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    FIBER REINFORCED THERMOPLASTIC RESIN MOLDING
    93.
    发明申请
    FIBER REINFORCED THERMOPLASTIC RESIN MOLDING 审中-公开
    纤维增强热塑性树脂模塑

    公开(公告)号：US20110198016A1

    公开(公告)日：2011-08-18

    申请号：US13097474

    申请日：2011-04-29

    申请人： Akira KASUYA ,  Hiroyuki HAMADA ,  Asami NAKAI

    发明人： Akira KASUYA ,  Hiroyuki HAMADA ,  Asami NAKAI

    IPC分类号： B32B7/08 ,  B29C70/02

    CPC分类号： B32B5/26 ,  B29C70/16 ,  B29C70/46 ,  B29K2311/10 ,  B32B5/026 ,  B32B5/06 ,  B32B2038/008 ,  B32B2307/52 ,  Y10T428/24033 ,  Y10T428/24132

    摘要： The present invention provides thermoplastic resin molding fiber that is reinforced with natural fiber. The natural fiber is linen fiber to be twisted into spun yarns, and the spun yarns are pulled parallel in at least one direction and are molded integrally with a thermoplastic resin. The linen fiber is flax yarn (linen) fiber molded into the fiber thermoplastic resin molding by a film-stacking method in which a thermoplastic resin film is melted and compressed while having an equilibrium moisture regain. Consequently, the thermoplastic resin molding reinforced with a plant fiber of the present application poses no environmental problem, has a high strength, and has a uniform physical property.

    摘要翻译： 本发明提供用天然纤维增强的热塑性树脂成型纤维。 天然纤维是将亚麻纤维扭曲成短纤纱，并且将短纤纱沿至少一个方向平行拉伸并与热塑性树脂一体成型。 亚麻纤维是通过膜层叠法将纤维热塑性树脂成型体中的亚麻纤维（亚麻）纤维成型，其中热塑性树脂膜熔融并压缩，同时具有平衡回潮。 因此，用本申请的植物纤维增强的热塑性树脂成型体不会造成环境问题，具有高强度，并且具有均匀的物理性能。

    METHOD FOR MANUFACTURING A CORE COMPOSITE PROVIDED WITH COVER LAYERS ON BOTH SIDES AS WELL AS A CORE COMPOSITE
    94.
    发明申请
    METHOD FOR MANUFACTURING A CORE COMPOSITE PROVIDED WITH COVER LAYERS ON BOTH SIDES AS WELL AS A CORE COMPOSITE 有权
    用于制作核心复合材料的方法，作为核心复合材料，在两面上提供覆盖层

    公开(公告)号：US20110020595A1

    公开(公告)日：2011-01-27

    申请号：US12736303

    申请日：2009-02-20

    申请人： Michael Kolax ,  Wolf-Dietrich Dolzinski

    发明人： Michael Kolax ,  Wolf-Dietrich Dolzinski

    IPC分类号： B32B3/12 ,  B32B7/08

    CPC分类号： B29C70/086 ,  B29D99/0021 ,  B29K2063/00 ,  B29K2707/04 ,  B29L2031/608 ,  B32B3/12 ,  B32B3/28 ,  B32B5/024 ,  B32B5/22 ,  B32B5/26 ,  B32B7/045 ,  B32B7/08 ,  B32B7/14 ,  B32B37/1018 ,  B32B37/146 ,  B32B38/10 ,  B32B2038/008 ,  B32B2260/021 ,  B32B2260/023 ,  B32B2260/046 ,  B32B2262/0269 ,  B32B2262/106 ,  B32B2305/188 ,  B32B2307/50 ,  B32B2307/718 ,  B32B2311/00 ,  B32B2313/04 ,  B32B2605/18 ,  Y02T50/43 ,  Y10T428/24149

