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15 条记录 (耗时 0.022 秒)

    UV-IR COMBINATION CURING SYSTEM AND METHOD OF USE FOR WIND BLADE MANUFACTURE AND REPAIR
    4.
    发明申请
    UV-IR COMBINATION CURING SYSTEM AND METHOD OF USE FOR WIND BLADE MANUFACTURE AND REPAIR 审中-公开
    UV-IR组合固化系统及风叶制造与维修方法

    公开(公告)号：US20120138223A1

    公开(公告)日：2012-06-07

    申请号：US13248144

    申请日：2011-09-29

    申请人： Xiaomei Fang ,  Thomas Miebach ,  David Simon ,  Jordan Philip Seeger

    发明人： Xiaomei Fang ,  Thomas Miebach ,  David Simon ,  Jordan Philip Seeger

    IPC分类号： B32B37/06 ,  B32B37/14

    CPC分类号： F03D1/0675 ,  B29C35/0805 ,  B29C70/28 ,  B29C73/34 ,  B29C2035/0822 ,  B29C2035/0827 ,  B29L2031/08 ,  Y02E10/721

    摘要： A UV-IR combination curing system and method for manufacture and repair of composite parts, such as for use in wind blade manufacture and repair. The system and method utilize UV and IR dual radiation sources to cure glass fiber reinforced laminates containing a photo initiator. The UV and IR dual radiation sources can be configured as discrete stand-alone UV and IR lamps used in a side by side configuration, a plurality of UV lamps with thermal IR radiation, a combined UV/IR lamp, or other forms of light sources providing both UV and IR radiation. To achieve high glass transition and complete curing of thick laminates, the IR radiation source is initially turned on to heat the laminate to close to 40° C-100° C. before the UV radiation source is turned on. The IR radiation source can be turned off after UV radiation source is activated.

    摘要翻译： UV-IR组合固化系统以及用于制造和修复复合材料部件的方法，例如用于风叶片的制造和修理。 该系统和方法利用UV和IR双重辐射源来固化含有光引发剂的玻璃纤维增​​强层压板。 UV和IR双重辐射源可以配置为并排配置使用的独立UV和IR灯，具有热IR辐射的多个UV灯，组合的UV / IR灯或其他形式的光源 提供UV和IR辐射。 为了实现高的玻璃化转变和厚层压板的完全固化，在紫外线辐射源开启之前，首先打开IR辐射源以将层压板加热至接近40℃-100℃。 紫外线辐射源激活后，红外辐射源可以关闭。

    MULTI-RESIN COMPOSITE ARTICLES AND SYSTEM AND METHOD OF MANUFACTURE
    5.
    发明申请
    MULTI-RESIN COMPOSITE ARTICLES AND SYSTEM AND METHOD OF MANUFACTURE 有权
    多树脂复合材料及其制造方法及制造方法

    公开(公告)号：US20080305340A1

    公开(公告)日：2008-12-11

    申请号：US11759356

    申请日：2007-06-07

    申请人： Xiaomei Fang ,  Wendy Wen-Ling Lin ,  Ming Xie ,  Scott Roger Finn

    发明人： Xiaomei Fang ,  Wendy Wen-Ling Lin ,  Ming Xie ,  Scott Roger Finn

    IPC分类号： B29C70/48 ,  B29C70/06 ,  B32B5/28 ,  F04D29/40

    CPC分类号： F04D29/023 ,  B29C70/443 ,  B29K2063/00 ,  B29K2995/0089 ,  F04D29/526 ,  F05D2300/43 ,  F05D2300/603 ,  F05D2300/6031 ,  Y10T428/31504

    摘要： A method for manufacturing a multi-resin composite article is provided. The method comprises providing at least one fiber preform in a mold; injecting a plurality of resins into the at least one fiber preform at a plurality of locations on the at least one fiber preform; and forming at least one transition region along a mutual contact surface between the resins. Each of the at least one transition regions is defined by a gradual transition in composition from one of the resins to another of the resins. A multi-resin composite article is also provided. The article comprises: at least one fiber preform; a plurality of resins, wherein the at least one fiber preform is infused with the resins; and at least one transition region extending along a mutual contact surface between respective ones of the resins. A system for manufacturing such a multi-resin composite article is also provided.

