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公开(公告)号：US20170266753A1
公开(公告)日：2017-09-21
申请号：US15442785
申请日：2017-02-27
Applicant: Goodrich Corporation
Inventor： Samual Steven Riczo Schomer , Alan J. Fahrner , Kurt M. Tauscher , Andrew Taylor , James R. Hunter , David L. Brittingham
CPC classification number: B23K20/10 , B29C65/04 , B29C65/08 , B29C65/1403 , B29C65/1467 , B29C65/62 , B29C66/1122 , B29C66/232 , B29C66/244 , B29C66/438 , B29C66/71 , B29C66/7292 , B29C66/81417 , B29C66/81427 , B29C66/8322 , B29L2022/02 , B29L2024/006 , B29L2031/3076 , B64D15/166 , B64F5/10 , B29K2021/00
Abstract: A method of manufacturing a de-icer assembly includes disposing a first welded-material layer and a second welded-material layer beneath a horn of a horn-based welding system, controlling the horn to move along a welded-portion pattern configured to weld the first welded-material layer to the second welded-material layer in the pattern of the welded-portion pattern such that inflatable portions are formed within the welded-portion pattern formed in the de-icer assembly between non-welded sections of the first welded-material layer and the second welded-material layer, and applying high-frequency energy to the first welded-material layer and a second welded-material layer using the horn such that the first welded-material layer and the second welded-material layer are welded together at areas in the shape of the welded-portion pattern to form a welded de-icer assembly.
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公开(公告)号：US20160340020A1
公开(公告)日：2016-11-24
申请号：US15149966
申请日：2016-05-09
Applicant: Goodrich Corporation
Inventor： George Owens , Kevin E. Roach , Kurt M. Tauscher
CPC classification number: B64C1/18 , B64C1/40 , B64C2001/0072 , B64D13/08 , F24D13/024 , Y02B30/26
Abstract: An aircraft heated floor panel includes a first support layer, a second support layer, and a heating layer located between the first support layer and the second support layer. An aircraft floor panel includes a floor panel body and a removal feature that provides a mechanism for the aircraft floor panel to be removed from an attached aircraft structure.
Abstract translation: 飞机加热地板镶板包括第一支撑层，第二支撑层和位于第一支撑层和第二支撑层之间的加热层。 飞机地板镶板包括地板面板主体和移除特征，其提供用于飞行器地板面板从附接的飞行器结构中移除的机构。
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公开(公告)号：US20200298983A1
公开(公告)日：2020-09-24
申请号：US16360988
申请日：2019-03-21
Applicant: Goodrich Corporation
Inventor： Kurt M. Tauscher , Rick Pudoka , Joseph B. Honaker
IPC: B64D15/00
Abstract: An assembly for connecting an air connection fitting to a pneumatic de-icer of an aircraft includes a molded base and a machined insert. The molded base includes a flexible material and forms a sealing interface with a portion of the pneumatic de-icer. The machined insert is set into the molded base and includes a radially inward threaded surface that forms an opening extending axially through the machined insert. The radially inward threaded surface is configured to mate with a terminal end of the air connection fitting.
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公开(公告)号：US20190185168A1
公开(公告)日：2019-06-20
申请号：US15845428
申请日：2017-12-18
Applicant: Goodrich Corporation
Inventor： James R. Hunter , Galdemir Cezar Botura , Samual Steven Riczo Schomer , Alan J. Fahrner , Kurt M. Tauscher
CPC classification number: B64D15/166 , B32B7/08 , B32B2250/02 , B32B2605/18
Abstract: A de-icing assembly for a surface of an aircraft includes a carcass with a first layer and a second layer, a plurality of seams sewn into the carcass, and a bonded region. The plurality of seams join the first and second layers of the carcass together. Each of the plurality of seams comprises two or more stitchlines. The bonded region is disposed between the two or more stitchlines and seals a portion of the first layer of the carcass to a portion of the second layer of the carcass.
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Patent Agency Ranking
公开(公告)号：US11104443B2
公开(公告)日：2021-08-31
申请号：US16360988
申请日：2019-03-21
Applicant: Goodrich Corporation
Inventor： Kurt M. Tauscher , Rick Pudoka , Joseph B. Honaker
IPC: B64D15/00
Abstract: An assembly for connecting an air connection fitting to a pneumatic de-icer of an aircraft includes a molded base and a machined insert. The molded base includes a flexible material and forms a sealing interface with a portion of the pneumatic de-icer. The machined insert is set into the molded base and includes a radially inward threaded surface that forms an opening extending axially through the machined insert. The radially inward threaded surface is configured to mate with a terminal end of the air connection fitting.
