-
公开(公告)号：US11851176B1
公开(公告)日：2023-12-26
申请号：US17190071
申请日：2021-03-02
申请人： Wing Aviation LLC
发明人： Adam Woodworth , Adem Rudin , Stephen Benson
CPC分类号： B64C3/24 , B29C45/0053 , B64C3/18 , B29C2045/0079 , B29C2045/0093 , B64C29/02 , B64C39/024
摘要： An example method of manufacturing a wing includes providing a wing frame. The wing frame includes a primary spar, a drag spar, a plurality of transverse frame elements having at least one spar joiner, and a plurality of mounting elements. The primary spar is coupled to the drag spar via the at least one spar joiner. The method further includes placing the wing frame into a mold, wherein the mold defines a shape of the wing. The method also includes injecting the mold with an air-filled matrix material, such that the air-filled matrix material substantially encases the wing frame and fills the defined shape of the wing, and such that the plurality of transverse frame elements provide torsional rigidity to the wing.
-
公开(公告)号：US20180273174A1
公开(公告)日：2018-09-27
申请号：US15781930
申请日：2016-12-06
发明人： Nigel Frank Gifford
CPC分类号： B64C39/024 , B64C1/00 , B64C1/061 , B64C3/18 , B64C2201/00 , B64C2201/128 , B64D9/00 , B64D25/00 , B64F5/00
摘要： An unmanned disposable air vehicle (1) comprising a structural part (3) that has an outer structure (17) and an inner structure (15) located inside the outer structure (17), the inner structure (15) being arranged to support the outer structure (17), wherein at least one of the inner structure (15) and outer structure (17) comprises an article of aid (19) such that the air vehicle (1) may be flown to a relief zone and the structural part (3) dismantled from the air vehicle (1) to allow the article of aid (19) to be used.
-
公开(公告)号：US09926067B1
公开(公告)日：2018-03-27
申请号：US13913764
申请日：2013-06-10
申请人： The Boeing Company
CPC分类号： B64C1/064 , B32B15/08 , B32B2605/18 , B64C1/069 , B64C3/18 , B64C3/182 , B64C2001/0072 , Y02T50/12 , Y10T428/24777
摘要： A method and apparatus are provided. The apparatus comprises a composite stringer having a flange configured to contact a composite skin. The flange comprises a first region comprising tapered plies, a second region comprising tapered plies, and a first end. The first end is configured to extend to an edge of the composite skin.
-
公开(公告)号：US09849967B2
公开(公告)日：2017-12-26
申请号：US14676271
申请日：2015-04-01
申请人： The Boeing Company
摘要： A rib is disclosed for use in a torque box of a wing structure provided on an aircraft. The wing structure has a skin panel and a stringer coupled to the skin panel. The rib includes a web defining at least one stringer hole sized to receive the stringer, a shear tie coupled to the web and configured to engage the skin panel, and a clip positioned adjacent the at least one stringer hole. The clip has a base coupled to and aligned with the web, a head extending at an angle relative to the base and configured to engage the stringer, and a transition portion extending between the base and the head.
-
公开(公告)号：US20170276648A1
公开(公告)日：2017-09-28
申请号：US15451792
申请日：2017-03-07
发明人： Kohei TAKAHASHI
IPC分类号： G01N29/24 , B32B5/10 , B32B27/00 , B64C3/18 , B29C59/02 , B29C65/48 , G01N29/04 , B32B7/12 , B32B37/12
CPC分类号： G01N29/2418 , B29C33/42 , B29C43/021 , B29C43/58 , B29C59/022 , B29C59/026 , B29C65/4855 , B29C70/34 , B29C70/42 , B29C2033/0094 , B29C2043/5808 , B29K2105/06 , B29K2995/0001 , B29L2031/3076 , B29L2031/3082 , B32B5/10 , B32B7/12 , B32B27/00 , B32B37/12 , B32B2307/10 , B32B2605/18 , B64C3/18 , G01N29/043 , Y02T50/43
摘要： According to one implementation, a composite material molding jig includes a rigid portion and a convex portion for forming a groove for inserting an optical fiber sensor. The rigid portion has a surface for laminating prepreg sheets. The convex portion is formed in a surface side of the rigid portion. Further, according to one implementation, a composite material molding method is a method for molding a composite material, on which the groove for inserting the optical fiber sensor has been formed, by heating and curing a laminated body of the prepreg sheets laminated on the above-mentioned composite material molding jig.
-
公开(公告)号：US09771140B2
公开(公告)日：2017-09-26
申请号：US14140511
申请日：2013-12-25
CPC分类号： B64C1/061 , B32B2605/18 , B64C1/064 , B64C1/12 , B64C1/1461 , B64C3/18 , B64C3/182 , B64C2001/0072 , Y02T50/43 , Y10T428/24008
摘要： The invention provides an integrated aircraft structure, such as a fuselage, with reinforcing elements in areas of the structure that need them because they have openings or are subjected to high loads. The structure comprises a skin, a plurality of stringers and a plurality of frames with mouseholes for the passage of stringers at their crossing zones. The reinforcing elements are configured with a suitable shape to be superimposed to the stringers in said areas. A manufacturing processes of said integrated aircraft structure is also provided.
