公开(公告)号：US07516918B2

公开(公告)日：2009-04-14

申请号：US11432865

申请日：2006-05-11

申请人： Brian N. Cox ,  Janet B. Davis ,  Sergio Luis dos Santos e Lucato ,  David B. Marshall ,  Brock S. McCabe ,  Olivier H. Sudre

发明人： Brian N. Cox ,  Janet B. Davis ,  Sergio Luis dos Santos e Lucato ,  David B. Marshall ,  Brock S. McCabe ,  Olivier H. Sudre

IPC分类号： B64D29/00 ,  B64C9/02 ,  B32B5/08

CPC分类号： B64C30/00 ,  B64D33/02 ,  B64D2033/026 ,  F02C7/042 ,  F05D2220/80 ,  F05D2300/2112 ,  F05D2300/224 ,  F05D2300/226 ,  F05D2300/2261 ,  F05D2300/228 ,  F05D2300/614 ,  Y02T50/672 ,  Y10T428/249928

摘要： An exemplary morphable ceramic composite structure includes a flexible ceramic composite skin and a truss structure attached to the skin. The truss structure can morph shape of the skin from a first shape to a second shape that is different than the first shape. The flexible ceramic composite skin may include a single-layer of three-dimensional woven fabric fibers and a ceramic matrix composite. The truss structure may include at least one actuatable element or an actuator may move a portion of the truss structure from a first position to a second position. A cooling component may be disposed in thermal communication with the skin. The cooling component may include thermal insulation or a cooling system that circulates cooling fluid in thermal communication with the skin. The morphable ceramic composite structure may be incorporated into any of an air inlet, combustor, exhaust nozzle, or control surfaces of a hypersonic aircraft.

摘要翻译： 示例性的变形陶瓷复合结构包括柔性陶瓷复合材料表皮和附着于皮肤的桁架结构。 桁架结构可以将皮肤的形状从第一形状变形为与第一形状不同的第二形状。 柔性陶瓷复合表皮可以包括单层三维织物纤维和陶瓷基复合材料。 桁架结构可以包括至少一个可启动元件，或者致动器可将桁架结构的一部分从第一位置移动到第二位置。 冷却部件可以设置成与皮肤热连通。 冷却部件可以包括热绝缘或冷却系统，其使冷却流体与皮肤热连通。 变形陶瓷复合结构可以结合到超音速飞机的空气入口，燃烧器，排气喷嘴或控制表面中的任何一个中。

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。

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。

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。

公开(公告)号：US06863999B1

公开(公告)日：2005-03-08

申请号：US10057184

申请日：2002-01-23

申请人： Olivier H. Sudre ,  David B. Marshall ,  Peter E. D. Morgan

发明人： Olivier H. Sudre ,  David B. Marshall ,  Peter E. D. Morgan

IPC分类号： B32B9/06 ,  C23C28/00 ,  C23C28/04 ,  F01D5/28 ,  F03B3/12

CPC分类号： F01D5/288 ,  C23C28/04 ,  C23C28/042 ,  C23C28/048

摘要： Monazites and xenotimes are rare-earth phosphates showing a combination of properties expected to be suitable for thermal barrier coatings. For example, lanthanum phosphate (La-monazite) can be used to form thermal barrier coatings to protect superalloy and ceramic parts exposed to high temperature and damage by sulfur, vanadium, phosphorus and other contaminants. The monazite or xenotime coatings can be applied using any of the common application methods including EB-PVD, laser ablation and plasma spraying. The stoichiometry of the coatings can be modulated according to the stoichiometry of specially prepared starting target (source) material. The most effective coatings appear to be largely crystalline and show a columnar structure with feather-like microstructure. For La-monazite, effective coatings between 10 and 500 micrometers in thickness can be deposited on substrates having temperatures between about 750° C. and about 950° C.

摘要翻译： 独居石和异味是稀土磷酸盐，显示出预期适用于热障涂层的性能组合。 例如，可以使用磷酸镧（La-monazite）形成热障涂层，以保护暴露于高温的高温合金和陶瓷部件，并受到硫，钒，磷和其他污染物的损害。 可以使用任何常见的应用方法（包括EB-PVD，激光烧蚀和等离子体喷涂）来应用独居石或含钇矿涂层。 涂层的化学计量可以根据专门制备的起始靶（源）材料的化学计量来调节。 最有效的涂层看起来很大程度上是结晶的，并且显示出具有羽状微结构的柱状结构。 对于独立For石，厚度为10至500微米的有效涂层可以沉积在温度在约750℃至约950℃之间的基底上。