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公开(公告)号：US20200148326A1
公开(公告)日：2020-05-14
申请号：US16184469
申请日：2018-11-08
Applicant: The Boeing Company
Inventor： Kim A. Linton , James P. Dobberfuhl , Jaime E. Baraja , Hsi-Yung T. Wu
Abstract: An example aircraft wing includes a first skin, a second skin opposite to the first skin, and a composite spar. The composite spar includes a double-flanged spar cap, a single-flanged spar cap, a spar web connecting the double-flanged spar cap and the single-flanged spar cap, and a tear strap. The double-flanged spar cap includes an inward-facing flange and a first outward-facing flange, and the inward-facing flange and the first outward-facing flange are integrated with the first skin during a co-curing process. The single-flanged spar cap includes a second outward-facing flange that is attached to the second skin. The tear strap is stitched to an inner side of the spar web along at least a portion of a length of the composite spar.
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公开(公告)号：US09849967B2
公开(公告)日：2017-12-26
申请号：US14676271
申请日：2015-04-01
Applicant: The Boeing Company
Inventor： James P. Dobberfuhl , Matt D. Uhlman , William J. Moon
Abstract: A rib is disclosed for use in a torque box of a wing structure provided on an aircraft. The wing structure has a skin panel and a stringer coupled to the skin panel. The rib includes a web defining at least one stringer hole sized to receive the stringer, a shear tie coupled to the web and configured to engage the skin panel, and a clip positioned adjacent the at least one stringer hole. The clip has a base coupled to and aligned with the web, a head extending at an angle relative to the base and configured to engage the stringer, and a transition portion extending between the base and the head.
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公开(公告)号：US20180015996A1
公开(公告)日：2018-01-18
申请号：US15209974
申请日：2016-07-14
Applicant: The Boeing Company
Inventor： Michael P. Shemkunas , Kenneth D. Cominsky , Steven S. Heer , David P. Heck , Benjamin D. Smith , John A. Baumann , Matthew D. Uhlman , Burke L. Reichlinger , Eric E. Thomas , James P. Dobberfuhl
IPC: B64C3/18 , B64C3/26 , C25D11/04 , B23K20/233 , B23K20/12 , B23K103/10 , B23K101/12
CPC classification number: B64C3/18 , B23K20/1265 , B23K20/2336 , B23K2101/12 , B23K2103/10 , B64C3/182 , B64C3/185 , B64C3/20 , B64C3/26 , B64C23/065 , B64F5/10 , C25D11/04 , Y02T50/164
Abstract: Provided are wingtip torque boxes and methods of fabricating such boxes using friction stir welding. Specifically, a wingtip torque box may be formed by friction stir welding two monolithic clamshells along their respective spars thereby forming a new monolithic structure. Use of the friction stir welding and monolithic clamshells simplifies the overall fabrication process and yields a robust wingtip torque box that can be bolted on or otherwise attached to an aircraft wing. The wingtip torque box may include internal grid stiffeners and/or external stiffeners that may be also monolithic with other components of the box. For example, the stiffeners may be machined in spars or skin portions of the clamshells during fabrication of clamshells. The wingtip torque box may have a continuous cavity extending between the ends and, in some embodiments, between spars of the box and providing access for performing various operations inside the box.
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公开(公告)号：US20240399408A1
公开(公告)日：2024-12-05
申请号：US18326882
申请日：2023-05-31
Applicant: The Boeing Company
Inventor： James P. Dobberfuhl , Jordon T. Ho , Allan Tien , Nathan H. Jones , Jason A. Fraser , Scott F. Hart
Abstract: A dauber assembly may comprise a manifold body comprising a first end configured to receive a nozzle, and a collar extending at least partially around the manifold body. The collar may comprise an inlet port. The manifold body may have one or more holes providing fluid communication between the inlet port of the collar and an outlet of a nozzle received by the first end of the manifold body.
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Patent Agency Ranking
公开(公告)号：US20240399407A1
公开(公告)日：2024-12-05
申请号：US18327365
申请日：2023-06-01
Applicant: The Boeing Company
Inventor： James P. Dobberfuhl , Nathan H. Jones , Jason A. Fraser , Mark D. Fuller , Raajan N. Desai , Allan Tien
Abstract: A gripper for a fastener installation assembly includes a body having a passage extending from a first end of the body to a second end of the body. The gripper includes an inlet of the passage disposed at the second end of the body and an outlet of the passage disposed at the first end of the body. The first end of the body includes a lip configured to engage a fastener and the lip includes the outlet of the passage. The inlet is configured to couple to a sealant source to receive sealant into the passage. The gripper is configured such that sealant received at the inlet passes through the passage and is dispensed through the outlet onto the fastener engaged by the lip of the body.
