49616 , Y10T29/49622 , Y10T29/49826 , Y10T428/19 , Y10T428/24331 , Y10T428/24612 , Y10T428/24628 , Y10T428/24661
摘要： Structures and methods for joining composite fuselage sections and other panel assemblies together are disclosed herein. In one embodiment, a shell structure configured in accordance with the present disclosure includes a first panel portion positioned adjacent to a second panel portion. The first panel portion can include a first stiffener attached to a first composite skin, and the second panel portion can include a second stiffener attached to a second composite skin. The shell structure can include a fitting extending across a first edge region of the first panel portion and a second edge region of the second panel portion. A first end portion of the fitting can be attached to the first stiffener and the first composite skin, and a second end portion of the fitting can be attached to a second stiffener and a second composite skin, to join the first panel portion to the second panel portion.
摘要翻译： 本文公开了将复合机身部分和其它面板组件连接在一起的结构和方法。 在一个实施例中，根据本公开构造的壳结构包括邻近第二面板部分定位的第一面板部分。 第一面板部分可以包括附接到第一复合皮肤的第一加强件，并且第二面板部分可以包括附接到第二复合皮肤的第二加强件。 外壳结构可以包括穿过第一面板部分的第一边缘区域延伸的配件和第二面板部分的第二边缘区域。 配件的第一端部可以附接到第一加强件和第一复合表皮，并且配件的第二端部可以附接到第二加强件和第二复合表皮，以将第一面板部分连接到第二加强件 面板部分。
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公开(公告)号：US20140165361A1
公开(公告)日：2014-06-19
申请号：US13225057
申请日：2011-09-02
IPC分类号： B64C1/06
CPC分类号： B64C1/069 , B64C1/068 , B64C1/12 , B64C1/1492 , B64C2001/0072 , Y02T50/43 , Y10T29/49616 , Y10T29/49622 , Y10T29/49826 , Y10T428/19 , Y10T428/24331 , Y10T428/24612 , Y10T428/24628 , Y10T428/24661
摘要： Structures and methods for joining composite fuselage sections and other panel assemblies together are disclosed herein. In one embodiment, a shell structure configured in accordance with the present disclosure includes a first panel portion positioned adjacent to a second panel portion. The first panel portion can include a first stiffener attached to a first composite skin, and the second panel portion can include a second stiffener attached to a second composite skin. The shell structure can include a fitting extending across a first edge region of the first panel portion and a second edge region of the second panel portion. A first end portion of the fitting can be attached to the first stiffener and the first composite skin, and a second end portion of the fitting can be attached to a second stiffener and a second composite skin, to join the first panel portion to the second panel portion.
摘要翻译： 本文公开了将复合机身部分和其它面板组件连接在一起的结构和方法。 在一个实施例中，根据本公开构造的壳结构包括邻近第二面板部分定位的第一面板部分。 第一面板部分可以包括附接到第一复合皮肤的第一加强件，并且第二面板部分可以包括附接到第二复合皮肤的第二加强件。 外壳结构可以包括穿过第一面板部分的第一边缘区域延伸的配件和第二面板部分的第二边缘区域。 配件的第一端部可以附接到第一加强件和第一复合表皮，并且配件的第二端部可以附接到第二加强件和第二复合表皮，以将第一面板部分连接到第二加强件 面板部分。
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