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    USE OF MONAZITE OR XENOTIME SOLUTION PRECURSORS TO INCREASE THE DENSITY AND SHEAR STRENGTH OF OXIDE COMPOSITES
    1.
    发明申请
    USE OF MONAZITE OR XENOTIME SOLUTION PRECURSORS TO INCREASE THE DENSITY AND SHEAR STRENGTH OF OXIDE COMPOSITES 有权
    使用MONAZITE或XENOTIME解决方案前提物提高氧化复合材料的密度和剪切强度

    公开(公告)号：US20140065292A1

    公开(公告)日：2014-03-06

    申请号：US12044336

    申请日：2008-03-07

    申请人： David B. Marshall ,  Janet B. Davis ,  Peter D. Morgan

    发明人： David B. Marshall ,  Janet B. Davis ,  Peter D. Morgan

    IPC分类号： C04B41/45 ,  C04B41/87

    CPC分类号： C04B41/4596 ,  C04B35/447 ,  C04B35/62881 ,  C04B35/803 ,  C04B41/87 ,  C04B2235/3217 ,  C04B2235/3224 ,  C04B2235/3225 ,  C04B2235/3227 ,  C04B2235/3229 ,  C04B2235/443 ,  C04B2235/447 ,  C04B2235/5224 ,  C04B2235/5445 ,  C04B2235/616

    摘要： Aqueous precursor solutions are described that comprise at least one monazite-based material precursor, at least one xenotime-based material precursor or a combination thereof; and a plurality of fine suspended particles of an oxide material. Contemplated oxide composites, as described herein, comprise a plurality of fibers surrounded by at least one monazite or xenotime-based material, wherein the oxide composite has nearly a fully dense matrix. Contemplated embodiments disclosed herein provides a method for producing an oxide composite with nearly fully dense matrix and with all fibers surrounded by a monazite- or xenotime-based material that prevents embrittlement at temperatures at least as high as 1200° C. Oxide composites are described that contain a plurality of fibers, a matrix containing at least one or more oxide materials, and at least one monazite-based material, xenotime-based material or combination thereof, wherein the monazite-based or xenotime-based material is formed from the aqueous precursor solutions disclosed herein. Contemplated methods of production include: a) providing a composite comprising oxide-reinforcing fibers and a porous matrix of oxide materials, and b) infiltrating the porosity in the matrix with a solution that contains precursors for at least one monazite-based material, at least one xenotime-based material or a combination thereof; and c) heat treating the composite to convert the precursors to monazite, xenotime, or combinations thereof.

    摘要翻译： 描述了包含至少一种独居石基材料前体，至少一种基于堇青石的材料前体或其组合的水性前体溶液; 和多个细小的氧化物悬浮颗粒。 如本文所述，沉积的氧化物复合材料包含被至少一种独居石或基于堇青石的材料包围的多个纤维，其中氧化物复合材料具有几乎完全致密的基质。 本文公开的考虑的实施例提供了一种用于生产具有几乎完全致密的基质的氧化物复合材料的方法，并且所有的纤维都被独立铁矿或堇青石基材料包围，以防止在至少高达1200℃的温度下的脆化。氧化物复合材料被描述为 含有多个纤维，含有至少一种或多种氧化物材料的基质，以及至少一种独居石类材料，堇青石类材料或其组合，其中所述独居石类或堇青石类材料由水性前体形成 本文公开的解决方案。 考虑的生产方法包括：a）提供包含氧化物增强纤维和氧化物材料的多孔基质的复合材料，以及b）用包含至少一种独居石基材料的前体的溶液渗透到基体中的孔隙，至少 一种基于脱乙酸铁基的材料或其组合; 和c）热处理复合材料以将前体转化为独居石，堇青石或其组合。

    HYBRID COMPOSITE FOR EROSION RESISTANT HELICOPTER BLADES
    5.
    发明申请
    HYBRID COMPOSITE FOR EROSION RESISTANT HELICOPTER BLADES 有权
    用于耐腐蚀直升机叶片的混合复合材料

    公开(公告)号：US20100329880A1

    公开(公告)日：2010-12-30

    申请号：US12650172

    申请日：2009-12-30

    申请人： Janet B. Davis ,  David B. Marshall ,  Olivier H. Sudre ,  Sergio dos Santos e Lucato

    发明人： Janet B. Davis ,  David B. Marshall ,  Olivier H. Sudre ,  Sergio dos Santos e Lucato

    IPC分类号： B64C11/16 ,  B64C11/20

    CPC分类号： B29D99/0025 ,  B64C27/473 ,  B64C2027/4736

    摘要： A protective hybrid composite for a rotor blade is based on the use of tape cast ceramic layers densified by pre-ceramic polymer infiltration methods and laminated together with polymer matrix composite prepregs, with or without an embedded metallic mesh, to form a conforming helicopter blade cladding that is laminated to the blade surface for added erosion protection. The hybrid composite is fabricated to net shape and laminated to the blade using either an adhesive or a polymer composite prepreg inner layer. Installation is accomplished by a standard composite fabrication method of vacuum bagging the blade while the system is laminated to its surface. Repair methods based on removal of ceramic tiles is facilitated by incorporation of a metallic mesh element laminated beneath the ceramic tiles that can be used to heat the tile and decrease its adhesion strength.

