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公开(公告)号：US10275564B2
公开(公告)日：2019-04-30
申请号：US15186200
申请日：2016-06-17
申请人： THE BOEING COMPANY
摘要： An apparatus is provided for analysis of a repair for a structure by identifying component parts of the structure that have common material properties and geometric constraints, and based thereon determining a generic repair component for the component parts that also have the common material properties and the geometric constraints. A set of loads are extracted from a loads model of the undamaged structure and redistributed in a loads redistribution model at a damaged or defective portion of the component part. The set of redistributed loads indicate loading incurred by the generic repair component under an external load. The apparatus then uses the redistributed loads to perform an analysis to determine a margin of safety of the generic repair component and, in instances in which the margin of safety is positive, outputs the material properties and geometric constraints of the generic repair component to a fabrication system for production thereof.
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公开(公告)号：US11511847B2
公开(公告)日：2022-11-29
申请号：US15471422
申请日：2017-03-28
申请人： The Boeing Company
摘要： A skin panel configured for attachment to an aircraft structure is constructed of a composite material and has a continuous, smooth outer surface; a continuous, smooth inner surface that is configured for attachment to an aircraft structure; a peripheral edge that extends entirely around the skin panel and has a continuous, smooth surface and a plurality of cavities inside the material of the skin panel. The cavities reduce the weight of the skin panel without significantly detracting from the compression strength and tensile strength of the skin panel.
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公开(公告)号：US20190184652A1
公开(公告)日：2019-06-20
申请号：US15847294
申请日：2017-12-19
申请人： THE BOEING COMPANY
CPC分类号： B29C70/443 , B29C65/18 , B29C66/1122 , B29C66/5326 , B29C66/71 , B29C66/721 , B29C66/7212 , B29C66/73941 , B29C66/81455 , B29C73/10 , B29C73/30 , B29D99/0014 , B29L2031/3076 , B29L2031/3082 , B29L2031/3085 , B29K2307/04 , B29K2307/02 , B29K2063/00
摘要： A method of bonding composite structures includes positioning a second structure at a bonding site on a first structure and coupling a first vacuum bag to the first structure such that the first vacuum bag covers the bonding site. The method also includes applying a vacuum to the first vacuum bag to induce a first mechanical force to the second structure via the first vacuum bag. A second vacuum bag is coupled to the first structure such that second vacuum bag covers the second structure and at least a portion of the first vacuum bag. The method further includes applying a vacuum to the second vacuum bag to induce a second mechanical force to the second structure via the second vacuum bag.
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公开(公告)号：US20180065761A1
公开(公告)日：2018-03-08
申请号：US15258919
申请日：2016-09-07
申请人： The Boeing Company
CPC分类号： B64C1/06 , B64C1/068 , B64C1/069 , B64C2001/0072 , B64F5/40
摘要： Disclosed herein is a method of repairing damage to a fuselage barrel, having a one-piece construction, of an aircraft. The method includes determining at least a first virtual splice line and a second virtual splice line along the fuselage barrel in a direction parallel to a longitudinal axis of the fuselage barrel. The method also includes detecting damage in a first section of the fuselage barrel between the first virtual splice line and the second virtual splice line. The method further includes cutting through the fuselage barrel along the first virtual splice line and the second virtual splice line to physically separate the first section from a main section of the fuselage barrel. The method also includes removing the first section from the main section of the fuselage barrel, and splicing a new section to the main section of the fuselage barrel in place of the first section.
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公开(公告)号：US20170364627A1
公开(公告)日：2017-12-21
申请号：US15186200
申请日：2016-06-17
申请人： THE BOEING COMPANY
IPC分类号： G06F17/50
CPC分类号： G06F17/5086 , B29C73/04 , B29C73/24 , B64F5/40 , G06F17/5009
摘要： An apparatus is provided for analysis of a repair for a structure by identifying component parts of the structure that have common material properties and geometric constraints, and based thereon determining a generic repair component for the component parts that also have the common material properties and the geometric constraints. A set of loads are extracted from a loads model of the undamaged structure and redistributed in a loads redistribution model at a damaged or defective portion of the component part. The set of redistributed loads indicate loading incurred by the generic repair component under an external load. The apparatus then uses the redistributed loads to perform an analysis to determine a margin of safety of the generic repair component and, in instances in which the margin of safety is positive, outputs the material properties and geometric constraints of the generic repair component to a fabrication system for production thereof.
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