    摘要翻译： 提供了一种多树脂复合制品的制造方法。 该方法包括在模具中提供至少一个纤维预制件; 在所述至少一个纤维预制件上的多个位置处将多个树脂注入到所述至少一个纤维预制件中; 以及沿树脂之间的相互接触表面形成至少一个过渡区域。 至少一个过渡区域中的每一个由组合物中的一种树脂到另一种树脂的逐渐过渡来限定。 还提供了多树脂复合制品。 该制品包括：至少一个纤维预制件; 多个树脂，其中所述至少一个纤维预制体被所述树脂注入; 以及沿着相应的树脂之间的相互接触表面延伸的至少一个过渡区域。 还提供了一种用于制造这种多树脂复合制品的系统。

    LAMINATE THERMAL INSULATION BLANKET FOR AIRCRAFT APPLICATIONS AND PROCESS THEREFOR
    6.
    发明申请
    LAMINATE THERMAL INSULATION BLANKET FOR AIRCRAFT APPLICATIONS AND PROCESS THEREFOR 审中-公开
    用于飞机应用的层压热绝缘棉和其过程

    公开(公告)号：US20120308369A1

    公开(公告)日：2012-12-06

    申请号：US13118867

    申请日：2011-05-31

    申请人： Mahendra Maheshwari ,  Xiaomei Fang

    发明人： Mahendra Maheshwari ,  Xiaomei Fang

    IPC分类号： F04D29/40 ,  B32B37/06 ,  B32B3/00

    CPC分类号： B64D33/02 ,  B64D2033/0206 ,  Y10T428/233

    摘要： A thermal insulation blanket for an aircraft engine, and processes for producing the thermal insulation blanket to have low thermal conductivity and high temperature capability. The thermal insulation blanket has a layered construction that includes an aerogel insulation material, a composite layer disposed at a first surface of the aerogel insulation material, and a backing layer disposed at an opposite surface of the aerogel insulation material so that the aerogel insulation material is encapsulated between the composite and backing layers. The composite layer contains a resin matrix material reinforced with a fiber reinforcement material.

    摘要翻译： 用于飞机发动机的隔热毯，以及用于制造隔热毯以具有低导热性和高温能力的方法。 隔热毯具有分层结构，其包括气凝胶绝缘材料，设置在气凝胶绝缘材料的第一表面的复合层和设置在气凝胶绝缘材料的相对表面处的背衬层，使得气凝胶绝缘材料为 封装在复合层和背衬层之间。 复合层包含用纤维增强材料增强的树脂基质材料。

    CURED COMPOSITE COMPOSITION
    7.
    发明申请
    CURED COMPOSITE COMPOSITION 审中-公开
    固化复合组合物

    公开(公告)号：US20100249277A1

    公开(公告)日：2010-09-30

    申请号：US12414707

    申请日：2009-03-31

    申请人： Xiaomei Fang ,  Wendy Wen-Ling Lin ,  Amitabh Bansal ,  Yosang Yoon

    发明人： Xiaomei Fang ,  Wendy Wen-Ling Lin ,  Amitabh Bansal ,  Yosang Yoon

    IPC分类号： C08L63/00

    CPC分类号： C08J5/24 ,  B82Y30/00 ,  C08J2363/00 ,  C08L53/00 ,  C08L63/00 ,  C08L2666/04

    摘要： In one aspect, the present invention provides a cured composite composition comprising (a) a fiber component; and (b) an organic composition. The organic composition comprises a cured epoxy continuous phase and a nanoparticulate thermoplastic block copolymeric discontinuous phase. The nanoparticulate thermoplastic block copolymeric discontinuous phase has a domain size distribution in a range from about 1 nanometer to about 500 nanometers, and the discontinuous phase is substantially uniformly distributed throughout the cured composite composition. Articles and method of making the cured composite compositions are also provided.

