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公开(公告)号：US10232550B2
公开(公告)日：2019-03-19
申请号：US14841470
申请日：2015-08-31
Applicant: The Boeing Company
Inventor： Nick S. Evans , Faraón Torres , Ryan G. Ziegler , Samuel F. Harrison , Ciro J. Grijalva, III , Hayden S. Osborn
IPC: B29C64/20 , B29C64/165 , B29C70/38 , B29C70/52 , B29B15/12 , B29C64/106 , B29C64/386 , B33Y30/00
Abstract: A system for additively manufacturing a composite part comprises a delivery assembly, a feed mechanism, and a source of curing energy. The delivery assembly comprises a delivery guide movable relative to a surface and is configured to deposit a continuous flexible line along a print path. The delivery assembly further comprises a first inlet, configured to receive a non-resin component, and a second inlet, configured to receive a photopolymer resin. The delivery assembly applies the photopolymer resin to the non-resin component. The feed mechanism pushes the continuous flexible line out of the delivery guide. The source of the curing energy delivers the curing energy to a portion of the continuous flexible line after it exits the delivery guide.
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公开(公告)号：US10189242B2
公开(公告)日：2019-01-29
申请号：US14995620
申请日：2016-01-14
Applicant: The Boeing Company
Inventor： Nick S. Evans , Faraón Torres , Ryan G. Ziegler , Samuel F. Harrison , Ciro J. Grijalva, III , Hayden S. Osborn
IPC: B05D1/34 , B33Y70/00 , B29C69/00 , B29C70/28 , B05D1/26 , B05D3/06 , B05D3/12 , B29C35/16 , B29C70/16 , B29C70/38 , B29C70/54 , C09D5/00 , B29B11/00 , B29B11/16 , C09D201/00 , B29C47/00 , B29C64/106 , B29C64/135 , B29C64/129 , B29C64/386 , B29C64/20 , B29C64/00 , B29C64/40 , B29C64/165 , B29K105/00 , B33Y10/00 , B29L31/30 , B29L31/00 , B33Y30/00 , B33Y40/00 , B29K63/00 , B29K105/08 , B29K105/10 , B33Y50/02 , B29K101/10 , B29K105/12 , B29C35/08 , B29K105/06 , B29C64/25
Abstract: A method of additively manufacturing a composite part is disclosed. The method comprises depositing a segment of a continuous flexible line along a print path. The continuous flexible line comprises a non-resin component and a thermosetting resin component that is not fully cured. The method further comprises, while advancing the continuous flexible line toward the print path, delivering a predetermined or actively determined amount of curing energy at least to a portion of the segment of the continuous flexible line at a controlled rate after the segment of the continuous flexible line is deposited along the print path to at least partially cure at least the portion of the segment of the continuous flexible line.
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公开(公告)号：US10183478B2
公开(公告)日：2019-01-22
申请号：US14931692
申请日：2015-11-03
Applicant: The Boeing Company
Inventor： Nick S. Evans , Faraón Torres , Ryan G. Ziegler , Samuel F. Harrison , Ciro J. Grijalva, III , Hayden S. Osborn
IPC: B29C67/00 , B33Y70/00 , B29C69/00 , B29C70/28 , B05D1/26 , B05D1/34 , B05D3/06 , B05D3/12 , B29C35/16 , B29C70/16 , B29C70/38 , B29C70/54 , C09D5/00 , B29B11/00 , B29B11/16 , C09D201/00 , B29C47/00 , B29C64/106 , B29K105/00 , B33Y10/00 , B29L31/30 , B29L31/00 , B33Y30/00 , B33Y40/00 , B29K63/00 , B29K105/08 , B29K105/10 , B33Y50/02 , B29K101/10 , B29K105/12 , B29C35/08 , B29K105/06 , B29C64/135 , B29C64/129 , B29C64/25
Abstract: A method of additively manufacturing a composite part is disclosed. The method comprises depositing, via a delivery guide, a segment of a continuous flexible line along a print path. The continuous flexible line comprises a non-resin component and a thermosetting-epoxy-resin component that is partially cured. The method also comprises maintaining the thermosetting-epoxy-resin component of at least the continuous flexible line being advanced toward the print path via the delivery guide below a threshold temperature. The method further comprises delivering a predetermined or actively determined amount of curing energy to the segment of the continuous flexible line at a controlled rate while advancing the continuous flexible line toward the print path to at least partially cure the segment of the continuous flexible line.