    摘要翻译： 用于转子叶片的保护性混合复合材料基于使用通过预陶瓷聚合物渗透方法致密化的带状陶瓷层，并与具有或不具有嵌入金属网的聚合物基质复合预浸料层压在一起以形成一致的直升机叶片覆层 层压到叶片表面以增加侵蚀保护。 将混合复合材料制成网状，并使用粘合剂或聚合物复合预浸料内层层压到叶片上。 安装是通过在将系统层压到其表面上的真空袋装刀片的标准复合制造方法来实现的。 基于去除瓷砖的修复方法通过结合层压在陶瓷砖下方的金属网状元件而得以促进，其可用于加热瓷砖并降低其粘合强度。

    Use of monazite or xenotime solution precursors to increase the density and shear strength of oxide composites
    6.
    发明授权
    Use of monazite or xenotime solution precursors to increase the density and shear strength of oxide composites 有权
    使用独居石或堇青石溶液前体来增加氧化物复合材料的密度和剪切强度

    公开(公告)号：US08758908B2

    公开(公告)日：2014-06-24

    申请号：US12044336

    申请日：2008-03-07

    申请人： David B. Marshall ,  Janet B. Davis ,  Peter E. D. Morgan

    发明人： David B. Marshall ,  Janet B. Davis ,  Peter E. D. Morgan

    IPC分类号： B32B9/00 ,  B32B19/00 ,  B32B9/04

    CPC分类号： C04B41/4596 ,  C04B35/447 ,  C04B35/62881 ,  C04B35/803 ,  C04B41/87 ,  C04B2235/3217 ,  C04B2235/3224 ,  C04B2235/3225 ,  C04B2235/3227 ,  C04B2235/3229 ,  C04B2235/443 ,  C04B2235/447 ,  C04B2235/5224 ,  C04B2235/5445 ,  C04B2235/616

    摘要： Aqueous precursor solutions are described that comprise at least one monazite-based material precursor, at least one xenotime-based material precursor or a combination thereof; and a plurality of fine suspended particles of an oxide material. Contemplated oxide composites, as described herein, comprise a plurality of fibers surrounded by at least one monazite or xenotime-based material, wherein the oxide composite has nearly a fully dense matrix. Contemplated embodiments disclosed herein provides a method for producing an oxide composite with nearly fully dense matrix and with all fibers surrounded by a monazite- or xenotime-based material that prevents embrittlement at temperatures at least as high as 1200° C. Oxide composites are described that contain a plurality of fibers, a matrix containing at least one or more oxide materials, and at least one monazite-based material, xenotime-based material or combination thereof, wherein the monazite-based or xenotime-based material is formed from the aqueous precursor solutions disclosed herein. Contemplated methods of production include: a) providing a composite comprising oxide-reinforcing fibers and a porous matrix of oxide materials, and b) infiltrating the porosity in the matrix with a solution that contains precursors for at least one monazite-based material, at least one xenotime-based material or a combination thereof; and c) heat treating the composite to convert the precursors to monazite, xenotime, or combinations thereof.

    摘要翻译： 描述了包含至少一种独居石基材料前体，至少一种基于堇青石的材料前体或其组合的水性前体溶液; 和多个细小的氧化物悬浮颗粒。 如本文所述，沉积的氧化物复合材料包含被至少一种独居石或基于堇青石的材料包围的多个纤维，其中氧化物复合材料具有几乎完全致密的基质。 本文公开的考虑的实施例提供了一种用于生产具有几乎完全致密的基质的氧化物复合材料的方法，并且所有的纤维都被独立铁矿或堇青石基材料包围，以防止在至少高达1200℃的温度下的脆化。氧化物复合材料被描述为 含有多个纤维，含有至少一种或多种氧化物材料的基质，以及至少一种独居石类材料，堇青石类材料或其组合，其中所述独居石类或堇青石类材料由水性前体形成 本文公开的解决方案。 考虑的生产方法包括：a）提供包含氧化物增强纤维和氧化物材料的多孔基质的复合材料，以及b）用包含至少一种独居石基材料的前体的溶液渗透到基体中的孔隙，至少 一种基于脱乙酸铁基的材料或其组合; 和c）热处理复合材料以将前体转化为独居石，堇青石或其组合。

