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公开(公告)号：US20030131982A1
公开(公告)日：2003-07-17
申请号：US10304236
申请日：2002-11-25
发明人： James Albert Riedell
IPC分类号： F28F007/00
摘要： A method and system for assembly and attachment of high temperature materials used as thermal protection systems (TPS) for applications such as re-entry or hypersonic vehicles are disclosed. The attachment system comprises a fastener that passes through an aperture of and a fitting attached to a ceramic matrix composite (CMC) TPS panel. The flexure fitting allows thermal growth in the panel while providing a structurally stiff interface to support the panel through structural and acoustic loading. The flexure fitting is detachably attached to the substructure, or fuel tank of a vehicle. The fastened connection is accessed through an aperture via an access cover plate conformal to the surface of the CMC TPS panel. It is by way of the access cover that the fastened connection is externally serviced.
摘要翻译： 公开了一种用于组装和附接用作热保护系统（TPS）的高温材料用于诸如再入式或超音速车辆的应用的方法和系统。 附接系统包括通过孔的孔的紧固件和连接到陶瓷基体复合材料（CMC）TPS面板的配件。 弯曲配件允许面板中的热生长，同时提供结构上刚性的界面，以通过结构和声学负载来支撑面板。 挠性配件可拆卸地附接到车辆的底座或燃料箱。 通过与CMC TPS面板表面共形的通道盖板通过孔径来访问紧固连接。 通过接入盖，固定连接被外部维护。
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公开(公告)号：US20020144836A1
公开(公告)日：2002-10-10
申请号：US10050095
申请日：2002-01-15
发明人： David L. Hunn , Barry W. Bartos
IPC分类号： H01B007/18
摘要： An electrically-conductive, thermally-insulating structure includes a thermally-insulating layer having a thermal conductivity of no more than about 3.5null10null3 W/hrnullcmnullnull K and an electrically-conductive layer, applied to the thermally-insulating layer, which has an electrical resistivity of no more than about five ohms at 700null C. The thermally-insulating layer can comprise a plurality of microballoons to decrease the density of the thermally-insulating layer.
摘要翻译： 导电的绝热结构包括热导率不大于约3.5×10-3W / hr·cm·K的绝热层，以及施加到绝热层的导电层 ，其在700℃下的电阻率不超过约5欧姆。绝热层可以包括多个微球，以降低绝热层的密度。
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23.发明授权System and method for attaching a structural component to an aerospace vehicle 失效将结构部件连接到航天飞行器的系统和方法
公开(公告)号：US5979831A
公开(公告)日：1999-11-09
申请号：US104963
申请日：1998-06-25
申请人： John D. Seaquist
发明人： John D. Seaquist
摘要： A system and method for attaching an annular structural component to an aerospace vehicle is provided. The system includes a plurality of fittings circumferentially affixed to an engagement portion of the vehicle, and a plurality of supports. Each support has a first end connected to a corresponding fitting, and a second end having an elongate slot. A flange is configured to extend inwardly from the structural component and into engagement with the second end of each support. The flange has an elongate slot located at each support. Each flange slot is non-parallel to an open communication with each respective support slot. A plurality of pins connects the supports to the flange. Each pin extends through a corresponding flange slot and respective support slot to constrain the structural component, while attaching the structural component to the vehicle during use of the vehicle.
摘要翻译： 提供了一种用于将环形结构部件附接到航空航天车辆的系统和方法。 该系统包括周向地固定到车辆的接合部分上的多个配件和多个支撑件。 每个支撑件具有连接到相应配件的第一端和具有细长槽的第二端。 凸缘构造成从结构部件向内延伸并与每个支撑件的第二端接合。 该凸缘具有位于每个支撑件处的细长槽。 每个凸缘槽不平行于与每个相应的支撑槽的开放式连接。 多个销将支撑件连接到凸缘。 每个销延伸穿过对应的凸缘槽和相应的支撑槽以约束结构部件，同时在车辆使用期间将结构部件附接到车辆。
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公开(公告)号：US5452866A
公开(公告)日：1995-09-26
申请号：US197894
申请日：1994-02-17
申请人： Melvin J. Bulman
发明人： Melvin J. Bulman
摘要： A transpiration cooling system for avoiding overheating of an airfoil is provided. The airfoil is provided with a plurality of apertures and a source of pressurized fluid for providing a flow of fluid through the apertures to establish an aerodynamic radius. The aerodynamic radius of curvature of leading edge is sufficiently greater than the mechanical radius of curvature of the leading edge that peak heat flux is independent of the mechanical radius of curvature. The mechanical radius of curvature is preferably less than 50% of the aerodynamic radius of curvature during hypersonic operation. Preferably the mechanical radius of curvature is the smallest allowed by the fabrication method (i.e., a knife edge), such as being less than about 0.02 inches, preferably less than about 0.01 inches. The transpiration blowing rate can be adjusted so that the blowing rate and aerodynamic radius of curvature are relatively low except during periods of maximum heat flux, such as the shock-on-lip point. Since the mechanical radius of curvature is effectively zero, control of the aerodynamic radius of curvature provides complete control of peak heat flux. By adjusting blowing rate to the minimum necessary at any given velocity, transpiration consumption, drag and fuel injection are reduced or eliminated.
