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1.发明公开公开(公告)号：US20230341303A1
公开(公告)日：2023-10-26
申请号：US17726091
申请日：2022-04-21
Applicant: The Boeing Company
Inventor： Joseph D. Schaefer , Brian P. Justusson , Haozhong Gu
IPC: G01N3/08
CPC classification number: G01N3/08 , G01N2203/04 , G01N2203/0017
Abstract: A tension load fixture for applying tension or loading forces to a specimen comprises a pair of tension arms and an imaging device. The pair of tension arms are configured to releasably couple to opposite end regions of a specimen and to apply tension or loading forces to the specimen. The specimen is configured to be positioned between the pair of tension arms and defines a notch between the opposite end regions of the specimen. The notch extends from a side of the specimen to a middle region of the specimen. The imaging device is configured to capture one or more images of the middle region of the specimen and is configured to rotate about a central axis of the tension load fixture that is proximate to the middle region of the specimen to facilitate generation of a three-dimensional image of the middle region of the specimen as the specimen is subjected to tension or loading forces.
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2.发明申请公开(公告)号：US20200173881A1
公开(公告)日：2020-06-04
申请号：US16207311
申请日：2018-12-03
Applicant: The Boeing Company
Inventor： Joseph D. Schaefer , Brian P. Justusson
Abstract: A computer is configured to generate visual representations of a composite filler material, such as a noodle or a crossply laminate, for example, to determine the progressive creation, density, and spacing of a plurality of cracks in the filler material. The composite filler material is disposed at a connection interface between a load-bearing composite structural component, such as a stringer or a spar, for example, and the structural framework of a vehicle on which those structural components are utilized.
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公开(公告)号：US20230401686A1
公开(公告)日：2023-12-14
申请号：US17664463
申请日：2022-05-23
Applicant: The Boeing Company
Inventor： Bryan Lilley , Brittan A. Farmer , Troy Winfree , Yadan Wu , Brian P. Justusson , Jordan A. Severson
CPC classification number: G06T7/0004 , G06T2207/10072 , G06F30/15
Abstract: A computer-based method for evaluating progressive damage in a metal test component includes providing Computed Tomography (CT) image data of the component to a processor and processing the CT image data via the processor, including detecting observable defects in the component. The method also includes characterizing the observable defects into corresponding defect categories, generating a data table of the observable defects and the corresponding defect categories, and embedding a collective set of data from the data table into a finite element model (FEM) of the component to thereby construct a modified FEM of the metal test component. Additionally, the method includes analyzing the modified FEM through an isotropic and/or anisotropic structural model, via the processor, to thereby generate a set of test results. A quality control action is then executed with respect to the metal test component based on the test results.
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公开(公告)号：US20230306147A1
公开(公告)日：2023-09-28
申请号：US17689563
申请日：2022-03-08
Applicant: The Boeing Company
Inventor： Joseph D. Schaefer , Brian P. Justusson
Abstract: An example method includes determining analytical material properties indicative of an effective fracture behavior of a through-thickness reinforcement. The method also includes obtaining data defining a cohesive formulation within a finite element analyzer. The cohesive formulation is representative of the through-thickness reinforcement, and the data defining the cohesive formulation is derived from the analytical material properties. The method further includes generating a finite element model for the composite structure. The composite structure includes the through-thickness reinforcement, and the finite element model represents the through-thickness reinforcement using the cohesive formulation. The method also includes analyzing a mechanical performance of the composite structure using the finite element analyzer and the finite element model, and outputting data indicative of the mechanical performance of the composite structure.
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公开(公告)号：US20230049264A1
公开(公告)日：2023-02-16
申请号：US17399815
申请日：2021-08-11
Applicant: The Boeing Company
Inventor： Brian P. Justusson , Joseph D. Schaefer
Abstract: An example method includes determining, by a computing system, a dry thickness of a fabric preform. The method also includes determining, by the computing system, a debulked thickness of the fabric preform using the dry thickness of the fabric preform. In addition, the method includes determining, by the computing system, a stitch tension using the dry thickness of the fabric preform and the debulked thickness of the fabric preform. And the method includes causing, by the computing system, a stitching machine to apply a through-the-thickness stitch having the stitch tension to the fabric preform.