    Temperature tolerant hooks for hook and loop attachment
    7.
    发明授权
    Temperature tolerant hooks for hook and loop attachment 有权
    用于钩环连接的耐温钩

    公开(公告)号：US08017213B2

    公开(公告)日：2011-09-13

    申请号：US11379677

    申请日：2006-04-21

    申请人： Olivier H. Sudre ,  Janet B. Davis ,  Stanley A. Lawton

    发明人： Olivier H. Sudre ,  Janet B. Davis ,  Stanley A. Lawton

    IPC分类号： B32B3/06

    CPC分类号： A44B18/0038 ,  Y10T29/49826 ,  Y10T29/49948 ,  Y10T428/23993 ,  Y10T428/24017

    摘要： A temperature tolerant hook and loop attachment, a method of forming a sheet of the hooks and, a method of insulating the skin of a flight vehicle. Temporary loops are formed in a fabric containing temperature tolerant fiber tows, e.g., the tows may be carbon, a metal, a carbide such as carbon silicide, a nitride, or an oxide. The temporary loops are stiffened (e.g., with resin, metal or ceramic), and severed to form temperature tolerant fiber composite hooks. The sheet may be cut and permanently applied, for example, to the skin of a spacecraft or aircraft. A fibrous material, e.g., fibrous insulation or batting, may be pressed in place or formed into the hooks, or the fibrous material may be attached to another structure and pressed in place for a temperature tolerant hook and loop attachment.

    摘要翻译： 耐温钩钩环附件，形成钩片的方法，以及使飞行器的皮肤绝缘的方法。 在包含耐温纤维丝束的织物中形成临时环，例如，丝束可以是碳，金属，碳化硅如碳化硅，氮化物或氧化物。 临时环被加固（例如用树脂，金属或陶瓷），并且被切断以形成耐温纤维复合钩。 片可以被切割并永久地施加到例如航天器或飞行器的皮肤上。 纤维材料，例如纤维绝缘或棉絮，可以被压在适当位置或形成钩子，或者纤维材料可以附着到另一结构上，并被压在适当的位置，以实现耐温钩挂环。

    Materials for self-transpiring hot skins for hypersonic vehicles or reusable space vehicles
    10.
    发明授权
    Materials for self-transpiring hot skins for hypersonic vehicles or reusable space vehicles 有权
    超音速车辆或可重复使用的太空车辆自发热皮的材料

    公开(公告)号：US07281688B1

    公开(公告)日：2007-10-16

    申请号：US11380450

    申请日：2006-04-27

    申请人： Brian Nelson Cox ,  Janet B. Davis ,  Julia Mack ,  David Bruce Marshall ,  Peter E. Morgan ,  Olivier H. Sudre

    发明人： Brian Nelson Cox ,  Janet B. Davis ,  Julia Mack ,  David Bruce Marshall ,  Peter E. Morgan ,  Olivier H. Sudre

    IPC分类号： B64G1/58

    CPC分类号： B64G1/58 ,  B64G1/14

    摘要： A self-transpiring hot skin for a hypersonic or reusable space vehicle that can provide protection to the vehicle during short periods of abnormally high heat flux (either planned in the flight profile or an off-nominal event). The hot skin includes a ceramic composite structure having an internal cavity that is coupled either to the insulating layer or directly to the support structure of the hypersonic vehicle. The internal cavity includes a material system that vaporizes, sublimes or decomposes into a gas when the temperature exceeds the upper temperature capability of the composite material. The gas transpires through the outer layer of the composite material to provide cooling to the outer layer below the upper temperature capability. Cooling may occur both by conduction of heat from the composite material to the transpiring gas and by the interaction of the transpiring gas with the boundary layer of hypersonic flow over the outer surface, leading to a reduction of the heat flux entering the surface.

    摘要翻译： 用于超音速或可重复使用的空中交通工具的自发热皮肤，可在短时间内异常高的热通量（在飞行情况下计划或非标称事件）中为车辆提供保护。 热皮肤包括具有内腔的陶瓷复合结构，其内部耦合到绝缘层或直接连接到超音速车辆的支撑结构。 内部空腔包括当温度超过复合材料的较高温度能力时气化，升华或分解成气体的材料体系。 气体通过复合材料的外层渗透，以便在较高温度能力以下向外层提供冷却。 冷却可以通过从复合材料传导到蒸发气体以及蒸发气体与外表面上的超音速流动边界层的相互作用而发生，导致进入表面的热通量减少。