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公开(公告)号：US10189578B2
公开(公告)日：2019-01-29
申请号：US13915994
申请日：2013-06-12
Applicant: The Boeing Company
Inventor： Paul Diep , Bernhard Dopker , Robert W. Johnson
Abstract: A pressure bulkhead may include a bulkhead wall having a radially inner disk and a radially outer compression ring, the outer compression ring being reinforced to balance meridional and hoop stresses sustained by the bulkhead wall in response to a pressure differential across the pressure bulkhead; and the radially inner disk being unitary with the outer compression ring and being made of the same material as the outer compression ring.
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公开(公告)号：US11420718B2
公开(公告)日：2022-08-23
申请号：US16832176
申请日：2020-03-27
Applicant: The Boeing Company
Inventor： Joel Kevin Joseph , Max Tyler Breedlove , Paul Diep , Peter John Newnham
Abstract: An aircraft tail assembly includes an aft fuselage section secured to a forward fuselage section, and includes a stiffener-reinforced pivot bulkhead defined by separate parts secured together by a first set of splices. A longeron extends longitudinally along the aft and forward fuselage sections, and includes a discontinuity adjacent a peripheral edge of the pivot bulkhead. The aircraft tail assembly includes a second set of splices that overlie the discontinuity. One of the second set of splices extends laterally over the longeron to bridge the discontinuity adjacent the peripheral edge of the pivot bulkhead, and another of the second set of splices extends longitudinally along the longeron to secure the longeron to the pivot bulkhead adjacent the discontinuity. A chord engages the peripheral edge of the pivot bulkhead to facilitate transfers of force loads from the bulkhead along a load path that includes the longerons and the splices.
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公开(公告)号：US11701796B2
公开(公告)日：2023-07-18
申请号：US17526718
申请日：2021-11-15
Applicant: THE BOEING COMPANY
Inventor： Courtney Michele Fix , Robert Wayne Murray , Paul Diep , Robert E. Lee , Richard A. Skilton , Ronald Leroy McGhee , Zachary Nathaniel Stoddard , Patrick B. Stone , Phillip Andrew Taylor , Nickolas Scott Ellerbeck
CPC classification number: B29C33/485 , B29C33/44 , B29C37/0003 , B64C1/064 , B29L2031/3082
Abstract: A system includes a mandrel contoured to define a tapering tubular shape of a workpiece cured on the mandrel and a demolding tool. The demolding tool is configured to remove the workpiece from the mandrel after the workpiece is cured on the mandrel and cut longitudinally. The demolding tool is configured to remove the workpiece from the mandrel by deforming a first end of the workpiece to at least partially disengage the first end of the workpiece from a first end of the mandrel, and subsequently, deforming a second end of the workpiece to at least partially disengage the second end of the workpiece from a second end of the mandrel. The first end of the workpiece may have a first cross-sectional area that is smaller than a second cross-sectional area of the second end of the workpiece.
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公开(公告)号：US20220193958A1
公开(公告)日：2022-06-23
申请号：US17526718
申请日：2021-11-15
Applicant: THE BOEING COMPANY
Inventor： Courtney Michele Fix , Robert Wayne Murray , Paul Diep , Robert E. Lee , Richard A. Skilton , Ronald Leroy McGhee , Zachary Nathaniel Stoddard , Patrick B. Stone , Phillip Andrew Taylor , Nickolas Scott Ellerbeck
Abstract: A system includes a mandrel contoured to define a tapering tubular shape of a workpiece cured on the mandrel and a demolding tool. The demolding tool is configured to remove the workpiece from the mandrel after the workpiece is cured on the mandrel and cut longitudinally. The demolding tool is configured to remove the workpiece from the mandrel by deforming a first end of the workpiece to at least partially disengage the first end of the workpiece from a first end of the mandrel, and subsequently, deforming a second end of the workpiece to at least partially disengage the second end of the workpiece from a second end of the mandrel. The first end of the workpiece may have a first cross-sectional area that is smaller than a second cross-sectional area of the second end of the workpiece.
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公开(公告)号：US08960606B2
公开(公告)日：2015-02-24
申请号：US13665664
申请日：2012-10-31
Applicant: The Boeing Company
Inventor： Paul Diep , Bernhard Dopker
CPC classification number: B64C1/069 , B64C1/064 , B64C1/12 , Y10T29/49622
Abstract: The disclosed shell structure splice and method may include a first panel having a first edge, a second panel having a second edge, the second edge being positioned in edgewise alignment with the first edge to form a splice joint, a strap bridging the splice joint and attached to the first panel and the second panel, the strap having a first tapered region and a second tapered region, a first fitting having a tapered section and a flat section, the tapered section being attached to the first tapered region of the strap, and a second fitting having a tapered section and a flat section, the tapered section being attached to the second tapered region of the strap.
Abstract translation: 所公开的壳体结构接头和方法可以包括具有第一边缘的第一面板，具有第二边缘的第二面板，第二边缘与第一边缘沿边缘对齐，以形成接合接头，桥接接头接头的带子和 附接到第一面板和第二面板，带子具有第一锥形区域和第二锥形区域，第一配件具有锥形部分和平坦部分，锥形部分附接到带子的第一锥形区域，以及 具有锥形部分和平坦部分的第二配件，所述锥形部分附接到所述带子的第二锥形区域。
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Patent Agency Ranking
公开(公告)号：US20140117157A1
公开(公告)日：2014-05-01
申请号：US13665664
申请日：2012-10-31
Applicant: The Boeing Company
Inventor： Paul Diep , Bernhard Dopker
CPC classification number: B64C1/069 , B64C1/064 , B64C1/12 , Y10T29/49622
Abstract: The disclosed shell structure splice and method may include a first panel having a first edge, a second panel having a second edge, the second edge being positioned in edgewise alignment with the first edge to form a splice joint, a strap bridging the splice joint and attached to the first panel and the second panel, the strap having a first tapered region and a second tapered region, a first fitting having a tapered section and a flat section, the tapered section being attached to the first tapered region of the strap, and a second fitting having a tapered section and a flat section, the tapered section being attached to the second tapered region of the strap.
