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1. 发明申请

US20190240949A1 Composite Sandwich Panels with Over-Crushed Edge Regions 审中-公开
公开(公告)号：US20190240949A1
公开(公告)日：2019-08-08
申请号：US15887839
申请日：2018-02-02
申请人： The Boeing Company
发明人： Jason Turner , Mitchell Zachary Kotlik , Christopher Robert Schwartz , Michael B. Black
IPC分类号： B32B3/12 , B32B3/30 , B32B3/02 , B29C43/02 , B29C43/20
CPC分类号： B32B3/12 , B29C43/02 , B29C43/203 , B29C43/36 , B29C43/40 , B29C70/026 , B29C70/545 , B29C70/685 , B29C70/72 , B29C70/763 , B29C2043/403 , B29C2793/0027 , B29C2793/009 , B29D99/0089 , B29L2031/3076 , B29L2031/608 , B29L2031/72 , B32B3/02 , B32B3/30 , B32B2250/40 , B32B2605/18
摘要： A composite sandwich panel comprises a first composite skin, a second composite skin, a hollow cell core between the first composite skin and the second composite skin, and a first over-crush edge region with a first edge. The first edge has a first thickness at least 40% less than a nominal thickness of the composite sandwich panel. The first over-crush edge region has a length of at least 0.25 inches over which a thickness of the composite sandwich panel decreases.

2. 发明申请

US20190240932A1 TAPE-LAYING DEVICE AND TAPE-LAYING METHOD USING A PIVOTAL CUTTING DEVICE 审中-公开
公开(公告)号：US20190240932A1
公开(公告)日：2019-08-08
申请号：US16328604
申请日：2017-09-06
申请人： DIEFFENBACHER GMBH MASCHINEN-UNDANLAGENBAU
发明人： Matthias GRAF
IPC分类号： B29C70/54 , B29C70/38
CPC分类号： B29C70/545 , B29C70/386
摘要： A tape-laying device includes a material feed unit configured to feed a taps strip material; a cutting device having a cutter adjustable in angle about an axis of rotation (Z) for detaching a tape from the tape strip material; a support table; and a laying device configured to receive and place the detached tape on the support table. The cutting device has a flat transport element, The tape strip material is configured to be fed between the cutter and the flat transport element. The tape strip material is configured to be cut on or over the flat transport element in order to detach the tape from the tape strip material.

3. 发明申请

US20190217559A1 Pultrusion Process and Arrangement for the Continuous Production of Blanks from a Fibre-Plastic Composite Material 审中-公开
公开(公告)号：US20190217559A1
公开(公告)日：2019-07-18
申请号：US16331963
申请日：2017-09-29
申请人： Thyssenkrupp Carbon Components GmbH
发明人： Jens Werner , Andre Kiessling , Jörn Kiele , Till Weinkauf
IPC分类号： B29C70/52 , B29C70/54
CPC分类号： B29C70/523 , B29C70/525 , B29C70/526 , B29C70/545
摘要： The invention relates to a pultrusion process for the continuous production of blanks from a fibre-plastic composite material (23), an arrangement for carrying out a pultrusion process and use of the pultrusion process according to the invention and the arrangement according to the invention. The pultrusion process comprises at least the following process steps: i. providing a strand of unimpregnated fibres (21); ii. feeding the strand of unimpregnated fibres (21) to a vacuum device (5, 5′, 5″), which has at least one vacuum chamber (52, 52′, 52″); iii. generating a negative relative pressure in the at least one vacuum chamber (52, 52′, 52″) of the vacuum device (5, 5′, 5″), whereby air (200) escapes from the strand of unimpregnated fibres (21); iv. removing the almost airless strand of unimpregnated fibres (22) from the vacuum device (5, 5′, 5″) and feeding the almost airless strand of unimpregnated fibres (22) to an injection device (6, 6′), which has at least one injection chamber (61, 61′), wherein the vacuum device (5, 5′, 5″) and the injection device (6, 6′) are connected to one another in an airtight manner, at least with respect to the surroundings; v. injecting matrix material (230) in a flowable state into the at least one injection chamber (61, 61′) of the injection device (6, 6′) and impregnating the strand (2) with the matrix material (230); vi. removing of the blank (23) from the injection device (6, 6′). With the process according to the invention, a homogeneous and complete wetting of the fibres of the strand is advantageously achieved at a high drawing rate. Furthermore, the fibre-plastic composite is not pressed in the process.

