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1. 发明申请

US20190016434A1 LOW STRESS STIFFENER RUNOUT IN PI BONDED STRUCTURE 审中-公开
公开(公告)号：US20190016434A1
公开(公告)日：2019-01-17
申请号：US16044118
申请日：2018-07-24
申请人： The Boeing Company
发明人： Jan T. Jansen , Ryan Stott , William Vallellanes , Jack Van Es
IPC分类号： B64C1/06 , B64G1/22 , B64C3/18 , B63B3/00
CPC分类号： B64C1/064 , B63B3/00 , B64C3/182 , B64G1/22
摘要： A stringer for having a runout with a raised area configured to reduces stress while improving drainage across the runout when utilized in a close structural component of a vehicle such as an aileron of an aircraft. In one or more configurations, the raised area of the runout of the stringer includes multiple tapered surfaces adjacent to one another oriented and configured as ramps to collectively guide water up, over and down the raised area of the stringer.

2. 发明授权

US10005267B1 Formation of complex composite structures using laminate templates 有权
公开(公告)号：US10005267B1
公开(公告)日：2018-06-26
申请号：US14861641
申请日：2015-09-22
申请人： Textron Innovations Inc.
发明人： Richard Boone , Benjamin de Putter
IPC分类号： B64C1/06 , B32B37/14 , B64C3/18
CPC分类号： B64F5/10 , B29C70/30 , B29C70/86 , B29D24/00 , B29D99/0003 , B32B38/1866 , B32B2305/076 , B32B2305/72 , B32B2305/74 , B32B2309/105 , B32B2605/18 , B64C3/182 , B64C3/185 , B64C3/187
摘要： Embodiments of a method to fabricate complex structures include making a pre-cured laminate template. The laminate template is first cured to the required shape, then surface prepared for joining to additional composite lamina. The laminate templates are used to position composite lamina in contact with one another. The composite lamina are then co-cured together to form one monolithic composite structure lacking bond lines or bonded joints. The laminate template supports additional composite lamina for formation of complex structures and replaces template tools from conventional methods.

3. 发明申请

US20180050787A1 AIRCRAFT COMPOSITE WINGBOX INTEGRATION 审中-公开
公开(公告)号：US20180050787A1
公开(公告)日：2018-02-22
申请号：US15238250
申请日：2016-08-16
申请人： The Boeing Company
发明人： Max U. Kismarton , Clayton L. Munk
IPC分类号： B64C3/18 , B64F5/00 , B64C3/26
CPC分类号： B64C3/182 , B29C70/00 , B29D99/0014 , B29L2031/3085 , B64C1/26 , B64C3/26 , B64F5/10
摘要： Systems and methods are provided for integrating structural components of a wing box. One embodiment is a system that includes outboard planked stringers within an outboard section of a wing box and are co-cured with composite skin at the outboard section. Each outboard planked stringer of the outboard section includes planar layers of Carbon Fiber Reinforced Polymer (CFRP) that are parallel with the composite skin at the outboard section, have fiber orientations aligned to bear tension and compression applied to the wing box, and each extend a different distance along the composite skin at the outboard section. The system also includes center planked stringers within the center section and are co-cured with composite skin at the center section. Each center planked stringer of the center section includes planar layers of CFRP that are parallel with the composite skin at the center section, have fiber orientations aligned to bear tension and compression applied to the wing box, and each extend a different distance along the skin at the center section.

4. 发明授权

US09856009B2 Manufacturing method of reinforcing structure 有权
公开(公告)号：US09856009B2
公开(公告)日：2018-01-02
申请号：US14901830
申请日：2014-06-26
申请人： MITSUBISHI HEAVY INDUSTRIES, LTD.
发明人： Taku Yamamori
IPC分类号： B64C1/12 , B64D45/02 , B29C70/86 , B29C31/00 , B29D99/00 , B64C1/06 , B64C3/18 , B29C70/88 , B29L31/30 , B29C35/00 , B64C1/00 , B29K105/08 , B29K307/04
CPC分类号： B64C1/12 , B29C31/008 , B29C70/86 , B29C70/882 , B29C2035/005 , B29D99/0014 , B29K2105/08 , B29K2307/04 , B29K2995/0005 , B29L2031/3085 , B64C1/064 , B64C3/182 , B64C2001/0072 , B64D45/02 , Y02T50/43
摘要： A manufacturing method of a reinforcing structure includes: preparing a stringer having a fiber exposure surface; arranging an insulation protection material to cover at least a part of the fiber exposure surface; arranging the stringer on a skin having an uncured resin component; and curing the skin after the arranging the stringer. The insulation protection material includes a composite material having a resin component and an insulative fiber component. The curing the skin includes curing the skin and the insulation protection material at the same time. In the manufacturing method of a reinforcing structure, an edge glow discharge can be prevented without increasing a manufacturing process.