Abstract translation: 所公开的壳体结构接头和方法可以包括具有第一边缘的第一面板，具有第二边缘的第二面板，第二边缘与第一边缘沿边缘对齐，以形成接合接头，桥接接头接头的带子和 附接到第一面板和第二面板，带子具有第一锥形区域和第二锥形区域，第一配件具有锥形部分和平坦部分，锥形部分附接到带子的第一锥形区域，以及 具有锥形部分和平坦部分的第二配件，所述锥形部分附接到所述带子的第二锥形区域。
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公开(公告)号：US20210300519A1
公开(公告)日：2021-09-30
申请号：US16832176
申请日：2020-03-27
Applicant: The Boeing Company
Inventor： Joel Kevin Joseph , Max Tyler Breedlove , Paul Diep , Peter John Newnham
Abstract: An aircraft tail assembly includes an aft fuselage section secured to a forward fuselage section, and includes a stiffener-reinforced pivot bulkhead defined by separate parts secured together by a first set of splices. A longeron extends longitudinally along the aft and forward fuselage sections, and includes a discontinuity adjacent a peripheral edge of the pivot bulkhead. The aircraft tail assembly includes a second set of splices that overlie the discontinuity. One of the second set of splices extends laterally over the longeron to bridge the discontinuity adjacent the peripheral edge of the pivot bulkhead, and another of the second set of splices extends longitudinally along the longeron to secure the longeron to the pivot bulkhead adjacent the discontinuity. A chord engages the peripheral edge of the pivot bulkhead to facilitate transfers of force loads from the bulkhead along a load path that includes the longerons and the splices.
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公开(公告)号：US10464691B2
公开(公告)日：2019-11-05
申请号：US16210430
申请日：2018-12-05
Applicant: The Boeing Company
Inventor： Paul Diep , Bernhard Dopker , Robert W. Johnson
Abstract: A pressure bulkhead for a vehicle disclosed. The pressure bulkhead is configured to separate a pressurized interior from an unpressurized interior of the vehicle. The pressure bulkhead includes a bulkhead wall having a radially inner disk and a radially outer compression ring. The radially inner disk has a surface and a first thickness and the radially outer compression ring having a second thickness that is greater than the first thickness. The radially outer compression ring defines a periphery of the bulkhead wall and the second thickness of the radially outer compression ring is effective to provide a strength to oppose meridional and hoop stresses across the surface of the radially inner disk in response to a pressure differential across the bulkhead wall. The pressure bulkhead also includes an attachment ring that is affixed to the periphery of the bulkhead wall.
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公开(公告)号：US20190106222A1
公开(公告)日：2019-04-11
申请号：US16210430
申请日：2018-12-05
Applicant: The Boeing Company
Inventor： Paul Diep , Bernhard Dopker , Robert W. Johnson
CPC classification number: B64D45/00 , B62D25/00 , B63B3/60 , B64C1/10 , Y10T29/49826 , Y10T428/215
Abstract: A pressure bulkhead for a vehicle disclosed. The pressure bulkhead is configured to separate a pressurized interior from an unpressurized interior of the vehicle. The pressure bulkhead includes a bulkhead wall having a radially inner disk and a radially outer compression ring. The radially inner disk has a surface and a first thickness and the radially outer compression ring having a second thickness that is greater than the first thickness. The radially outer compression ring defines a periphery of the bulkhead wall and the second thickness of the radially outer compression ring is effective to provide a strength to oppose meridional and hoop stresses across the surface of the radially inner disk in response to a pressure differential across the bulkhead wall. The pressure bulkhead also includes an attachment ring that is affixed to the periphery of the bulkhead wall.
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10.发明申请公开(公告)号：US20180345591A1
公开(公告)日：2018-12-06
申请号：US15608245
申请日：2017-05-30
Applicant: The Boeing Company
Inventor： Kenneth D. Cominsky , Trevor Shane McCrea , David Eric Gideon , Bernhard Dopker , Paul Diep , Julie Frances Murphy , Jordan Seth Erickson
IPC: B29C65/00
CPC classification number: B29C43/021 , B29C65/02 , B29C66/0384 , B29C66/1122 , B29C66/1162 , B29C66/12443 , B29C66/12464 , B29C66/1282 , B29C66/12822 , B29C66/12841 , B29C66/12842 , B29C66/12862 , B29C66/43 , B29C66/435 , B29C66/4722 , B29C66/7212 , B29C66/73921 , B29D99/001 , B29K2101/12 , B29K2105/06 , B29K2307/04 , B29L2031/3076
Abstract: A method of constructing a large, complex composite panel involves connecting smaller compression molded thermoplastic subpanels, edge to edge using a thermoplastic co-consolidation method. The edges of adjacent subpanels are given complementary surface configurations. The surface configurations are overlapped and heat and pressure are applied to the overlapping surface constructions to co-consolidate the surface constructions in forming a large, composite panel of two or more subpanels.
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