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公开(公告)号：US20170284434A1
公开(公告)日：2017-10-05
申请号：US15090146
申请日：2016-04-04
Applicant: The Boeing Company
Inventor： Karina R. Lopez , Hayden S. Osborn
CPC classification number: F16B5/01 , B32B7/08 , B32B2250/40 , B32B2605/18 , F16B5/02
Abstract: A threaded adjustable-height insert may be installed in a bore of a sandwich panel, such that the insert may be configured to transfer a load to the sandwich panel. The threaded adjustable-height insert may include a first insert part and a second insert part that may be selectively operatively positioned with respect to each other. The overall height of the threaded adjustable-height insert may be adjusted by longitudinally sliding the second insert part with respect to the first insert part and rotating the second insert part with respect to the first insert part. Presently disclosed threaded adjustable-height inserts may be configured for flush installation in a sandwich panel. Methods of installing such threaded adjustable-height inserts and adjusting the height of the same are also disclosed.
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公开(公告)号：US20170028634A1
公开(公告)日：2017-02-02
申请号：US14931635
申请日：2015-11-03
Applicant: The Boeing Company
Inventor： Nick S. Evans , Faraón Torres , Ryan G. Ziegler , Samuel F. Harrison , Ciro J. Grijalva, III , Hayden S. Osborn
CPC classification number: B33Y70/00 , B05D1/265 , B05D1/34 , B05D3/06 , B05D3/067 , B05D3/068 , B05D3/12 , B29B11/00 , B29B11/16 , B29C35/0805 , B29C35/16 , B29C47/0002 , B29C64/00 , B29C64/106 , B29C64/129 , B29C64/135 , B29C64/165 , B29C64/20 , B29C64/25 , B29C64/386 , B29C64/40 , B29C69/001 , B29C70/16 , B29C70/28 , B29C70/38 , B29C70/545 , B29C2035/0822 , B29C2035/0827 , B29C2035/0833 , B29C2035/0838 , B29C2035/0844 , B29K2063/00 , B29K2101/10 , B29K2105/0058 , B29K2105/06 , B29K2105/0872 , B29K2105/10 , B29K2105/101 , B29K2105/12 , B29K2105/25 , B29K2105/253 , B29K2995/005 , B29L2031/00 , B29L2031/3076 , B33Y10/00 , B33Y30/00 , B33Y40/00 , B33Y50/02 , C09D5/00 , C09D201/00
Abstract: A method (300) of additively manufacturing a composite part (102) is disclosed. The method (300) comprises pushing a continuous flexible line (106) through a delivery guide (112). The continuous flexible line (106) comprises a non-resin component (108) and a thermosetting-epoxy-resin component (110) that is partially cured. The method (300) also comprises depositing, via the delivery guide (112), a segment (120) of the continuous flexible line (106) along a print path (122). The method (300) further comprises maintaining the thermosetting-epoxy-resin component (110) of at least the continuous flexible line (106) being pushed through the delivery guide (112) below a threshold temperature prior to depositing the segment (120) of the continuous flexible line (106) along the print path (120).
