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1.发明公开公开(公告)号：US20230356857A1
公开(公告)日：2023-11-09
申请号：US17735426
申请日：2022-05-03
申请人： The Boeing Company
发明人： Santiago Mejia , Patrick James Macko , Byron James Autry , Paul Gabriel Werntges , Larry Scott Smotherman , David Raines , Sara Murphy
IPC分类号： B64F5/10
CPC分类号： B64F5/10
摘要： A device to assemble a skin and a frame of an aircraft fuselage. The device includes first and second brace members that extend along opposing sides of a gap. Arches are spaced apart and fixedly connected to the first and second brace members and that extend across the gap. A strongback is attached to and movable along the first and second brace members with the strongback having a curved shape that matches the plurality of arches. The strongback includes clamps configured to engage with the frame. First and second tension devices apply tension to the skin at the strongback.
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公开(公告)号：US11459124B2
公开(公告)日：2022-10-04
申请号：US16798220
申请日：2020-02-21
申请人： The Boeing Company
发明人： David Howard Curry, III , David Raines , Scott L. Smotherman , Paul Gabriel Werntges , Dennis Ray Mathis , Charlie E. Branyon, III , Daniel B. Freeman
摘要： An apparatus for mounting a splice component for joining two or more workpieces includes a base plate and one or more bias assemblies. The base plate includes one or more passageways extending through the base plate and one or more barrier elements mounted proximate to the passageway(s). Each barrier element and associated passageway are configured to freely receive a protrusion of a splice component. The bias assembly includes a bias element that extends proximate to the passageway and is configured to move resiliently to urge the protrusion against the barrier element. The passageway, the barrier element, and the bias assembly are configured to allow movement of the splice component relative to the base plate transverse to a direction of force applied by the bias element on the protrusion.
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3.发明公开公开(公告)号：US20240101277A1
公开(公告)日：2024-03-28
申请号：US18526548
申请日：2023-12-01
申请人： The Boeing Company
发明人： Santiago Mejia , Patrick James Macko , Byron James Autry , Paul Gabriel Werntges , Larry Scott Smotherman , David Raines , Sara Murphy
IPC分类号： B64F5/10
CPC分类号： B64F5/10 , B23P2700/01 , B64C1/061
摘要： A device to assemble a skin and a frame of an aircraft fuselage. The device includes first and second brace members that extend along opposing sides of a gap. Arches are spaced apart and fixedly connected to the first and second brace members and that extend across the gap. A strongback is attached to and movable along the first and second brace members with the strongback having a curved shape that matches the plurality of arches. The strongback includes clamps configured to engage with the frame. First and second tension devices apply tension to the skin at the strongback.
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公开(公告)号：US11931845B2
公开(公告)日：2024-03-19
申请号：US17548704
申请日：2021-12-13
申请人： The Boeing Company
摘要： In an example, a system is disclosed. The system comprises a one-piece mandrel, a fuselage coupled to the one-piece mandrel, and a strongback apparatus positioned on the fuselage. The strongback apparatus comprises an arcuate central body comprising a front end, a rear end, and a plurality of elongated members that connect the front end to the rear end, and actuators mounted to the plurality of elongated members. The actuators are configured to move in a radially outward direction from extended positions to retracted positions and comprise (i) proximal ends mounted to the plurality of elongated members and (ii) distal ends having vacuum suction cups. In the extended positions, the vacuum suction cups engage the fuselage on which the strongback apparatus is positioned. As the actuators moves from the extended positions to the retracted positions, the vacuum suction cups pull the fuselage away from the one-piece mandrel.
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公开(公告)号：US11866201B2
公开(公告)日：2024-01-09
申请号：US17735426
申请日：2022-05-03
申请人： The Boeing Company
发明人： Santiago Mejia , Patrick James Macko , Byron James Autry , Paul Gabriel Werntges , Larry Scott Smotherman , David Raines , Sara Murphy
CPC分类号： B64F5/10 , B23P2700/01 , B64C1/061 , B64C1/068 , B64C1/12
摘要： A device to assemble a skin and a frame of an aircraft fuselage. The device includes first and second brace members that extend along opposing sides of a gap. Arches are spaced apart and fixedly connected to the first and second brace members and that extend across the gap. A strongback is attached to and movable along the first and second brace members with the strongback having a curved shape that matches the plurality of arches. The strongback includes clamps configured to engage with the frame. First and second tension devices apply tension to the skin at the strongback.