4. 发明申请

US20190202147A1 Method for Producing a Structural Element Consisting of a Fibre-Composite Hollow Profile and Load-Introducing Element, and Structural Element 审中-公开
公开(公告)号：US20190202147A1
公开(公告)日：2019-07-04
申请号：US16074088
申请日：2017-01-23
申请人： Leichtbau-Zentrum Sachsen GmbH
发明人： Florian Lenz , Bernhard Witschel , Martin Lepper
IPC分类号： B29C70/52 , B29C70/54
CPC分类号： B29C70/52 , B29C70/545 , B29C70/86 , B29K2101/10 , B29L2023/00
摘要： The invention relates to a method for producing structural elements (14) that comprise a hollow profile (1) made of continuous fibre-reinforced plastics material that comprises a thermosetting matrix material that has a softening temperature that is below the cross-linking temperature, and at least one load-application element (15), and to a structural element (14) produced by the method and comprising a hollow profile (1) made of continuous fibre-reinforced plastics material that comprises a thermosetting matrix material that has a softening temperature that is below the cross-linking temperature, and at least one load-application element (15), the hollow profile (1) and the load-application element (15) being interconnected in a form-fitting manner. The method according to the invention comprises at least the following method steps: a. providing a cut-to-size hollow profile (1) made of plastics material (3) that is reinforced by continuous fibres, on a liner (2), wherein the liner (2) forms the inner lateral surface of the hollow profile (1), and wherein the hollow profile (1) is impregnated by means of heating to a temperature that is equal to or above the softening temperature of the matrix material (9) and below the cross-linking temperature of the matrix material (9); b. removing the liner (2) in the inner region (17) of the hollow profile (1) that is intended for load application; c. arranging a load-application element (15) on the inner region (17) of the hollow profile (1) that is intended for load application; d. consolidating and functionalising the structural element (14) consisting of the hollow profile (1) and the load-application element (15) by means of heating the structural element (14) to a temperature that is equal to or above the cross-linking temperature of the matrix material (9) and applying a radially inwardly acting pressure to the structural element (14), wherein the hollow profile (1) is moulded onto the load-application element (15) in a form-fitting manner.

5. 发明申请

US20190039345A1 RESIN STRUCTURE 审中-公开
公开(公告)号：US20190039345A1
公开(公告)日：2019-02-07
申请号：US16046398
申请日：2018-07-26
申请人： TOYOTA JIDOSHA KABUSHIKI KAISHA
发明人： Yoshihiro IWANO
IPC分类号： B32B5/12 , B32B5/02 , B32B5/24 , B29C70/22 , B29C70/44 , B29C70/54
CPC分类号： B32B5/12 , B29C70/222 , B29C70/443 , B29C70/545 , B29K2105/0836 , B29K2105/089 , B29K2307/04 , B29L2031/3058 , B32B3/14 , B32B5/02 , B32B5/026 , B32B5/142 , B32B5/145 , B32B5/245 , B32B5/28 , B32B2250/44 , B32B2260/023 , B32B2260/046 , B32B2262/106 , B32B2307/40 , B32B2451/00 , B32B2605/08 , B62D29/04 , B62D35/007
摘要： A resin structure includes a first structural portion and a second structural portion. The first structural portion includes a characteristic design surface and structures an end portion at a side of the resin structure at which the characteristic design surface is disposed. An orientation direction of fibers in a first pattern portion of the first structural portion differs from an orientation direction of fibers in a second pattern portion. The second structural portion includes a region disposed at the opposite side of the first structural portion to the side at which the characteristic design surface is disposed. Fibers contained in the second structural portion differ in fiber width from the fibers contained in the first structural portion. A portion of the fibers contained in a region of the second structural portion superposed with the first structural portion are configured to be visible through the resin of the first structural portion.

6. 发明申请

US20180244392A1 THERMOPLASTIC COMPOSITE COMPONENTS FOR COMMERCIAL AIRCRAFT SEATS 审中-公开
公开(公告)号：US20180244392A1
公开(公告)日：2018-08-30
申请号：US15747814
申请日：2016-02-12
申请人： Zodiac Seats US LLC
发明人： Joshua T. Smith , Donald M. Lasell , Jean-marie Daout
IPC分类号： B64D11/06 , B29C70/54 , B29C70/46 , B29C51/26
CPC分类号： B64D11/0648 , B29C51/264 , B29C70/46 , B29C70/545 , B29C2791/002 , B29C2793/0018 , B29C2793/0027 , B29C2793/0081 , B29K2081/04 , B29K2105/0845 , B29K2307/04 , B29L2031/3481 , B29L2031/771
摘要： Described are thermoplastic composite parts (30, 110) made up of resin-based fiber composites for use in aircraft furnishings. The thermoplastic composite parts (30, 110) can be formed into various shapes including bends so as to be suitable for replacing heavier sheet-metal components (100), particularly in aircraft furnishings.