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公开(公告)号：US20220153400A1
公开(公告)日：2022-05-19
申请号：US17454399
申请日：2021-11-10
Applicant: The Boeing Company
Inventor： Darrell D. Jones , Daniel R. Smith , Carlos Walker , Kurtis Shuldberg Willden , Hiteshkumar M. Patel , Jacob E. Koopmans , Scott Krajca , James P. Dobberfuhl , Marcus C. Hart , Gregory R. Klempel , Steven Kuan-chi Wu , Justin K. Alfred
Abstract: Systems and methods are provided for fabricating multiple segment spars for an aircraft. In one example the method includes fabricating preforms of fiber reinforced material for spar segments, hardening the preforms to form the spar segments, and bonding the spar segments together to form a completed spar detail. In addition to bonding, other examples include co-curing and fastening the spar segments. In additional examples, the spar segments include kinks or sub-kinks as described.
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公开(公告)号：US11001363B2
公开(公告)日：2021-05-11
申请号：US16184469
申请日：2018-11-08
Applicant: The Boeing Company
Inventor： Kim A. Linton , James P. Dobberfuhl , Jaime E. Baraja , Hsi-Yung T. Wu
Abstract: An example aircraft wing includes a first skin, a second skin opposite to the first skin, and a composite spar. The composite spar includes a double-flanged spar cap, a single-flanged spar cap, a spar web connecting the double-flanged spar cap and the single-flanged spar cap, and a tear strap. The double-flanged spar cap includes an inward-facing flange and a first outward-facing flange, and the inward-facing flange and the first outward-facing flange are integrated with the first skin during a co-curing process. The single-flanged spar cap includes a second outward-facing flange that is attached to the second skin. The tear strap is stitched to an inner side of the spar web along at least a portion of a length of the composite spar.
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公开(公告)号：US10479474B2
公开(公告)日：2019-11-19
申请号：US15209974
申请日：2016-07-14
Applicant: The Boeing Company
Inventor： Michael P. Shemkunas , Kenneth D. Cominsky , Steven S. Heer , David P. Heck , Benjamin D. Smith , John A. Baumann , Matthew D. Uhlman , Burke L. Reichlinger , Eric E. Thomas , James P. Dobberfuhl
IPC: B64C3/18 , B23K20/12 , B23K20/233 , B64C3/26 , C25D11/04 , B23K101/12 , B23K103/10
Abstract: Provided are wingtip torque boxes and methods of fabricating such boxes using friction stir welding. Specifically, a wingtip torque box may be formed by friction stir welding two monolithic clamshells along their respective spars thereby forming a new monolithic structure. Use of the friction stir welding and monolithic clamshells simplifies the overall fabrication process and yields a robust wingtip torque box that can be bolted on or otherwise attached to an aircraft wing. The wingtip torque box may include internal grid stiffeners and/or external stiffeners that may be also monolithic with other components of the box. For example, the stiffeners may be machined in spars or skin portions of the clamshells during fabrication of clamshells. The wingtip torque box may have a continuous cavity extending between the ends and, in some embodiments, between spars of the box and providing access for performing various operations inside the box.
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公开(公告)号：US20160288899A1
公开(公告)日：2016-10-06
申请号：US14676271
申请日：2015-04-01
Applicant: The Boeing Company
Inventor： James P. Dobberfuhl , Matt D. Uhlman , William J. Moon
Abstract: A rib is disclosed for use in a torque box of a wing structure provided on an aircraft. The wing structure has a skin panel and a stringer coupled to the skin panel. The rib includes a web defining at least one stringer hole sized to receive the stringer, a shear tie coupled to the web and configured to engage the skin panel, and a clip positioned adjacent the at least one stringer hole. The clip has a base coupled to and aligned with the web, a head extending at an angle relative to the base and configured to engage the stringer, and a transition portion extending between the base and the head.
Abstract translation: 公开了一种用于设置在飞行器上的机翼结构的扭矩箱的肋。 机翼结构具有皮肤面板和连接到皮肤面板的纵梁。 所述肋包括限定至少一个纵梁孔的腹板，所述至少一个纵梁孔的尺寸适于容纳所述纵梁，联接到所述腹板并且被构造成接合所述皮肤面板的剪切平台以及邻近所述至少一个纵梁孔定位的夹子。 夹子具有联接到腹板上并与其对准的基部，头部相对于基部以一定角度延伸并且构造成接合纵梁，以及在基部和头部之间延伸的过渡部分。
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