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Patent Agency Ranking
公开(公告)号：US11846055B2
公开(公告)日：2023-12-19
申请号：US17399815
申请日：2021-08-11
Applicant: The Boeing Company
Inventor： Brian P. Justusson , Joseph D. Schaefer
Abstract: An example method includes determining, by a computing system, a dry thickness of a fabric preform. The method also includes determining, by the computing system, a debulked thickness of the fabric preform using the dry thickness of the fabric preform. In addition, the method includes determining, by the computing system, a stitch tension using the dry thickness of the fabric preform and the debulked thickness of the fabric preform. And the method includes causing, by the computing system, a stitching machine to apply a through-the-thickness stitch having the stitch tension to the fabric preform.
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公开(公告)号：US20230118613A1
公开(公告)日：2023-04-20
申请号：US17501798
申请日：2021-10-14
Applicant: The Boeing Company
Inventor： Joseph D. Schaefer , Brian P. Justusson
IPC: G06F30/20
Abstract: Systems, apparatuses and methods provides for technology that generates a plurality of discrete and finite elements associated with a component, where a number of the plurality of discrete and finite elements corresponds to a size of an estimated process zone. The technology further identifies material input properties of the component, models crack propagation throughout the plurality of discrete and finite elements based on the material input properties and models a release response in the plurality of discrete and finite elements based on the material input properties.
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公开(公告)号：US11379628B2
公开(公告)日：2022-07-05
申请号：US16584119
申请日：2019-09-26
Applicant: The Boeing Company
Inventor： Brian P. Justusson , Joseph D. Schaefer , Bryan W. Lilley
Abstract: A method, apparatus, and system for managing a composite structure. A set of component models is created for a set of components in the composite structure. A set of embedded reinforcement element models is placed within the set of component models for the set of components in the composite structure to form a composite structure model for the composite structure. The set of embedded reinforcement element models is for a set of embedded reinforcements embedded within the set of components in the composite structure. A structural analysis of the composite structure is performed using the composite structure model formed by the set of component models and the set of embedded reinforcement element models, wherein the set of embedded reinforcement element models enables modeling at least one of a deformation or a failure of embedded reinforcements.
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公开(公告)号：US10997330B2
公开(公告)日：2021-05-04
申请号：US16274868
申请日：2019-02-13
Applicant: THE BOEING COMPANY
Inventor： Brian P. Justusson , Joseph D. Schaefer , Matthew Jeffrey Molitor
IPC: G06F30/23 , G06F111/10 , G06F113/26
Abstract: A method includes obtaining failure initiation characteristics of a bonding layer of one or more bonded structures and determining, based on the failure initiation characteristics, a first characteristic dimension for each analysis element of a first portion of a finite element analysis model. The method includes obtaining failure propagation characteristics of the bonding layer and determining, based on the failure propagation characteristics, a second characteristic dimension for each analysis element of a second portion of the model. The method includes assigning a first set of material parameters to analysis elements of the first portion of the model and assigning a second set of material parameters to analysis elements of the second portion of the model. The method includes evaluating failure modes of the one or more bonded structures based on a solution to the model, the first set of material parameters, and the second set of material parameters.
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公开(公告)号：US12165303B2
公开(公告)日：2024-12-10
申请号：US17664463
申请日：2022-05-23
Applicant: The Boeing Company
Inventor： Bryan Lilley , Brittan A. Farmer , Troy Winfree , Yadan Wu , Brian P. Justusson , Jordan A. Severson
Abstract: A computer-based method for evaluating progressive damage in a metal test component includes providing Computed Tomography (CT) image data of the component to a processor and processing the CT image data via the processor, including detecting observable defects in the component. The method also includes characterizing the observable defects into corresponding defect categories, generating a data table of the observable defects and the corresponding defect categories, and embedding a collective set of data from the data table into a finite element model (FEM) of the component to thereby construct a modified FEM of the metal test component. Additionally, the method includes analyzing the modified FEM through an isotropic and/or anisotropic structural model, via the processor, to thereby generate a set of test results. A quality control action is then executed with respect to the metal test component based on the test results.
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