    摘要： The invention relates to a method for manufacturing a core composite (1, 20, 26) having a folded honeycomb core (2, 21, 29) provided on both sides with cover layers (3, 4, 22, 23, 27, 28) wherein the folded honeycomb core (2, 21, 29) has a number of drainage-enabling channels (5). First a core filler material (16, 17) is introduced into the folded honeycomb core (2, 21, 29) at least in some areas in order to provide the filler material with sufficient stability for the subsequent sewing process. The cover layers (3, 4, 22, 23, 27, 28) which are not yet impregnated with a curable plastics material are then placed on the folded honeycomb core (2, 21, 29) and stitched to this along the base lines (6 to 8) and/or apex lines (9, 10) at least in some sections by means of a sewing thread (19). The infiltration of the overall structure with a curable plastics material is then carried out followed by hardening by applying pressure and/or temperature. The core filler material (16, 17) can to complete the process be removed again completely from the folded honeycomb core (2, 21, 29) by being dissolved and washed out or by melting and flowing out. Delamination of the cover layers (3, 4, 22, 23, 27, 28) from the folded honeycomb core (2, 21, 29) is prevented by the stitching so that core composites (1, 20, 26) manufactured by the method according to the invention can be used in the primary structure of aircraft.The invention further relates to a core composite (1, 20, 26) manufactured according to the provisions of the method.

    摘要翻译： 本发明涉及一种用于制造具有折叠蜂窝芯（2,21,29）的芯复合材料（2,20,26）的方法，该复合蜂窝芯（2,21,29）在两侧设置有覆盖层（3,4,22,23,27,28） 其中所述折叠的蜂窝芯（2,21,29）具有多个引流通道（5）。 首先，至少在一些区域中，将芯填充材料（16,17）引入到折叠的蜂窝芯（2,21,29）中，以便为随后的缝制过程提供足够的稳定性的填充材料。 然后将尚未浸渍可固化塑料材料的覆盖层（3,4,22,23,27,28）放置在折叠的蜂窝芯（2,21,29）上，并沿着基线（ 6至8）和/或顶线（9,10），至少在一些部分中借助于缝纫线（19）。 然后用可固化塑料材料渗透整个结构，然后施加压力和/或温度进行硬化。 芯填充材料（16,17）可以通过溶解和洗涤或熔化和流出而完成从折叠的蜂窝芯（2,21,29）完全去除的过程。 通过缝合防止从折叠的蜂窝芯（2,21,29）中的覆盖层（3,4,22,23,27,28）的分层，使得通过该方法制造的芯复合材料（1,20,26） 根据本发明可以用于飞机的一级结构。 本发明还涉及根据该方法的规定制造的芯复合体（1,20,26）。

    Stitch-bonded and gathered composites
    97.
    发明授权
    Stitch-bonded and gathered composites 有权
    缝合和收集的复合材料

    公开(公告)号：US06936327B2

    公开(公告)日：2005-08-30

    申请号：US10611287

    申请日：2003-07-01

    申请人： Dimitri Peter Zafiroglu

    发明人： Dimitri Peter Zafiroglu

    IPC分类号： B32B7/02 ,  B32B7/08 ,  D04B21/02 ,  D04B21/14 ,  B32B33/00 ,  D04H11/00 ,  D05B93/00

    CPC分类号： B32B7/12 ,  B32B7/02 ,  B32B7/08 ,  B32B37/144 ,  B32B2038/008 ,  B32B2307/736 ,  D04B21/02 ,  D04B21/165 ,  D10B2503/041 ,  Y10T428/23957 ,  Y10T428/23979 ,  Y10T442/30 ,  Y10T442/3976 ,  Y10T442/60 ,  Y10T442/696

    摘要： Disclosed herein is a composite comprising at least one heat shrinkable adhesive layer stitch-bonded with yarns, which shrink less than the adhesive layer or do not shrink, when the adhesive layer is exposed to heat. The stitch-bonded yarns form loops upstanding from the shrunk adhesive layer and the loops create a textured surface on the composite, and the composite is substantially inelastic after the adhesive layer is shrunk. The composite may further comprise at least one fibrous layer stitch-bonded to the shrinkable adhesive layer, and the fibrous layer is less shrinkable than the adhesive layer or is substantially non-shrinkable.

    摘要翻译： 本文公开了一种复合材料，其包括至少一个与所述粘合剂层暴露于热时与所述粘合剂层收缩或不收缩的纱线缝合的至少一个热收缩粘合剂层。 缝合线形成从收缩的粘合剂层直立的环，并且环在复合材料上形成纹理表面，并且在粘合剂层收缩之后复合材料基本上是无弹性的。 复合材料还可以包括至少一个纤维层，该纤维层缝合到可收缩粘合剂层上，并且纤维层比粘合剂层收缩较少或基本上不可收缩。