7. 发明申请

US20180229453A1 METHOD OF ASSEMBLY OF COMPOSITE CORE SANDWICH EDGE JOINT 审中-公开
公开(公告)号：US20180229453A1
公开(公告)日：2018-08-16
申请号：US15468793
申请日：2017-03-24
申请人： THE BOEING COMPANY
发明人： Juan Carlos Guzman , Michael Leslie Hand , Douglas McCarville
IPC分类号： B29C70/68 , B29C70/54 , B29C70/30 , B32B3/12 , B64F5/10 , F16B5/02
CPC分类号： B29C70/682 , B29C70/30 , B29C70/545 , B32B3/12 , B64C1/069 , B64F5/10 , F16B5/0291 , F16B5/121 , F16B11/006
摘要： A method for assembling a composite wall assembly edge joint including laying up a first composite face sheet, laying up a first composite buildup pad having a first tapered section onto the first composite face sheet and positioning a composite flute core member, including a tapered first portion with a first inclined surface and a second inclined surface. First inclined surface is positioned onto the first tapered section of the first composite buildup pad and a second portion of the composite flute core member extends from the tapered first portion along first composite face sheet. The method also includes laying up a second composite buildup pad having a second tapered section with the second composite buildup pad spaced apart from the first composite buildup pad and having at least a portion of the second tapered section overlying the second inclined surface of the tapered first portion.

8. 发明申请

US20180207891A1 Systems and Methods for Forming a Composite Part 审中-公开
公开(公告)号：US20180207891A1
公开(公告)日：2018-07-26
申请号：US15412674
申请日：2017-01-23
申请人： The Boeing Company
发明人： Chelsey Elizibeth Henry , Jeremy Robert Larkin , Kari P. Larkin , Hong Hue Tat , Yuan-Jye Wu
IPC分类号： B29C70/54 , B29C70/16 , B29C70/44
CPC分类号： B29C70/541 , B29C70/16 , B29C70/386 , B29C70/44 , B29C70/545 , B29C70/546 , B29C2793/0081 , B29K2045/00 , B29K2063/00 , B29K2105/089 , B29K2105/256
摘要： In an example, a method for forming a composite part includes, based on a part specification, cutting layers of material in a sequence and positioning the layers to form a stack. For each layer, after positioning the layer and before cutting a next layer in the sequence, the method includes (i) scanning along a length of the layer to determine an image, (ii) determining, based on the image, at least two edges of the layer, (iii) determining, based on the edges, a measured width at locations along the length of the layer, (iv) comparing the measured width at each location to a target width at the location, (v) deciding, based on the comparison, whether to adjust the production process, and (vi) if the decision is to adjust the production process, then adjusting the production process based on the comparison. The part specification specifies the target width at each location.

9. 发明申请

US20180156310A1 LINK BELT AND METHOD FOR PRODUCING SAME 审中-公开
公开(公告)号：US20180156310A1
公开(公告)日：2018-06-07
申请号：US15826094
申请日：2017-11-29
申请人： Fenner U.S., Inc.
发明人： Eric S. Mosser , Tyson Gabler
IPC分类号： F16G1/24 , B65G15/34 , B29C70/30 , B29C70/54
CPC分类号： F16G1/24 , B29C70/06 , B29C70/30 , B29C70/545 , B29C2793/0009 , B29L2031/7092 , B65G15/34 , B65G17/08 , B65G17/40 , B65G2201/02 , B65G2812/02198
摘要： A link belt is provided wherein the link belt is formed of a plurality of links forming a series of links in successive overlapping relation. The link belt includes a first end having a first connector and a second end having a second connector so that the first connector is connected with the second connector to form a continuous loop of link belt. The link belt is formed by applying a lateral force against the assembled link belt while the link belt is under an axial tension to stretch the belt. After the step of stretching the belt, the first connector is connected with the second connector to form a continuous belt.

10. 发明授权

US09925680B2 System and method of post-cure processing of composite core 有权
公开(公告)号：US09925680B2
公开(公告)日：2018-03-27
申请号：US13914737
申请日：2013-06-11
申请人： Bell Helicopter Textron Inc.
发明人： Phillip A. Kendrick , Levi H. Armstrong
IPC分类号： B29C70/54 , B32B3/12 , B26D1/157 , B26D7/01 , B29C69/00 , B29D99/00 , B29C53/60 , B26D1/10 , B26D3/16 , B26D1/08 , B29C65/00 , B32B37/14 , B29C70/30
CPC分类号： B26D1/157 , B26D1/08 , B26D1/10 , B26D3/167 , B26D7/01 , B29C53/60 , B29C66/543 , B29C69/001 , B29C70/30 , B29C70/545 , B29D99/0089 , B32B3/12 , B32B37/146 , Y10T83/04 , Y10T83/0405 , Y10T83/0524 , Y10T156/1026 , Y10T156/1059 , Y10T156/1066 , Y10T156/1079 , Y10T156/13 , Y10T156/1357
摘要： A method of cutting a wafer of composite core from a bulk composite core includes stabilizing the bulk composite core with a fixture, the bulk composite core having a plurality of tube members. The method also includes cutting through each of the tube members to create the wafer while the bulk composite core is stabilized by the fixture.

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