-
公开(公告)号：US20220169364A1
公开(公告)日：2022-06-02
申请号：US17522759
申请日：2021-11-09
申请人： The Boeing Company
发明人： Gregory A. Cass , Ian E. Schroeder , Khanh M. Pham
摘要： Provided are stiffened stringer panels with integrated shim structures. An example composite panel comprises a skin member having an inner surface, and a stringer positioned on the inner surface. The stringer comprises a first flange portion and a second flange portion with the first flange portion and the second flange portion contacting the inner surface. The composite panel further comprises an integrated shim positioned on the first flange portion. The integrated shim may comprise a sacrificial material configured to be trimmed to the desired geometry. The sacrificial material may comprise a glass fiber reinforced plastic fabric pre-impregnated with resin. The integrated shim may be configured to interface with internal support structures of a wing assembly. The integrated shim may be configured to he machined to fit dimensions and measurements corresponding to the internal support structures of the wing assembly.
-
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.
-
公开(公告)号：US10183735B2
公开(公告)日：2019-01-22
申请号：US15012325
申请日：2016-02-01
申请人： The Boeing Company
发明人： David E. Gideon , Ian E. Schroeder , Kristin L. Hall , Kin M. Ng , Megan C. Kinney , Greg M. Reyneke , Randall D. Wilkerson , Richard R. Rosman , Aaron W. Bartel
IPC分类号： B64C1/14
摘要： A window frame assembly for an aircraft, includes a window frame of composite material, adapted for attachment in a window opening of an aircraft, having an outer flange with an exterior surface and an interior surface, a metal erosion shield attached to the exterior surface of the outer flange, and a polymer adapter ring, attached to the interior surface of the outer flange. The window frame has a substantially constant thickness, and the erosion shield has a substantially constant cross-sectional shape. The adapter ring has a sloped engagement surface configured for supporting a window pane assembly.
-
公开(公告)号：US20220001973A1
公开(公告)日：2022-01-06
申请号：US17331379
申请日：2021-05-26
申请人： The Boeing Company
摘要： A fastening system to couple a first aircraft structure and a second aircraft structure is disclosed. The fastening system includes a fastener, a nutplate having a body defining an opening to receive the fastener, a flange extending from the body to engage an outer surface of the first structure, and a first sleeve protruding from the flange in a direction away from the body, the first sleeve to couple to a first bore formed in the first structure and prevents rotation of the nutplate relative to the first structure.
-
公开(公告)号：US20210107621A1
公开(公告)日：2021-04-15
申请号：US16596878
申请日：2019-10-09
申请人： The Boeing Company
发明人： Brett D. Whitmer , Kristopher Talcott , Tyler W. Downey , Dan D. Day , Jean R. Paillant , Thanh Quach , Ian E. Schroeder , Jason H. Inouye , William H. Graham
摘要： Examples include an apparatus configured for attaching a rib of an aircraft wing to a panel of the aircraft wing, the apparatus including: an insert that is configured to be attached, via an interference fit, to a hole in the rib; a shear tie including a socket at a first end of the shear tie, where the shear tie is configured to be attached to the panel at a second end of the shear tie; a ball stud including a shaft and a ball that is opposite the shaft, where the shaft is configured to be attached to the insert and the ball is configured to be positioned within the socket; and a fastener that is configured to secure the ball within the socket, thereby attaching the ball stud to the shear tie.
-
公开(公告)号：US20180072399A1
公开(公告)日：2018-03-15
申请号：US15264209
申请日：2016-09-13
申请人： The Boeing Company
发明人： Steven P. Walker , Forouzan Behzadpour , Gary D. Oakes , Ian E. Schroeder , Patrick B. Stickler , Jason H. Inouye
摘要： Aircraft wings and aircraft including such aircraft wings are disclosed. An example apparatus includes an aircraft wing having a first panel; a second panel; ribs coupled between the first and second panels; and stiffeners coupled between the ribs in a spanwise direction and to the first panel, the coupling between the stiffeners and the first panel to deter axial loads from being received by the stiffeners, the stiffeners to increase a compressional stability of the first panel, wherein the coupling between the stiffeners and the first panel are indirect couplings formed via clips, the couplings formed via the clips deter the axial loads from being received by the stiffeners while increasing the compressional stability of the first panel.
-
公开(公告)号：US11878792B2
公开(公告)日：2024-01-23
申请号：US17522759
申请日：2021-11-09
申请人： The Boeing Company
发明人： Gregory A. Cass , Ian E. Schroeder , Khanh M. Pham
CPC分类号： B64C3/182 , B29C66/0326 , B32B3/085 , B32B5/10 , B32B5/26 , B32B38/0004 , B32B38/10 , B32B2038/0076 , B32B2260/023 , B32B2605/18
摘要： Provided are stiffened stringer panels with integrated shim structures. An example composite panel comprises a skin member having an inner surface, and a stringer positioned on the inner surface. The stringer comprises a first flange portion and a second flange portion with the first flange portion and the second flange portion contacting the inner surface. The composite panel further comprises an integrated shim positioned on the first flange portion. The integrated shim may comprise a sacrificial material configured to be trimmed to the desired geometry. The sacrificial material may comprise a glass fiber reinforced plastic fabric pre-impregnated with resin. The integrated shim may be configured to interface with internal support structures of a wing assembly. The integrated shim may be configured to be machined to fit dimensions and measurements corresponding to the internal support structures of the wing assembly.
-
公开(公告)号：US20200247523A1
公开(公告)日：2020-08-06
申请号：US16856420
申请日：2020-04-23
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
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 may also include a first overwrap layer covering the top segment, the transition segment, and at least a portion of the base segment. The solid laminate stringer may also include a second overwrap layer overlapping at least a portion of the first overwrap layer covering the base segment.
-
公开(公告)号：US20190263496A1
公开(公告)日：2019-08-29
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
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.
-
公开(公告)号：US11260954B2
公开(公告)日：2022-03-01
申请号：US16596878
申请日：2019-10-09
申请人： The Boeing Company
发明人： Brett D. Whitmer , Kristopher Talcott , Tyler W. Downey , Dan D. Day , Jean R. Paillant , Thanh Quach , Ian E. Schroeder , Jason H. Inouye , William H. Graham
摘要： Examples include an apparatus configured for attaching a rib of an aircraft wing to a panel of the aircraft wing, the apparatus including: an insert that is configured to be attached, via an interference fit, to a hole in the rib; a shear tie including a socket at a first end of the shear tie, where the shear tie is configured to be attached to the panel at a second end of the shear tie; a ball stud including a shaft and a ball that is opposite the shaft, where the shaft is configured to be attached to the insert and the ball is configured to be positioned within the socket; and a fastener that is configured to secure the ball within the socket, thereby attaching the ball stud to the shear tie.
-
-
-
-
-
-
-
-
-
搜索结果
12 条记录 (耗时 0.034 秒)