5. 发明申请

US20170240286A1 AIRCRAFT WITH A PROPULSION UNIT WITH OFFSET FAN 审中-公开
公开(公告)号：US20170240286A1
公开(公告)日：2017-08-24
申请号：US15284895
申请日：2016-10-04
申请人： SAFRAN AIRCRAFT ENGINES
发明人： Kevin Morgane Lemarchand , Tewfik Boudebiza , Gilles Alain Charier , Nathalie Nowakowski
IPC分类号： B64D27/18 , B64D35/02 , B64D27/26 , B64D27/12 , B64C3/18 , B64C3/32 , B64C11/00 , F02K1/54
CPC分类号： B64D27/18 , B64C3/182 , B64C3/32 , B64C11/001 , B64D27/12 , B64D27/26 , B64D35/02 , B64D35/04 , B64D2027/266 , F02K1/54 , F02K3/077 , Y02T50/671
摘要： An aircraft includes a wing having a first upstream longeron and a second downstream longeron extending in the direction of the span of said wing, and at least one propulsion unit supported by the wing. The propulsion unit includes a turboprop engine and a propeller. The propeller includes an external annular casing fixed to a suction surface of the wing, and at least to the first upstream longeron via at least one first and second fastener.

6. 发明授权

US09731808B2 Upper joints between outboard wing boxes and wing center sections of aircraft wing assemblies 有权
公开(公告)号：US09731808B2
公开(公告)日：2017-08-15
申请号：US15266779
申请日：2016-09-15
申请人： The Boeing Company
发明人： Jordan Daniel Charles , Jason Hamada
IPC分类号： B64C1/00 , B64C3/00 , B64C5/00 , B64C1/26 , B64C3/18
CPC分类号： B64C1/26 , B64C3/00 , B64C3/182 , B64C3/187 , B64C2001/0072 , B64C2001/0081
摘要： An upper joint of a wing assembly of an aircraft includes an outboard upper wing panel, a center upper wing panel, a rib, and an upper joint assembly operatively interconnecting the outboard upper wing panel, the center upper wing panel, and the rib. For a substantial fore/aft span of the upper joint, a first subset of a plurality of center upper stringers is operatively coupled to the upper joint assembly, and a second subset of the plurality of center upper stringers terminates without being directly coupled to the upper joint assembly.

7. 发明申请

US20160325820A1 STRUCTURAL COMPONENT 审中-公开
标题翻译：结构部件
公开(公告)号：US20160325820A1
公开(公告)日：2016-11-10
申请号：US15147460
申请日：2016-05-05
申请人： AIRBUS OPERATIONS LIMITED
发明人： Steven EVANS
IPC分类号： B64C3/26 , B64C3/18
CPC分类号： B64C3/26 , B29C70/00 , B29C70/30 , B29C70/545 , B29L2031/3076 , B64C1/064 , B64C3/182 , B64C3/185 , B64C3/187 , B64C2001/0072 , Y02T50/43
摘要： The present invention relates to structural component for an aircraft. The structural component comprises a body with a first surface and a lug that extends out of the first surface. The body and lug comprise a composite material and are integrally formed.
摘要翻译：本发明涉及飞机的结构部件。结构部件包括具有第一表面的主体和从第一表面延伸出的凸耳。主体和凸耳包括复合材料并且整体形成。

8. 发明申请

US20160318597A1 Apparatuses and Methods for Manufacturing a Structure 有权
标题翻译：制造结构的装置和方法
公开(公告)号：US20160318597A1
公开(公告)日：2016-11-03
申请号：US14698566
申请日：2015-04-28
申请人： The Boeing Company
发明人： Steven R. Kent
IPC分类号： B64C3/18 , B64C3/26
CPC分类号： B64C3/185 , B64C3/18 , B64C3/182 , B64C3/26
摘要： A structure (100) comprises a first panel (102); first stringers (106), coupled to the first panel (102) and comprising stringer pairs A; a second panel (104) opposite the first panel (102); and second stringers (108), coupled to the second panel (104) and opposite the first stringers (106). The second stringers (108) comprise stringer pairs B. The structure (100) also comprises braces (200). Each of the braces (200) is geometrically interlocked with one of the stringer pairs A of the first stringers (106) and one of the stringer pairs B of the second stringers (108) in all directions along a plane (112) perpendicular to the first stringers (106) and the second stringers (108).
摘要翻译：一种结构（100）包括第一面板（102）; 第一桁条（106），连接到第一面板（102）并且包括桁条对A; 与第一面板（102）相对的第二面板（104）; 和连接到第二面板（104）并与第一桁条（106）相对的第二桁条（108）。第二桁条（108）包括桁条对B.结构（100）还包括支柱（200）。每个支架（200）沿着垂直于第一桁条（106）的平面（112）的所有方向在几何上与第一桁条（106）的纵梁对A和第二桁条（108）的纵梁对B中的一个几何地互锁，第一桁条（106）和第二桁条（108）。