Abstract translation: 公开了一种叠加制造复合部件（102）的方法（300）。 方法（300）包括通过输送引导件（112）推动连续的柔性管线（106）。 连续柔性线（106）包括部分固化的非树脂组分（108）和热固性环氧树脂组分（110）。 方法（300）还包括经由输送引导件（112）沿着打印路径（122）沉积连续柔性管线（106）的段（120）。 所述方法（300）还包括将至少所述连续柔性管线（106）的所述热固性环氧树脂组分（110）保持在阈值温度之前被推动通过所述输送引导件（112），然后将所述段（120） 所述连续柔性线（106）沿着所述打印路径（120）。
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Patent Agency Ranking
公开(公告)号：US20170028434A1
公开(公告)日：2017-02-02
申请号：US14841504
申请日：2015-08-31
Applicant: The Boeing Company
Inventor： Nick S. Evans , Faraón Torres , Ryan G. Ziegler , Samuel F. Harrison , Ciro J. Grijalva, III , Hayden S. Osborn
CPC classification number: B33Y70/00 , B05D1/265 , B05D1/34 , B05D3/06 , B05D3/067 , B05D3/068 , B05D3/12 , B29B11/00 , B29B11/16 , B29C35/0805 , B29C35/16 , B29C47/0002 , B29C64/00 , B29C64/106 , B29C64/129 , B29C64/135 , B29C64/165 , B29C64/20 , B29C64/25 , B29C64/386 , B29C64/40 , B29C69/001 , B29C70/16 , B29C70/28 , B29C70/38 , B29C70/545 , B29C2035/0822 , B29C2035/0827 , B29C2035/0833 , B29C2035/0838 , B29C2035/0844 , B29K2063/00 , B29K2101/10 , B29K2105/0058 , B29K2105/06 , B29K2105/0872 , B29K2105/10 , B29K2105/101 , B29K2105/12 , B29K2105/25 , B29K2105/253 , B29K2995/005 , B29L2031/00 , B29L2031/3076 , B33Y10/00 , B33Y30/00 , B33Y40/00 , B33Y50/02 , C09D5/00 , C09D201/00
Abstract: A method (300) of additively manufacturing a composite part (102) comprises depositing a segment (120) of a continuous flexible line (106) along a print path (106). The continuous flexible line (106) comprises a non-resin component (108) and further comprises a photopolymer-resin component (110) that is uncured. The method (300) further comprises delivering a predetermined or actively determined amount of curing energy (118) at least to a portion (124) of the segment (120) of the continuous flexible line (106) at a controlled rate while advancing the continuous flexible line (106) toward the print path (122) and after the segment (120) of the continuous flexible line (106) is deposited along the print path (122) to at least partially cure at least the portion (124) of the segment (120) of the continuous flexible line (106).
Abstract translation: 叠加制造复合部件（102）的方法（300）包括沿着打印路径（106）沉积连续柔性线（106）的段（120）。 连续柔性线（106）包括非树脂组分（108），并且还包含未固化的光聚合物树脂组分（110）。 所述方法（300）还包括以可控制的速率将至少预定或主动确定量的固化能量（118）输送到连续柔性管线（106）的段（120）的一部分（124） 柔性线（106）朝向打印路径（122）并且在连续柔性线（106）的段（120）之后沿着打印路径（122）沉积以至少部分地固化至少部分（124）的部分 所述连续柔性管线（106）的段（120）。
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公开(公告)号：US11241834B2
公开(公告)日：2022-02-08
申请号：US16843099
申请日：2020-04-08
Applicant: The Boeing Company
Inventor： Robert L. Mann, Jr. , Hayden S. Osborn , Alexander J. Coco
IPC: B29C64/35 , B29C64/379 , B29C64/393 , B29C64/371 , B33Y40/20 , B29C64/153 , B33Y10/00 , B33Y30/00 , B33Y50/02 , B29C64/245 , B29C64/188
Abstract: A system for removing residual powder from a three-dimensional (3D)-printed component integrally constructed with a build plate during an additive manufacturing (AM) process includes an end-effector, an enclosure, one or more transducers, and an electronic control unit (ECU). The end-effector includes a base surrounded by a perimeter flange, and includes a through-opening that receives the build plate. A perimeter clamp attaches and seal the enclosure to a perimeter flange of the end-effector such that the enclosure, the base, and the build plate collectively form a powder containment cavity. The transducers vibrate at a predetermined frequency or range thereof. The ECU transmits a vibration control signal to the transducers during a post-processing stage of the AM process to loosen and remove the residual powder from the component and collect the loosened powder within the powder containment cavity.
