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公开(公告)号：US10386254B2
公开(公告)日：2019-08-20
申请号：US15137366
申请日：2016-04-25
Applicant: The Boeing Company
Inventor： Lisa G. Schleuter , Kevin Christopher Klohe , Bret Alan Bowers
Abstract: A fastener status detection system is presented. The fastener status detection system comprises a primary fastener, a secondary fastener, and a sensor. The secondary fastener is configured to be a back-up to the primary fastener. The sensor is positioned to measure at least a portion of a load between the primary fastener and the secondary fastener.
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公开(公告)号：US20210053668A1
公开(公告)日：2021-02-25
申请号：US16548576
申请日：2019-08-22
Applicant: The Boeing Company
Inventor： Bryan J. Gruner , Lisa G. Schleuter
Abstract: An aircraft control structure includes first and second outer surfaced joined to a side wall. Stiffening webs extends between the first and second outer surfaces, each stiffening web at least partially surrounding an associated aperture formed in either the first or second outer surface and defining a stiffening recess. Skin plates are sized to extend over an associated stiffening recess and are shaped to conform to an associated aperture. Each skin plate is joined to an associated stiffening web by a friction stir welded seam.
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公开(公告)号：US20170305529A1
公开(公告)日：2017-10-26
申请号：US15137366
申请日：2016-04-25
Applicant: The Boeing Company
Inventor： Lisa G. Schleuter , Kevin Christopher Klohe , Bret Alan Bowers
IPC: B64C9/02
CPC classification number: G01L5/0047 , B64C9/02 , B64D2045/0085 , Y02T50/44
Abstract: A fastener status detection system is presented. The fastener status detection system comprises a primary fastener, a secondary fastener, and a sensor. The secondary fastener is configured to be a back-up to the primary fastener. The sensor is positioned to measure at least a portion of a load between the primary fastener and the secondary fastener.
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Patent Agency Ranking
公开(公告)号：US20200086975A1
公开(公告)日：2020-03-19
申请号：US16135777
申请日：2018-09-19
Applicant: The Boeing Company
Inventor： Michael P. Shemkunas , Lisa G. Schleuter , Bruce A. Dahl , Alain A. Adjorlolo
Abstract: A method of forming a monolithic aircraft structure having multiple aerodynamic surfaces includes forming a body component to have a body skin defining a body skin outer surface, and a body side wall integrally formed with the body skin and defining a body mating surface, the body skin outer surface providing a first aerodynamic surface. A cover component is formed to have a cover mating surface and a cover outer surface opposite the cover mating surface, the cover outer surface defining a second aerodynamic surface. The body component is positioned relative to the cover component so that the body mating surface engages the cover mating surface. At least portions of the cover mating surface are friction stir welded to the body mating surface to form friction stir welded joints between the body component and the cover component.
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公开(公告)号：US11155333B2
公开(公告)日：2021-10-26
申请号：US16548576
申请日：2019-08-22
Applicant: The Boeing Company
Inventor： Bryan J. Gruner , Lisa G. Schleuter
Abstract: An aircraft control structure includes first and second outer surfaced joined to a side wall. Stiffening webs extends between the first and second outer surfaces, each stiffening web at least partially surrounding an associated aperture formed in either the first or second outer surface and defining a stiffening recess. Skin plates are sized to extend over an associated stiffening recess and are shaped to conform to an associated aperture. Each skin plate is joined to an associated stiffening web by a friction stir welded seam.
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公开(公告)号：US11084569B2
公开(公告)日：2021-08-10
申请号：US16135777
申请日：2018-09-19
Applicant: The Boeing Company
Inventor： Michael P. Shemkunas , Lisa G. Schleuter , Bruce A. Dahl , Alain A. Adjorlolo
IPC: B64C9/32 , B64F5/10 , B23K20/12 , B23K20/233 , B64C3/26 , B64C9/02 , B23K103/10 , B23K101/00
Abstract: A method of forming a monolithic aircraft structure having multiple aerodynamic surfaces includes forming a body component to have a body skin defining a body skin outer surface, and a body side wall integrally formed with the body skin and defining a body mating surface, the body skin outer surface providing a first aerodynamic surface. A cover component is formed to have a cover mating surface and a cover outer surface opposite the cover mating surface, the cover outer surface defining a second aerodynamic surface. The body component is positioned relative to the cover component so that the body mating surface engages the cover mating surface. At least portions of the cover mating surface are friction stir welded to the body mating surface to form friction stir welded joints between the body component and the cover component.
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公开(公告)号：US10444128B2
公开(公告)日：2019-10-15
申请号：US15289310
申请日：2016-10-10
Applicant: The Boeing Company
Inventor： Lisa G. Schleuter , Bret Alan Bowers
Abstract: A load path status detection system comprising a primary fastener, a load sensor, a primary structural link, and a secondary structural link. The primary fastener extends through the primary structural link. The load sensor is associated with the primary structural link. The primary structural link carries a load when a primary load path, formed by the primary fastener and the primary structural link, is functioning. The secondary structural link is parallel to the primary structural link, wherein the secondary structural link does not carry a load when the primary load path is functioning.
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公开(公告)号：US20180100790A1
公开(公告)日：2018-04-12
申请号：US15289310
申请日：2016-10-10
Applicant: The Boeing Company
Inventor： Lisa G. Schleuter , Bret Alan Bowers
CPC classification number: G01N3/08 , B64C9/02 , B64D2045/0085 , G01L1/127 , G01L1/2287 , Y02T50/44
Abstract: A load path status detection system comprising a primary fastener, a load sensor, a primary structural link, and a secondary structural link. The primary fastener extends through the primary structural link. The load sensor is associated with the primary structural link. The primary structural link carries a load when a primary load path, formed by the primary fastener and the primary structural link, is functioning. The secondary structural link is parallel to the primary structural link, wherein the secondary structural link does not carry a load when the primary load path is functioning.
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