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1.发明授权公开(公告)号：US12259362B2
公开(公告)日：2025-03-25
申请号：US17454294
申请日：2021-11-10
Applicant: The Boeing Company
Inventor： Daniel R. Smith , Darrell D. Jones , Barry A. Fetzer , Jeremy Evan Justice , James C. Kennedy
IPC: G01N29/27 , G01N29/06 , G01N29/22 , G01N29/28 , G05B19/4155
Abstract: Systems and methods are provided for inspecting aircraft fuselages. Non-Destructive Inspection (NDI) stations inspect sections of a fuselage via pulsed-line assembly techniques. After each pulse, a section of fuselage is moved by less than its length, and one or more NDI stations disposed at different portions of the section to inspect the section of fuselage for out-of-tolerance conditions. A method for inspecting a structure for inconsistencies which includes advancing a structure along a track in a process direction through a Non-Destructive Inspection (NDI) station, indexing the structure to the NDI station and inspecting the structure with the NDI station.
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公开(公告)号：US12194651B2
公开(公告)日：2025-01-14
申请号：US17454255
申请日：2021-11-10
Applicant: The Boeing Company
Inventor： Daniel R. Smith , Darrell D. Jones , Monte D. Wright
Abstract: Apparatus and methods are provided for fabrication of a structure, for example, a half barrel section of a fuselage. The apparatus includes an indexing unit dimensioned for coupling to an indexing feature disposed on the structure. The structure proceeds along a process direction during fabrication. A cutting station cuts out manufacturing excess from the structure to form, for example, openings for windows and doors. A method for fabrication of a structure includes indexing a structure to a cutting station based on an indexing feature associated or located on the structure. The method includes operating the cutting station to cut manufacturing excess from the structure. A method includes removing cut sections of the manufacturing excess and routing these sections away from the cutting station.
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公开(公告)号：US12049330B2
公开(公告)日：2024-07-30
申请号：US17454291
申请日：2021-11-10
Applicant: The Boeing Company
Inventor： Daniel R. Smith , Darrell D. Jones , Jeremy Evan Justice
Abstract: Systems and methods are provided for assembling an aircraft. The method includes receiving a lower half barrel section of fuselage that is inverted to a keel-up orientation; and installing a floor grid into the lower half barrel section while inverted.
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公开(公告)号：US20240166372A1
公开(公告)日：2024-05-23
申请号：US18425314
申请日：2024-01-29
Applicant: The Boeing Company
Inventor： Daniel R. Smith , Darrell D. Jones
CPC classification number: B64F5/10 , B29C65/087 , B64C1/068 , B64F5/50 , B29L2031/3082
Abstract: Systems and methods are provided for assembling a section of a fuselage of an aircraft. The method includes pulsing a half barrel section of the fuselage along a track in a process direction, utilizing an indexing feature associated with the half barrel section to determine a desired contour for a portion of the half barrel section, and enforcing the desired contour onto the half barrel section using components that enforce an inner mold line and components that enforce an outer mold line when the half barrel section is out of tolerance from the desired contour.
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公开(公告)号：US20240158099A1
公开(公告)日：2024-05-16
申请号：US18545481
申请日：2023-12-19
Applicant: The Boeing Company
Inventor： Daniel R. Smith , Darrell D. Jones
CPC classification number: B64F5/10 , B23P21/004 , B64C3/185 , B64C3/187 , B64C3/26 , B64F5/50 , B23P2700/01
Abstract: Systems and methods are provided for assembling a wing. Methods include suspending an upper wing panel of an aircraft beneath a shuttle, translating a rib to a position it, and placing the rib into contact with, then affixing the rib to, the upper wing panel, while suspended. Some methods include installing ribs and spars to the upper wing panel, and joining a lower wing panel to the ribs and spars, while the upper wing panel is suspended. Some methods involve joining ribs to spars (e.g., all, or some) to produce a support structure that is then affixed to the upper wing panel. Systems include a shuttle that suspends an upper wing panel, and a cart that includes supports to hold a rib, a chassis to translate the rib to a position beneath the upper wing panel, and a lifting apparatus to lift the rib into contact with the upper wing panel.
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Patent Agency Ranking
公开(公告)号：US11926435B2
公开(公告)日：2024-03-12
申请号：US17454263
申请日：2021-11-10
Applicant: The Boeing Company
Inventor： Daniel R. Smith , Darrell D. Jones , Frederick M. Swanstrom
CPC classification number: B64F5/10 , B23P21/004 , B23P2700/01
Abstract: Systems and methods are provided for assembling a structure. The systems and method including micro pulsing a structure along a track in a process direction by less than a length of the structure. The structure is indexed to one or more work stations by mating indexing features in a manufacturing excess of the structure to complementary features at the work stations. The work stations would the perform work on the structure at the work stations while the structure is indexed to the work stations. Iteratively repeating the micro pulsing and indexing and working upon the structure until it is ready to advance to the next assembly process.
