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公开(公告)号：US11572148B2
公开(公告)日：2023-02-07
申请号：US15997331
申请日：2018-06-04
申请人： The Boeing Company
发明人： Jiangtian Cheng
摘要： Aircraft stringers having carbon fiber reinforced plastic (CFRP) material reinforced flanges are disclosed. An example stringer to be coupled to a skin of an aircraft comprises a flange. The flange includes a first portion of a first stiffening segment. The flange further includes a first portion of a second stiffening segment coupled to the first portion of the first stiffening segment. The flange further includes a CFRP reinforcement segment coupled to the first portion of the first stiffening segment and to the first portion of the second stiffening segment. The CFRP reinforcement segment strengthens the first portion of the first stiffening segment and the first portion of the second stiffening segment.
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公开(公告)号：US11085111B2
公开(公告)日：2021-08-10
申请号：US16157886
申请日：2018-10-11
申请人： The Boeing Company
发明人： Paul S. Nordman , Jiangtian Cheng
摘要： A method for fabricating a structural part is disclosed. The method can include forming a plurality of layers on a base of a system having one or more application heads. Forming the plurality of layers can include forming alternating layers of a first material and a second material. Forming the alternating layers can include forming a first layer from the first material, and forming a second layer adjacent the first layer from the second material. The plurality of layers can form the structural part, and one or more dimensions of the structural part can be greater than or equal to about 0.05 cm.
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公开(公告)号：US20210162697A1
公开(公告)日：2021-06-03
申请号：US17148974
申请日：2021-01-14
申请人： The Boeing Company
发明人： Jiangtian Cheng
IPC分类号： B32B3/10 , B32B3/26 , B32B1/00 , B32B27/08 , B32B27/38 , B32B5/28 , B32B5/12 , B32B5/26 , B64C3/18 , B64C1/06 , B29C70/20 , B29C70/54 , B29C70/30
摘要： In an example, a composite structure having a variable gage is described. The composite structure includes a first end having a first gage, a second end having a second gage, which is less than the first gage, a plurality of continuous plies, and a plurality of drop-off plies. Each continuous ply extends from the first end to the second end. Each drop-off ply includes a tip having a tapered shape. Each drop-off ply extends from the first end to a respective position of the tip of the drop-off ply between the first end and the second end. The tips of the plurality of drop-off plies are arranged in a monotonically-inward pattern.
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公开(公告)号：US10919260B2
公开(公告)日：2021-02-16
申请号：US16408409
申请日：2019-05-09
申请人： The Boeing Company
发明人： Jiangtian Cheng
IPC分类号： B32B3/10 , B32B3/26 , B32B5/12 , B32B5/26 , B32B5/28 , B29C70/20 , B29C70/30 , B32B5/14 , B29C70/10 , B64F5/10 , B32B1/00 , B32B27/04 , B32B5/02 , B32B3/02 , B64C3/18 , B64C1/06 , B29L31/30 , B29L9/00 , B29C70/54
摘要： In an example, a composite structure having a variable gage is described. The composite structure includes a first end having a first gage, a second end having a second gage, which is less than the first gage, a plurality of continuous plies, and a plurality of drop-off plies. Each continuous ply extends from the first end to the second end. Each drop-off ply includes a tip having a blunt-end shape. Each drop-off ply extends from the first end to a respective position of the tip of the drop-off ply between the first end and the second end. The plurality of drop-off plies are separated from each other by at least one of the plurality of continuous plies.
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公开(公告)号：US09856008B2
公开(公告)日：2018-01-02
申请号：US14281456
申请日：2014-05-19
申请人： The Boeing Company
CPC分类号： B64C1/06 , B29C37/0082 , B29C70/342 , B29C70/865 , B29D99/0003 , B29D99/0014 , B29K2705/00 , B29L2031/3076 , Y02T50/43
摘要： A composite structure is provided. The composite structure includes a first stiffener, a second stiffener, and an intermediate structure positioned between the first and second stiffeners such that the first stiffener is coupled to a first side of the intermediate structure, and such that the second stiffener is coupled to a second opposing side of the intermediate structure. A first radius gap is defined at least partially between the first stiffener and the intermediate structure, and a second radius gap is defined at least partially between the second stiffener and the intermediate structure.