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公开(公告)号：US20210316508A1
公开(公告)日：2021-10-14
申请号：US16843099
申请日：2020-04-08
Applicant: The Boeing Company
Inventor： Robert L. Mann, JR. , Hayden S. Osborn , Alexander J. Coco
IPC: B29C64/35 , B29C64/245 , B29C64/379 , B29C64/188 , B29C64/393 , B29C64/371
Abstract: A system for removing residual powder from a three-dimensional (3D)-printed component integrally constructed with a build plate during an additive manufacturing (AM) process includes an end-effector, an enclosure, one or more transducers, and an electronic control unit (ECU). The end-effector includes a base surrounded by a perimeter flange, and includes a through-opening that receives the build plate. A perimeter clamp attaches and seal the enclosure to a perimeter flange of the end-effector such that the enclosure, the base, and the build plate collectively form a powder containment cavity. The transducers vibrate at a predetermined frequency or range thereof. The ECU transmits a vibration control signal to the transducers during a post-processing stage of the AM process to loosen and remove the residual powder from the component and collect the loosened powder within the powder containment cavity.
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公开(公告)号：US20200061917A1
公开(公告)日：2020-02-27
申请号：US16112929
申请日：2018-08-27
Applicant: THE BOEING COMPANY
Inventor： Hayden S. Osborn , Michael T. Hilliard , Robert L. Kearney
IPC: B29C64/268 , H01S3/00 , B33Y30/00
Abstract: A laser assembly for additive manufacturing which includes a first laser beam aligned in a first direction and a first partial reflecting fixed mirror positioned aligned with the first direction which reflects a first portion of the first laser beam in a second direction and an exponentially reduced remaining second portion of the first laser beam passes through the first partial reflecting fixed mirror in the first direction. The laser beam assembly further includes a first oscillating mirror positioned aligned with the second direction of the first portion of the first laser beam wherein the first portion of the first laser beam is refracted by the first oscillating mirror in a third direction.
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公开(公告)号：US10350878B2
公开(公告)日：2019-07-16
申请号：US15063347
申请日：2016-03-07
Applicant: The Boeing Company
Inventor： Nick S. Evans , Faraòn Torres , Ryan G. Ziegler , Samuel F. Harrison , Ciro J. Grijalva, III , Hayden S. Osborn
IPC: B29C64/20 , B33Y70/00 , B29C69/00 , B29C70/28 , B29C48/02 , B05D1/26 , B05D1/34 , B05D3/06 , B05D3/12 , B29C35/16 , B29C70/16 , B29C70/38 , B29C70/54 , C09D5/00 , B29B11/00 , B29B11/16 , C09D201/00 , B29C64/106 , B29C64/135 , B29C64/129 , B29C64/386 , B29C64/00 , B29C64/40 , B29C64/165 , B29K105/00 , B33Y10/00 , B29L31/30 , B29L31/00 , B33Y30/00 , B33Y40/00 , B29K63/00 , B29K105/08 , B29K105/10 , B33Y50/02 , B29K101/10 , B29K105/12 , B29C35/08 , B29K105/06 , B29C64/25
Abstract: A system for additively manufacturing a composite part comprises a delivery guide, movable relative to a surface. The delivery guide is configured to deposit at least a segment of a continuous flexible line along a print path. The continuous flexible line comprises a non-resin component and a thermosetting-resin component. The thermosetting-resin component comprises a first part and a second part. The non-resin component comprises a first element and a second element. The system further comprises a first resin-part applicator, configured to apply the first part to the first element, and a second resin-part applicator, configured to apply the second part to the second element. The system also comprises a feed mechanism, configured to pull the first element through the first resin-part applicator, to pull the second element through the second resin-part applicator, and to push the continuous flexible line out of the delivery guide.
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