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公开(公告)号：US11897210B2
公开(公告)日：2024-02-13
申请号：US17454265
申请日：2021-11-10
Applicant: The Boeing Company
Inventor： Daniel R. Smith , Darrell D. Jones , Byron James Autry , James R. Kendall , Raviendra Sidath Suriyaarachchi
CPC classification number: B29C70/549 , B29C70/342 , B29C70/443
Abstract: Methods and apparatus involved in the process of hardening a composite part are disclosed herein. The methods include applying a preform to a mandrel, covering the preform with a caul plate, sealing the caul plate to the mandrel, pushing the caul plate toward the preform and the mandrel and hardening the preform into a composite part while the caul plate is held against the preform. The apparatus include a mandrel, a caul plate which defines a surface of a preform and where the caul plate may include a rigid material and seals disposed between the mandrel and the caul plate. In an additional aspect, the apparatus may include a sealed chamber with a mandrel and a caul plate and a circumferential seal between the mandrel and the caul plate.
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公开(公告)号：US11891193B2
公开(公告)日：2024-02-06
申请号：US17454289
申请日：2021-11-10
Applicant: The Boeing Company
Inventor： Daniel R. Smith , Darrell D. Jones
CPC classification number: B64F5/10 , B23P21/004 , B64C3/185 , B64C3/187 , B64C3/26 , B64F5/50 , B23P2700/01
Abstract: Systems and methods are provided for assembling a wing. Methods include suspending an upper wing panel of an aircraft beneath a shuttle, translating a rib to a position it, and placing the rib into contact with, then affixing the rib to, the upper wing panel, while suspended. Some methods include installing ribs and spars to the upper wing panel, and joining a lower wing panel to the ribs and spars, while the upper wing panel is suspended. Some methods involve joining ribs to spars (e.g., all, or some) to produce a support structure that is then affixed to the upper wing panel. Systems include a shuttle that suspends an upper wing panel, and a cart that includes supports to hold a rib, a chassis to translate the rib to a position beneath the upper wing panel, and a lifting apparatus to lift the rib into contact with the upper wing panel.
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公开(公告)号：US11724422B2
公开(公告)日：2023-08-15
申请号：US16876635
申请日：2020-05-18
Applicant: The Boeing Company
CPC classification number: B29C33/505 , B29C35/02 , B29C66/634 , B64C1/064 , B29L2031/3076
Abstract: A system for preparing a bladder for use in manufacturing a composite stringer includes a sock application station, a film application station, and a composite ply application station. The sock application station has a sock cartridge configured to progressively apply a breather sock of breather material in tubular form onto a bladder as the bladder exits the sock cartridge to thereby result in a sock-bladder assembly. The film application station is located downstream of the sock application station and is configured to inflate a film from a flat shape into an open film tube prior to application over the sock-bladder assembly to thereby result in a film-sock-bladder assembly. The composite ply application station is located downstream of the film application station and has a wrap ply forming bed containing at least one forming bed opening and configured to receive one or more wrap plies of a wrap laminate for urging into the forming bed opening by the film-sock-bladder assembly to produce a ply-film-sock-bladder assembly.
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公开(公告)号：US11660830B2
公开(公告)日：2023-05-30
申请号：US16252260
申请日：2019-01-18
Applicant: The Boeing Company
Inventor： Daniel Rotter , Lisa Carlson , Brad Andrew Coxon , Hyukbong Kwon , Khanh Mai Pham , Darrell D. Jones , Brian Robins
CPC classification number: B29C70/462 , B29C70/02 , B29D99/0003 , B64C1/064 , B64C1/12 , B64F5/10 , B29K2307/04 , B29L2031/3076
Abstract: Aircraft that incorporates a rounded-hat composite stringer connected to an inner side of the skin of the aircraft to form an elongate conduit that defines a conduit axis, where the conduit axis includes at least one curving portion. The rounded-hat composite stringer can be manufactured by constructing a lower forming die and an upper forming die, each forming die having a length and defining a curve along at least a portion of the length of the die, cutting a pre-cured flat composite charge dimensioned to form the rounded-hat composite stringer, pressing the flat composite charge between the lower and upper forming dies to shape the composite charge into a pre-formed stringer having an inner side between curved fillet portions, contacting a forming member against the inner side of the pre-formed stringer, applying radius fillers to the curved fillet portions of the pre-formed stringer, curing the pre-formed stringer, and removing the forming member from the cured stringer.
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