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公开(公告)号:EP3772406A1
公开(公告)日:2021-02-10
申请号:EP19382694.8
申请日:2019-08-06
申请人: The Boeing Company
发明人: SAMALOT, Francis J , MARTÍN ALONSO, Pedro Pablo , RUBIN, Alexander , JANSEN, Tom , LABORDUS, Maarten
摘要: Systems and methods are provided for induction welding. One embodiment is a method for induction welding a composite part. The method includes preheating a composite part comprising a matrix of thermoplastic reinforced by fibers, from an ambient temperature to a preheat temperature that is below a melting temperature of the thermoplastic, performing a welding pass of an induction coil over the composite part that initiates while the composite part remains above ambient temperature, and that is performed by generating a welding magnetic field that heats the composite part from the preheat temperature to a welding temperature that equals or exceeds the melting temperature.
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公开(公告)号:EP4215347A1
公开(公告)日:2023-07-26
申请号:EP22382043.2
申请日:2022-01-21
申请人: The Boeing Company
摘要: At least one braided composite layer configured to form a first ply (12, 12') may be provided. A plurality of slit tapes (16) may be arranged and aligned such that each slit tape is adjacent to one another and non-overlapping, to form a second ply (14). A hybrid composite laminate (10) may be formed by stacking a plurality of plies that includes at least one first ply and at least one second ply. Each slit tape may be a steered unidirectional composite slit tape that is aligned along an axis, contour line, or curve of the hybrid composite laminate, a mold/tooling used to shape the laminate, or the resulting composite part. Hybrid composite laminates may be formed by stacking at least one first ply formed of a braided composite layer and at least one second ply formed from a plurality of slit tapes. Composite parts may be formed by consolidating such hybrid composite laminates.
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公开(公告)号:EP3772402A1
公开(公告)日:2021-02-10
申请号:EP19382693.0
申请日:2019-08-06
申请人: The Boeing Company
发明人: MARTÍN ALONSO, Pedro Pablo , SAMALOT, Francis J , SACCHETTI, Francisco Raul , SACHS, Ulrich , RUBIN, Alexander
摘要: Systems and methods are provided for controlling welding. One embodiment is a method for controlling welding. The method includes initiating induction welding by operating an induction coil along a weld interface of a first composite part comprising a matrix of thermoplastic reinforced by fibers, in order to join the first composite part to a second composite part, determining a measured magnetic field strength at a location distinct from the induction coil, and determining a welding temperature at the weld interface of the first composite part based on the measured magnetic field strength.
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公开(公告)号:EP3772403A1
公开(公告)日:2021-02-10
申请号:EP19382695.5
申请日:2019-08-06
申请人: The Boeing Company
发明人: MARTÍN ALONSO, Pedro Pablo , SAMALOT, Francis J , BUSER, Yannick , RUBIN, Alexander , SACHS, Ulrich
摘要: Systems and methods are provided for controlling welding. One embodiment is a method for controlling welding of a composite part. The method includes locating a linear fiber optic sensor along a composite part comprising a matrix of thermoplastic reinforced by fibers, measuring temperatures along the weld line via the linear fiber optic sensor, performing induction welding at the composite part along the weld line, determining a continuum of weld temperatures along the weld line, and controlling the induction welding based on the continuum of weld temperatures.
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公开(公告)号:EP3702982A1
公开(公告)日:2020-09-02
申请号:EP19211998.0
申请日:2019-11-28
申请人: The Boeing Company
发明人: CROTHERS, Phillip John , RUBIN, Alexander , REYNOLDS, Carla Elizabeth , TUCKER, Samuel J. , BOGUCKI, Gregg Robert , KALIN, Joshua David
摘要: A system to aid in design for manufacturing an object includes a processor and a memory configured to store instructions. The processor is configured to receive first data representing a design of the object to be manufactured and second data representing a machine-learning model. The processor is configured to execute the instructions to generate third data using the first data and the second data. The third data indicates at least one of a modification to the design of the object or process conditions for production of the object. The processor is configured to send the design of the object, the process conditions, or both, to a manufacturing tool to enable production of the object. The machine-learning model is representative of production data and based at least partially on one or more of: object features, process parameters, environmental factors, and quality data.
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公开(公告)号:EP3335870A1
公开(公告)日:2018-06-20
申请号:EP17206292.9
申请日:2017-12-08
申请人: The Boeing Company
CPC分类号: B32B15/14 , B29C43/56 , B29C65/02 , B29C66/712 , B29C66/7212 , B29C66/7392 , B29C66/7422 , B29C66/7444 , B29C70/885 , B29C2043/561 , B29K2071/00 , B29K2105/0872 , B29K2105/12 , B29K2105/253 , B29K2307/04 , B29K2309/08 , B29K2705/02 , B29K2995/0078 , B29L2009/003 , B32B5/024 , B32B5/14 , B32B5/26 , B32B7/10 , B32B15/043 , B32B15/20 , B32B27/288 , B32B2260/021 , B32B2260/023 , B32B2260/046 , B32B2262/101 , B32B2262/106 , B32B2605/08 , B32B2605/10 , B32B2605/18
摘要: A material system may include: an aluminum layer; a glass composite layer adjacent to the first aluminum layer; and a carbon composite layer adjacent to the first glass composite layer, and opposite to the first aluminum layer. A method of manufacturing a material system may include: stacking an aluminum layer, glass composite layer that may include thermoplastic prepreg plies, and carbon composite layer so that the aluminum layer is adjacent to the glass composite layer, and the glass composite layer is adjacent to the carbon composite layer; and consolidating the thermoplastic prepreg plies to soften the aluminum layer. A method of manufacturing a material system may include: stacking an aluminum layer, glass composite layer that comprises thermoplastic resin, and carbon composite layer so that the glass composite layer is between the aluminum and carbon composite layers; and adjusting temperature and pressure to consolidate the stack.
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公开(公告)号:EP3335869A1
公开(公告)日:2018-06-20
申请号:EP17203697.2
申请日:2017-11-27
申请人: The Boeing Company
CPC分类号: B32B15/14 , B29C70/885 , B32B5/022 , B32B5/024 , B32B5/26 , B32B15/20 , B32B2260/023 , B32B2260/046 , B32B2262/101 , B32B2262/106 , B32B2307/202 , B32B2307/54 , B32B2605/08 , B32B2605/10 , B32B2605/16 , B32B2605/18
摘要: A laminate structure may include: an aluminum layer; a glass composite layer adjacent to the aluminum layer; and/or a carbon composite layer adjacent to the glass composite layer, opposite to the aluminum layer. The glass composite layer may include one or more glass-fiber-reinforced thermoplastic prepreg plies. The carbon composite layer may include one or more carbon-fiber-reinforced thermoplastic prepreg plies. A laminate structure may include: a first aluminum layer; a first glass composite layer adjacent to the first aluminum layer; a first carbon composite layer adjacent to the first glass composite layer, and opposite to the first aluminum layer; and/or a second glass composite layer adjacent to the first carbon composite layer, and opposite to the first glass composite layer. The first glass composite layer may include one or more glass-fiber-reinforced thermoplastic prepreg plies. The first carbon composite layer may include one or more carbon-fiber-reinforced thermoplastic prepreg plies.
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