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公开(公告)号：US08371531B2
公开(公告)日：2013-02-12
申请号：US12521819
申请日：2008-01-03
IPC分类号： B64C1/14
CPC分类号： B64C1/1492 , Y10T29/49826
摘要： A method for assembling a cabin window to a bay in a side wall of an aircraft fuselage, where the cabin window including an outer transparent element and at least one inner transparent element, includes making a non-through hole in a portion of the side wall. The outer transparent element includes a first part having a diameter greater than that of the bay and which is shaped to co-operate with the portion of the side wall to block the outer transparent element in the bay both laterally and longitudinally. A second part of the outer transparent element has a groove that projects into the fuselage. The outer transparent element and the at least one inner transparent element are welded to the fuselage using a strap which presses a seal against at least the fuselage and the inner wall of the groove.
摘要翻译： 一种用于将舱窗组装到飞行器机身的侧壁中的舱的方法，其中所述舱窗包括外部透明元件和至少一个内透明元件，包括在侧壁的一部分中形成非通孔 。 外部透明元件包括具有大于间隔部分的直径的第一部分，该第一部分被成形为与侧壁的一部分配合以在横向和纵向阻挡隔离物中的外部透明元件。 外部透明元件的第二部分具有突出到机身中的凹槽。 外部透明元件和至少一个内部透明元件使用将至少机身和凹槽的内壁压紧密封件的带焊接到机身上。
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公开(公告)号：US20100044513A1
公开(公告)日：2010-02-25
申请号：US12521819
申请日：2008-01-03
CPC分类号： B64C1/1492 , Y10T29/49826
摘要： A method for assembling a cabin window to a bay in a side wall of an aircraft fuselage, the cabin window including an outer transparent element and at least one inner transparent element. A non-through hole is made in a portion of the side wall along the edge of the bay. Subsequently, the outer transparent element is positioned in the bay from the exterior of the fuselage. The element includes a first part which has a diameter greater than that of the bay and which is shaped to co-operate with the above mentioned portion such as to block the outer transparent element in the bay both laterally and longitudinally. A second part of the outer transparent element has a groover that projects into the fuselage. The outer transparent element and the at least one inner transparent element are welded to the fuselage using a strap which presses a seal against at least the fuselage and the inner wall of the groove.
摘要翻译： 一种用于将舱窗组装到飞行器机身的侧壁中的舱的方法，所述舱窗包括外透明元件和至少一个内透明元件。 一个非贯通孔沿着该边缘的边缘在该侧壁的一部分中形成。 随后，外部透明元件从机身外部定位在隔间中。 该元件包括第一部分，该第一部分的直径大于该间隔部分的直径，并且该第一部分被成形为与上述部分配合，以便在横向和纵向上阻挡该间隔室中的外部透明元件。 外部透明元件的第二部分具有投影到机身中的凹槽。 外部透明元件和至少一个内部透明元件使用将至少机身和凹槽的内壁压紧密封件的带焊接到机身上。
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公开(公告)号：US08567720B2
公开(公告)日：2013-10-29
申请号：US12521367
申请日：2008-01-03
IPC分类号： B64C1/14
摘要： The invention relates to a section of fuselage for an aircraft, including frames and bays for receiving cabin windows. According the disclosed embodiments, at least some of the frames include at least one frame segment that surrounds at least one bay, the frame segment having two branches that are disposed to the side of the bay. The ends of the branches are attached to each of the ends of the frame segment such as to form a Y.
摘要翻译： 本发明涉及飞机机身的一部分，包括用于接收舱窗的框架和舱。 根据所公开的实施例，至少一些框架包括围绕至少一个隔间的至少一个框架段，框架段具有设置在隔间侧面的两个分支。 分支的端部附接到框架段的每个端部，以形成Y.
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公开(公告)号：US20110017870A1
公开(公告)日：2011-01-27
申请号：US12521367
申请日：2008-01-05
IPC分类号： B64C1/14
摘要： The invention relates to a section of fuselage for an aircraft, including frames and bays for receiving cabin windows. According the the disclosed embodiments, at least some of the frames include at least one frame segment that surrounds at least one bay, the frame segment having two branches that are disposed to the side of the bay. The ends of the branches are attached to each of the ends of the frame segment such as to form a Y.
摘要翻译： 本发明涉及飞机机身的一部分，包括用于接收舱窗的框架和舱。 根据所公开的实施例，至少一些框架包括围绕至少一个隔间的至少一个框架段，框架段具有设置在托架侧面的两个分支。 分支的端部附接到框架段的每个端部，以形成Y.
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5.发明授权公开(公告)号：US08550399B2
公开(公告)日：2013-10-08
申请号：US12681836
申请日：2008-09-29
IPC分类号： B64C1/00
CPC分类号： B64C1/068 , B64C1/12 , B64C2001/0072 , Y02T50/43
摘要： A fuselage structure for an aircraft fuselage in composite material and an aircraft including such a fuselage structure. The fuselage structure provides savings in mass while allowing grounding of electric systems, and with which substantial mechanical stiffness characteristics may be guaranteed. In the fuselage structure attachment modules provide an assembling function as well as an electric function.
摘要翻译： 用于复合材料中飞机机身的机身结构和包括这种机身结构的飞机。 机身结构提供了质量的节省，同时允许电气系统的接地，并且可以保证其具有显着的机械刚度特性。 在机身结构中，附件模块提供组装功能以及电气功能。
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6.发明申请FUSELAGE STRUCTURE FOR AN AIRCRAFT FUSELAGE IN COMPOSITE MATERIAL AND AIRCRAFT EQUIPPED WITH SUCH A FUSELAGE STRUCTURE 有权复合材料中的飞机熔接的熔敷结构和装有这种熔融结构的飞机公开(公告)号：US20100264273A1
公开(公告)日：2010-10-21
申请号：US12681836
申请日：2008-09-29
CPC分类号： B64C1/068 , B64C1/12 , B64C2001/0072 , Y02T50/43
摘要： A fuselage structure for an aircraft fuselage in composite material and an aircraft including such a fuselage structure. The fuselage structure provides savings in mass while allowing grounding of electric systems, and with which substantial mechanical stiffness characteristics may be guaranteed. In the fuselage structure attachment modules provide an assembling function as well as an electric function.
摘要翻译： 用于复合材料中飞机机身的机身结构和包括这种机身结构的飞机。 机身结构提供了质量的节省，同时允许电气系统的接地，并且可以保证其具有显着的机械刚度特性。 在机身结构中，附件模块提供组装功能以及电气功能。
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