9. 发明授权

US09481115B2 Moulding tool and method of manufacturing a part 有权
标题翻译：成型工具和制造零件的方法
公开(公告)号：US09481115B2
公开(公告)日：2016-11-01
申请号：US13773999
申请日：2013-02-22
申请人： Airbus Operations Limited
发明人： Marc Edwin Funnell
IPC分类号： B29C70/32 , B29C33/48 , B29C43/02 , B29D99/00 , B29C33/30 , B29C70/44 , B29C70/34 , B29L31/30 , B29K105/08 , B64C3/18 , B64C3/24
CPC分类号： B29C43/021 , B29C33/306 , B29C33/48 , B29C33/485 , B29C70/32 , B29C70/342 , B29C70/44 , B29C70/446 , B29D99/0014 , B29D99/0028 , B29K2105/0809 , B29K2105/0872 , B29L2031/3085 , B64C3/182 , B64C3/187 , B64C3/24 , Y02T50/43
摘要： A tool set comprising: a molding tool comprising a molding surface and a mandrel recess in the molding surface; a first mandrel configured to fit into the mandrel recess and form a first component; and a second mandrel configured to fit into the mandrel recess and form a second component which has a different shape or size to the first component. A method of manufacturing a part, the method comprising: arranging a set of components on one or more inner mould line tools; forming a layer around the inner mould line tool(s); fitting a pair of outer mould line tools on opposite sides of the inner mould line tool(s); molding the part by compressing the layer and the components between the inner and outer mould line tools; and removing the inner mould line tool(s) from the part.
摘要翻译：一种工具组，包括：模制工具，其包括模制表面和模制表面中的心轴凹槽; 第一心轴构造成装配到心轴凹槽中并形成第一组件; 以及第二心轴，其构造成装配到所述心轴凹部中并形成与所述第一部件具有不同形状或尺寸的第二部件。一种制造零件的方法，所述方法包括：在一个或多个内模具工具上布置一组零件; 围绕内模线工具形成一层; 在一个或多个内模具工具的相对侧上装配一对外模线工具; 通过压缩内部和外部模具线工具之间的层和部件来模制部件; 以及从所述部件移除所述内模线工具。

10. 发明授权

US09475570B2 Upper joints between outboard wing boxes and wing center sections of aircraft wing assemblies 有权
标题翻译：飞机机翼组件外侧机翼和机翼中心部分之间的上部接头
公开(公告)号：US09475570B2
公开(公告)日：2016-10-25
申请号：US13975158
申请日：2013-08-23
申请人： The Boeing Company
发明人： Jordan Daniel Charles , Jason Hamada
IPC分类号： B64C1/00 , B64C3/00 , B64C5/00 , B64C3/18 , B64C1/26
CPC分类号： B64C1/26 , B64C3/00 , B64C3/182 , B64C3/187 , B64C2001/0072 , B64C2001/0081
摘要： An upper joint of a wing assembly of an aircraft includes an outboard upper wing panel, a center upper wing panel, a rib, and an upper joint assembly operatively interconnecting the outboard upper wing panel, the center upper wing panel, and the rib. In some embodiments, outboard upper stringers may be configured differently than center upper stringers. In some embodiments, a subset of the center upper stringers may not directly oppose the outboard upper stringers. In other embodiments, for at least a substantial fore/aft span of the upper joint, each of the center upper stringers may directly oppose an outboard upper stringer.
摘要翻译：飞行器的机翼组件的上接头包括外侧上翼板，中心上翼板，肋和可操作地连接外侧上翼板，中心上翼板和肋的上接头组件。在一些实施例中，外侧上部桁条可以被配置为不同于中心上部桁条。在一些实施例中，中心上部纵梁的子集可以不直接与外侧上部纵梁相对。在其他实施例中，对于上关节的至少大体上/后跨距，每个中心上纵梁可以直接与外侧上纵梁相对。

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