-
公开(公告)号：US20170253346A1
公开(公告)日：2017-09-07
申请号：US15061942
申请日：2016-03-04
申请人： The Boeing Company
CPC分类号： B64D45/02 , B29C70/885 , B64C1/00 , B64C3/18 , B64C2001/0072 , B64F5/10 , Y02T50/43
摘要： There is provided a conductive radius filler system and method. The system has a composite assembly with one or more composite structures having one or more radius filler regions. The system further has one or more conductive radius fillers filling the one or more radius filler regions. Each of the conductive radius fillers has a conductive element of electrically conductive material. The system further has one or more over-arching systems connected to the one or more conductive radius fillers, via one or more conductive radius filler connections, forming one or more current handling systems of the system. The one or more current handling systems include one or more of an edge glow handling system configured to handle edge glow, a static dissipation handling system configured to handle static dissipation, and a current return handling system configured to handle current return.
-
公开(公告)号：US09751613B2
公开(公告)日：2017-09-05
申请号：US15343494
申请日：2016-11-04
申请人： The Boeing Company
发明人： Steven R. Kent
摘要： A brace (200) for geometrically interlocking stringer pairs A of first stringers (106), coupled to a first panel (102), and stringer pairs B of second stringers (108), coupled to a second panel (104), of a structure (100). The brace (200) comprises a chassis (202) comprising first interlocks (204) and second interlocks (206) opposite the first interlocks (204). The first interlocks (204) geometrically engage with one of the stringer pairs A of the first stringers (106) and the second interlocks (206) geometrically engage with one of the stringer pairs B of the second stringers (108) to constrain the brace (200) in all directions along a plane (112) perpendicular to the first stringers (106) and the second stringers (108).
-
公开(公告)号：US20160325822A1
公开(公告)日：2016-11-10
申请号：US15147202
申请日：2016-05-05
摘要： The present disclosure generally refers to an aircraft horizontal tail plane (HTP) having a multi-rib torsion box formed by first and second lateral torsion boxes symmetrically arranged with respect to a plane of symmetry of the horizontal tail plane. A group of ribs are substantially parallel to the plane of symmetry of the horizontal tail plane, and the stringers are arranged as to define an angle within the range 80°-100° with respect to the plane of symmetry of the horizontal tail plane. Due to this relative arrangement of the ribs and stringers, the stringers are not continuous through ribs, thus the ribs can be manufactured without mouse holes. The HTP of the invention can be manufactured easier and faster than traditional HTP designs.
摘要翻译： 本发明总体上涉及一种具有由相对于水平尾翼平面的对称平面对称布置的第一和第二横向扭转箱形成的多肋扭转箱的飞机水平尾翼平面（HTP）。 一组肋基本上平行于水平尾翼平面的对称平面，并且桁条被布置成相对于水平尾翼平面的对称平面限定在80°-100°的范围内的角度。 由于肋和桁条的这种相对布置，桁条不通过肋连续，因此肋可以被制造成没有鼠标孔。 本发明的HTP可以比传统的HTP设计更容易和更快地制造。
-
10.发明申请公开(公告)号：US20160304187A1
公开(公告)日：2016-10-20
申请号：US14687022
申请日：2015-04-15
发明人： Brenden Autry , Bryan Williams , Travis Cope , Susan Daggett , John McGuire , Michael McKee , Charles Aitken
CPC分类号： B64C3/187 , B29C70/00 , B29C70/342 , B29D99/0014 , B32B37/1018 , B64C3/18 , B64C3/20 , Y02T50/43
摘要： Stiffening structures, wing structures and methods for manufacturing stiffening structures are provided. In accordance with an exemplary embodiment, a stiffening structure includes a first longitudinal member, a second longitudinal member, and a first rib that extends from the first longitudinal member to the second longitudinal member and is integral with the first longitudinal member and the second longitudinal member. The first longitudinal member has a first wall, a second wall and a joining wall that joins the first wall and second wall. The first wall, the second wall and the joining wall form a space having a trapezoidal shape.
摘要翻译： 提供了加强结构，翼结构和制造加强结构的方法。 根据示例性实施例，加强结构包括第一纵向构件，第二纵向构件和从第一纵向构件延伸到第二纵向构件的第一肋，并且与第一纵向构件和第二纵向构件 。 第一纵向构件具有连接第一壁和第二壁的第一壁，第二壁和接合壁。 第一壁，第二壁和连接壁形成具有梯形形状的空间。
-
-
-
-
-
-
-
-
-
搜索结果
293 条记录 (耗时 0.025 秒)