    摘要翻译： 一方面，本发明提供一种固化的复合组合物，其包含（a）纤维组分; 和（b）有机组合物。 有机组合物包含固化的环氧连续相和纳米颗粒热塑性嵌段共聚物不连续相。 纳米颗粒热塑性嵌段共聚物不连续相具有在约1纳米至约500纳米范围内的畴尺寸分布，并且不连续相基本均匀地分布在整个固化的复合组合物中。 还提供了制备固化的复合组合物的制品和方法。

    UV Curing System and Method For Wind Blade Manufacture And Repair
    8.
    发明申请
    UV Curing System and Method For Wind Blade Manufacture And Repair 审中-公开
    紫外线固化系统及风叶制造与维修方法

    公开(公告)号：US20140077420A1

    公开(公告)日：2014-03-20

    申请号：US13619154

    申请日：2012-09-14

    申请人： Xiaomei Fang ,  Jordan P. Seeger

    发明人： Xiaomei Fang ,  Jordan P. Seeger

    IPC分类号： B29C35/08 ,  C08L33/06

    CPC分类号： B29C35/0805 ,  B29C73/00 ,  B29C73/34 ,  B29C2035/0827 ,  C08J5/24 ,  C08J2363/00 ,  C08L33/06 ,  C09D133/068

    摘要： A UV curing system and method for manufacture and repair of composite parts, such as for use in wind blade manufacture and repair is disclosed. The system and method utilize UV as the single radiation source to cure laminates such as glass fiber reinforced laminates containing a photo initiator. The use of Co naphthenate or phenoxyethyl methacrylate in the curing of thick laminates produces high glass transition and complete curing of thick laminates. The addition of cobalt naphthenate and phenoxyethyl methacrylate shows no significant reduction on the bonding strength.

    摘要翻译： 公开了用于制造和修理复合零件的UV固化系统和方法，例如用于风力叶片的制造和修理。 该系统和方法利用UV作为单一辐射源来固化层压材料，例如含有光引发剂的玻璃纤维增​​强层压板。 在厚层压板的固化中使用环烷酸环氧化物或苯氧基乙基酯可以产生高的玻璃化转变和完全固化厚层压板。 添加环烷酸钴和甲基丙烯酸苯氧基乙酯显示结合强度没有显着降低。

    Polymer composite materials and processes therefor
    9.
    发明授权
    Polymer composite materials and processes therefor 有权
    聚合物复合材料及其工艺

    公开(公告)号：US08668864B2

    公开(公告)日：2014-03-11

    申请号：US13118885

    申请日：2011-05-31

    申请人： Mahendra Maheshwari ,  Xiaomei Fang

    发明人： Mahendra Maheshwari ,  Xiaomei Fang

    IPC分类号： B29C70/02

    CPC分类号： B32B5/28 ,  C08J5/24 ,  F01D5/282 ,  Y02T50/672 ,  Y02T50/673

    摘要： Processes for fabricating polymer composite materials that contain a polymer matrix, reinforcement fabrics, and particles of a filler material. The processes include spraying the particles of the filler material on at least two articles that each comprise at least one of the reinforcement fabrics to form particle-laden articles. The particle-laden articles are stacked to form a stacked structure, and a resin present within the stacked structure is then cured to form a laminate polymer composite material. The process can be employed in the fabrication of at least a portion of an aircraft engine nacelle, for example, the inlet lip of a fan nacelle.

    摘要翻译： 用于制造含有聚合物基质，增强织物和填充材料颗粒的聚合物复合材料的方法。 这些方法包括将填料材料的颗粒喷洒在至少两个制品上，每个制品包括至少一个增强织物以形成载有颗粒的制品。 将载有颗粒的物品层叠以形成堆叠结构，然后将存在于堆叠结构内的树脂固化以形成层压聚合物复合材料。 该方法可以用于制造飞机发动机机舱的至少一部分，例如风扇机舱的入口唇缘。