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公开(公告)号：US10780983B2
公开(公告)日：2020-09-22
申请号：US15845428
申请日：2017-12-18
Applicant: Goodrich Corporation
Inventor： James R. Hunter , Galdemir Cezar Botura , Samual Steven Riczo Schomer , Alan J. Fahrner , Kurt M. Tauscher
Abstract: A de-icing assembly for a surface of an aircraft includes a carcass with a first layer and a second layer, a plurality of seams sewn into the carcass, and a bonded region. The plurality of seams join the first and second layers of the carcass together. Each of the plurality of seams comprises two or more stitchlines. The bonded region is disposed between the two or more stitchlines and seals a portion of the first layer of the carcass to a portion of the second layer of the carcass.
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公开(公告)号：US10279886B2
公开(公告)日：2019-05-07
申请号：US15149966
申请日：2016-05-09
Applicant: Goodrich Corporation
Inventor： George Owens , Kevin E. Roach , Kurt M. Tauscher
Abstract: An aircraft heated floor panel includes a first support layer, a second support layer, and a heating layer located between the first support layer and the second support layer. An aircraft floor panel includes a floor panel body and a removal feature that provides a mechanism for the aircraft floor panel to be removed from an attached aircraft structure.
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公开(公告)号：US20170273148A1
公开(公告)日：2017-09-21
申请号：US15442752
申请日：2017-02-27
Applicant: Goodrich Corporation
Inventor： Samual Steven Riczo Schomer , Alan J. Fahrner , Kurt M. Tauscher , Andrew Taylor , James R. Hunter , David L. Brittingham
CPC classification number: H05B6/62 , B29C65/04 , B29C65/08 , B29C65/1403 , B29C65/1467 , B29C65/62 , B29C66/1122 , B29C66/244 , B29C66/438 , B29C66/439 , B29C66/81417 , B29C66/81427 , B29C66/8322 , B29L2022/02 , B29L2024/006 , B29L2031/3076 , B64D15/166 , B64D2033/0233 , B64F5/10
Abstract: A die-welding system for a de-icer assembly includes a die, a die base, a high energy source, and a de-icer assembly. The de-icer assembly includes a first welded-material layer and a second welded-material layer. At least one of the die and the die base includes a welded-portion pattern thereon configured to weld the first welded-material layer to the second welded-material layer in the pattern of the welded-portion pattern such that inflatable portions are formed within the welded-portion pattern formed in the de-icer assembly between non-welded sections of the first welded-material layer and the second welded-material layer.
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公开(公告)号：US20170266869A1
公开(公告)日：2017-09-21
申请号：US15442772
申请日：2017-02-27
Applicant: Goodrich Corporation
Inventor： Samuel Steven Riczo Schomer , Alan J. Fahrner , Kurt M. Tauscher , Andrew Taylor , James R. Hunter , David L. Brittingham
CPC classification number: B29C65/04 , B29C65/08 , B29C65/1403 , B29C65/1467 , B29C65/62 , B29C66/1122 , B29C66/244 , B29C66/438 , B29C66/439 , B29C66/71 , B29C66/7392 , B29C66/81417 , B29C66/81427 , B29C66/8322 , B29L2022/02 , B29L2024/006 , B29L2031/3076 , B64D15/166 , B64D2033/0233 , B29K2021/00 , B29K2011/00 , B29K2021/006 , B29K2007/00 , B29K2075/00
Abstract: A method of manufacturing a de-icer assembly includes positioning a first welded-material layer and a second welded-material layer between a die and a die base of a die-based welding system, wherein at least one of the die and the die base includes a welded-portion pattern configured to weld the first welded-material layer to the second welded-material layer in the pattern such that inflatable portions are formed within the welded-portion pattern formed in the de-icer assembly between non-welded sections of the first welded-material layer and the second welded-material layer, pressing the first welded-material layer and the second welded-material layer together between the die and die base, and applying high energy to the die-based welding system using a high energy source such that the first welded-material layer and the second welded-material layer are welded together at the areas in the shape of the welded-portion pattern to form a welded de-icer assembly.
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