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公开(公告)号：US11724421B2
公开(公告)日：2023-08-15
申请号：US17454273
申请日：2021-11-10
申请人： The Boeing Company
发明人： Darrell D. Jones , Daniel R. Smith , Patrick B. Stone , David Raines , Byron James Autry , Matthew B. Moore
CPC分类号： B29C33/50 , B29C70/342 , B29C70/54 , B64F5/10 , B64F5/50 , B64C1/12 , B64C2001/0072
摘要： Systems and methods are provided for demolding a composite part from a mandrel. The method includes mechanically coupling a first arm of an extraction tool to a first arcuate portion of a composite part that has been hardened onto a mandrel, mechanically coupling a second arm of an extraction tool to a second arcuate portion of the composite part, and separating the composite part from the mandrel by iteratively performing the following operations until the composite part no longer contacts the mandrel: elastically straining the first arcuate portion of the composite part via the first arm, and elastically straining the second arcuate portion of the composite part via the second arm.
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公开(公告)号：US20220184760A1
公开(公告)日：2022-06-16
申请号：US17548704
申请日：2021-12-13
申请人： The Boeing Company
摘要： In an example, a system is disclosed. The system comprises a one-piece mandrel, a fuselage coupled to the one-piece mandrel, and a strongback apparatus positioned on the fuselage. The strongback apparatus comprises an arcuate central body comprising a front end, a rear end, and a plurality of elongated members that connect the front end to the rear end, and actuators mounted to the plurality of elongated members. The actuators are configured to move in a radially outward direction from extended positions to retracted positions and comprise (i) proximal ends mounted to the plurality of elongated members and (ii) distal ends having vacuum suction cups. In the extended positions, the vacuum suction cups engage the fuselage on which the strongback apparatus is positioned. As the actuators moves from the extended positions to the retracted positions, the vacuum suction cups pull the fuselage away from the one-piece mandrel.
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公开(公告)号：US20220152880A1
公开(公告)日：2022-05-19
申请号：US17454273
申请日：2021-11-10
申请人： The Boeing Company
发明人： Darrell D. Jones , Daniel R. Smith , Patrick B. Stone, II , David Raines , Byron James Autry , Matthew B. Moore
摘要： Systems and methods are provided for demolding a composite part from a mandrel. The method includes mechanically coupling a first arm of an extraction tool to a first arcuate portion of a composite part that has been hardened onto a mandrel, mechanically coupling a second arm of an extraction tool to a second arcuate portion of the composite part, and separating the composite part from the mandrel by iteratively performing the following operations until the composite part no longer contacts the mandrel: elastically straining the first arcuate portion of the composite part via the first arm, and elastically straining the second arcuate portion of the composite part via the second arm.
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公开(公告)号：US20210261231A1
公开(公告)日：2021-08-26
申请号：US16798220
申请日：2020-02-21
申请人： The Boeing Company
发明人： David Howard Curry, III , David Raines , Scott L. Smotherman , Paul Gabriel Werntges , Dennis Ray Mathis , Charlie E. Branyon, III , Daniel B. Freeman
摘要： An apparatus for mounting a splice component for joining two or more workpieces includes a base plate and one or more bias assemblies. The base plate includes one or more passageways extending through the base plate and one or more barrier elements mounted proximate to the passageway(s). Each barrier element and associated passageway are configured to freely receive a protrusion of a splice component. The bias assembly includes a bias element that extends proximate to the passageway and is configured to move resiliently to urge the protrusion against the barrier element. The passageway, the barrier element, and the bias assembly are configured to allow movement of the splice component relative to the base plate transverse to a direction of force applied by the bias element on the protrusion.
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