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公开(公告)号：US11325339B2
公开(公告)日：2022-05-10
申请号：US17148974
申请日：2021-01-14
申请人： The Boeing Company
发明人： Jiangtian Cheng
IPC分类号： B32B3/02 , B32B5/26 , B29C70/20 , B29C70/30 , B32B3/10 , B32B3/26 , B32B1/00 , B32B27/08 , B32B27/38 , B32B5/28 , B32B5/12 , B64C3/18 , B64C1/06 , B29C70/54 , B32B5/02 , B32B27/04 , B29L9/00 , B29L31/30
摘要： In an example, a composite structure having a variable gage is described. The composite structure includes a first end having a first gage, a second end having a second gage, which is less than the first gage, a plurality of continuous plies, and a plurality of drop-off plies. Each continuous ply extends from the first end to the second end. Each drop-off ply includes a tip having a tapered shape. Each drop-off ply extends from the first end to a respective position of the tip of the drop-off ply between the first end and the second end. The tips of the plurality of drop-off plies are arranged in a monotonically-inward pattern.
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公开(公告)号：US11052617B2
公开(公告)日：2021-07-06
申请号：US16178354
申请日：2018-11-01
申请人： The Boeing Company
发明人： Scott M. Spencer , Jessica R. Hughes , Jae Dong Hwang , Joseph L. Sweetin , Kanna M. Pham , Jaime C. Garcia , Gregory P. Freed , Frederick T. Calkins , Cynthia G. Feng , Jiangtian Cheng
IPC分类号： B29C70/38 , B29C70/54 , B29K307/04
摘要： A method of fabricating a plank stringer for use in an aircraft includes grouping a plurality of stacked plies of reinforcing material into a plurality of charges, where each charge in the plurality of charges includes a substack of plies. The method also includes grouping the plurality of charges into two or more groups such that, for each charge in a given group, a respective substack of plies includes a sequence of orientation angles with respect to a longitudinal axis of the plank stringer corresponding to the given group. The method also includes laying up each group of charges as a continuous blanket of plies, where each continuous blanket of plies includes the respective substack of plies for each charge in the respective group. The method also includes cutting each continuous blanket of plies into the respective group of charges and stacking the plurality of charges to form the plank stringer.
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公开(公告)号：US20200353708A1
公开(公告)日：2020-11-12
申请号：US16408401
申请日：2019-05-09
申请人： The Boeing Company
发明人： Jiangtian Cheng
摘要： A composite stringer assembly includes a composite stringer and a radius filler. The composite stringer includes a skin flange, a web, a corner portion extending from the skin flange to the web, an inner surface, and an outer surface. At the corner portion, the outer surface is defined by a first radius of curvature, which is substantially constant between the skin flange and the web. The support structure includes at least one of a skin of a vehicle or a base charge. The radius filler includes a first surface coupled to the inner surface at the corner portion, a second surface configured to couple to the support structure, and a third surface extending between the first surface and the second surface. The first surface of the radius filler is defined by a second radius of curvature, which is substantially constant between the second surface and the third surface.
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公开(公告)号：US20200346733A1
公开(公告)日：2020-11-05
申请号：US16402034
申请日：2019-05-02
申请人： The Boeing Company
发明人： Jiangtian Cheng , Paul S. Nordman
摘要： One piece, multifunctional window assemblies for use in vehicles, equipment, or structures and methods for making them is provided. The disclosed window assembly can include a protection panel and a structural panel each formed of a plurality of nanolaminated layers. The nanolaminated window assembly is self-supporting and does not need a frame. For particular applications, such as in an aircraft, the one piece, multifunctional, nanolaminated window can be directly attached to the fuselage to provide load bearing capability, a larger window area, impact protection, ice buildup prevention, and/or electromagnetic effect protection.
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公开(公告)号：US10669005B2
公开(公告)日：2020-06-02
申请号：US15907224
申请日：2018-02-27
申请人： The Boeing Company
发明人： Jiangtian Cheng , Ian E. Schroeder , Gary D. Swanson , Kanna M. Pham , Samuel E. Cregger , Scott M. Spencer
IPC分类号： B32B3/06 , B64C1/06 , B32B3/26 , B64C3/18 , B29C70/30 , B29C70/20 , B32B5/12 , B29D99/00 , B29L31/30 , B64C1/00
摘要： A solid laminate stringer includes a base segment that forms a first generally trapezoidal cross section. The solid laminate stringer also includes a transition segment abutting the base segment, with concave sides that are continuous with the sides of the base segment. The solid laminate stringer also includes a top segment abutting the transition segment, where the top segment forms a second generally trapezoidal cross section with sides that are continuous with the concave sides of the transition segment. The solid laminate stringer also includes a first overwrap layer covering the top segment, the transition segment, and at least a portion of the base segment. The solid laminate stringer also includes a second overwrap layer overlapping at least a portion of the first overwrap layer covering the base segment.
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