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1. 发明专利

JP2014111437A Vertically integrated stringers 审中-公开
标题翻译：垂直集成的STRINGERS
公开(公告)号：JP2014111437A
公开(公告)日：2014-06-19
申请号：JP2013242978
申请日：2013-11-25
申请人： Boeing Co , ザ・ボーイング・カンパニーThe Boeing Company
发明人： MOSELAGE III JOHN H
IPC分类号： B64C1/08 , B64C1/26 , B64C3/18
CPC分类号： B64C1/26 , B64C1/061 , B64C1/065 , B64C1/068 , B64C3/182 , B64C3/185 , B64C3/20 , B64C2001/0072 , Y02T50/433 , Y10T29/49622
摘要： PROBLEM TO BE SOLVED: To provide an apparatus and methods for realizing a reinforced aircraft fuselage utilizing vertically oriented circumferential stringers.SOLUTION: Barrel skin of an aircraft fuselage may be reinforced using stringers 628 that are vertically oriented and circumferential. In addition, wing stringers 606, 608 of a wing can be aligned with circumferential stringers. Further, the wing may also have one or more wing spars 610a-b, 612a-b having an elliptical aperture. The elliptical shape may be configured for attachment to the fuselage such that an outer surface of the aperture is disposed nearly at an inner surface of the fuselage.
摘要翻译：要解决的问题：提供一种利用垂直定向的圆周桁条实现增强的飞机机身的装置和方法。解决方案：可以使用垂直取向和周向的桁条628来加强飞行器机身的桶形皮肤。此外，机翼的机翼桁条606,608可与圆周桁条对准。此外，机翼还可以具有一个或多个具有椭圆形孔的翼梁610a-b，612a-b。椭圆形可以被配置为附接到机身，使得孔的外表面几乎位于机身的内表面。

2. 发明专利

JP2014104975A Multi-box wing spar and skin 有权
标题翻译：多盒威斯康星和皮肤
公开(公告)号：JP2014104975A
公开(公告)日：2014-06-09
申请号：JP2013242986
申请日：2013-11-25
申请人： Boeing Co , ザ・ボーイング・カンパニーThe Boeing Company
发明人： MOSELAGE III JOHN H
IPC分类号： B64C3/18 , B64C1/00
CPC分类号： B64C3/185 , B29C70/347 , B29L2031/3085 , B64C1/26 , B64C3/20 , Y02T50/433
摘要： PROBLEM TO BE SOLVED: To provide an apparatus and methods that realize construction of wing sections having multi-box wing spars.SOLUTION: An aircraft wing may be constructed by applying one or more layers of a composite material onto a plurality of wing mandrels 500. When placed together, the wing mandrels form the shape of the wing. After the layers of the composite material are applied to each individual mandrel, the mandrels are in contact with each other. Thereafter, the mandrels are compressed using wing surface tooling 506-512 applied to the plurality of wing mandrels. The composite material is thereafter cured. After curing, the wing surface tooling and mandrels are removed, resulting in a wing having multi-box wing spars and skin.
摘要翻译：要解决的问题：提供一种实现具有多箱翼梁的翼部构造的装置和方法。解决方案：飞机机翼可以通过将一层或多层复合材料施加到多个翼心轴500上而构成。放置在一起时，机翼心轴形成机翼的形状。在将复合材料层施加到每个单独的心轴之后，心轴彼此接触。此后，使用应用于多个机翼心轴的机翼表面工具506-512来压缩心轴。此后复合材料固化。固化后，机翼表面加工和心轴被去除，导致翼具有多箱翼翼和皮肤。

3. 发明专利

JP2013233923A Method and system for use in assembling fuselage 有权
标题翻译：用于组装熔融的方法和系统
公开(公告)号：JP2013233923A
公开(公告)日：2013-11-21
申请号：JP2013097016
申请日：2013-05-02
申请人： Boeing Co:The , ザ・ボーイング・カンパニーThe Boeing Company
发明人： MOSELAGE III JOHN H
IPC分类号： B64C1/12
CPC分类号： B64C1/069 , B64C2001/0072 , Y02T50/433 , Y10T29/49908
摘要： PROBLEM TO BE SOLVED: To provide a system and a method essentially eliminating the need for fasteners when coupling fuselage barrel sections together.SOLUTION: A fuselage assembly 200 includes a first barrel section 200 including a body that extends from a first end 211 to a second end 213 and a second barrel section 220 coupled to the first barrel section. The second barrel section includes a body that extends from a first end 221 to a second end 223, and the second end of the first barrel section is coupled to the second end of the second barrel section. At least one member maintains a coupling between the first barrel section and the second barrel section. The at least one member induces a compressive force to at least one of the first barrel section and the second barrel section.
摘要翻译：要解决的问题：提供一种系统和方法，其基本上消除了将机身筒部分连接在一起时对紧固件的需要。解决方案：机身组件200包括第一筒部分200，其包括从第一端211延伸到第二端部211的主体端部213和耦合到第一筒部分的第二筒部分220。第二筒部包括从第一端221延伸到第二端223的主体，并且第一筒部的第二端联接到第二筒部的第二端。至少一个构件在第一筒部和第二筒部之间保持联接。至少一个构件对第一筒部分和第二筒部分中的至少一个引起压缩力。

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