摘要翻译： 提供了一种用于避免翼型件过热的蒸腾冷却系统。 机翼设置有多个孔和加压流体源，用于提供通过孔的流体流以建立空气动力学半径。 前缘的空气动力学曲率半径充分大于前缘的机械曲率半径，峰值热通量与机械曲率半径无关。 在超音速操作期间，机械曲率半径优选小于空气动力学曲率半径的50％。 优选地，机械曲率半径是制造方法（即，刀刃）允许的最小值，例如小于约0.02英寸，优选小于约0.01英寸。 可以调节蒸腾吹送速率，使得吹出速率和空气动力学曲率半径相对较低，除了在最大热通量期间，例如冲击冲击点。 由于机械曲率半径实际上为零，因此空气动力学曲率半径的控制提供了峰值热通量的完全控制。 通过将吹入速率调整到任何给定速度所需的最小值，减少或消除蒸腾消耗，阻力和燃料喷射。
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公开(公告)号：US5236151A
公开(公告)日：1993-08-17
申请号：US812665
申请日：1991-12-23
申请人： Michael P. Hagle , Reed R. Oliver
发明人： Michael P. Hagle , Reed R. Oliver
摘要： An insulative panel is attachable to a structure to thermally protect the structure. The insulative panel includes a piece of a compliant, porous material. A support base is bonded to a first side of the piece of porous material, the support base including means for attaching the support base to the structure that is to be protected. A skin made of a thermally resistant material is bonded to a second side of the piece of porous material. Preferably, the porous material is a piece of porous ceramic foam having an apparent density of less than about 25 percent, the support base is a piece of nonporous ceramic material, and the skin is a ceramic thermal barrier coating that is plasma sprayed onto the porous material.
摘要翻译： 绝缘板可附接到结构以热保护结构。 绝缘面板包括一块兼容的多孔材料。 支撑基部结合到多孔材料片的第一侧，支撑基底包括用于将支撑基座附接到待保护结构的装置。 由耐热材料制成的皮肤粘合到多孔材料片的第二侧。 优选地，多孔材料是具有小于约25％的表观密度的一块多孔陶瓷泡沫，支撑基底是一块无孔陶瓷材料，并且皮肤是陶瓷热障涂层，其被等离子体喷涂到多孔 材料。
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公开(公告)号：US5016015A
公开(公告)日：1991-05-14
申请号：US421490
申请日：1989-10-13
CPC分类号： H01Q17/00 , B64C1/38 , F41H3/00 , Y10T428/24149
摘要： An aircraft structure for the minimization of microwave energy reflection from the aircraft back to a receiver. The provision of structural configurations and materials operate to reduce microwave energy reflection toward its source or another receiver located at a level below the aircraft and laterally or forward thereof.
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公开(公告)号：US4991797A
公开(公告)日：1991-02-12
申请号：US298071
申请日：1989-01-17
IPC分类号： B64C1/38
CPC分类号： B64C1/38
摘要： The invention provides a system for selective reduction of infrared signature of a vehicle subjected to aerodynamic heating. Liquid coolant under pressure vaporizes in porous sections of the skin of the vehicle to transpiration-cool the skin. Adjacent downstream solid skin sections are film-cooled by the vapor introduced in the boundary layer. Coolant flow control is achieved by pressurizing the liquid coolant, by modulating flow control valves, and, optionally, by configuring the porous section to operate as a cavitating venturi, or combinations of these methods.
摘要翻译： 本发明提供一种用于选择性地减少经受空气动力学加热的车辆的红外特征的系统。 压力下的液体冷却剂在车辆皮肤的多孔部分中蒸发蒸发，冷却皮肤。 相邻的下游固体皮肤部分由引入边界层的蒸气进行薄膜冷却。 冷却剂流量控制通过对液体冷却剂进行加压，通过调节流量控制阀以及可选地通过将多孔部分配置为气蚀文丘里管来操作或这些方法的组合来实现。
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公开(公告)号：US4923146A
公开(公告)日：1990-05-08
申请号：US217438
申请日：1988-07-11
申请人： Frank M. Anthony
发明人： Frank M. Anthony
摘要： An improved means for convection cooling the skin surfaces of an atmospheric flight craft such as are subject to air friction-induced overheating when the craft operates at high speed, featuring employment of multiple layered, spaced apart skin members separated and relatively braced by web and post members. Fresh coolant fluid is simultaneously flushed against and contiguously covers a multiplicity of relatively small patches of the inside surface of the outer skin member to be protected, and the spent coolant from each patch is separately removed therefrom and returned to the craft's refrigeration facility. The web and post members also act to direct the pattern of coolant flow so as to provide a much improved heat transfer coefficient than can be attained by other coolant path configurations when an equal pressure drop is applied.
摘要翻译： 一种改进的方法，用于对流冷却大气飞行器的皮肤表面，例如当飞行器高速运行时，受到空气摩擦引起的过热，特征在于使用多个分层的间隔开的皮肤部件，其被分离并相对地通过腹板和后支撑 会员 新鲜的冷却剂流体同时冲洗并连续地覆盖待保护的外部皮肤构件的内表面的多个相对小的贴片，并且来自每个贴片的废弃的冷却剂被单独地从其中移除并返回到工艺的制冷设备。 网和柱构件还用于引导冷却剂流动的模式，以便当施加相等的压降时，提供比其它冷却剂路径构造可以获得的传热系数更大的改善。
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公开(公告)号：US4786015A
公开(公告)日：1988-11-22
申请号：US948109
申请日：1986-12-31
申请人： Richard E. Niggemann
发明人： Richard E. Niggemann
IPC分类号： B64C1/38
CPC分类号： B64C1/38
摘要： In order to dissipate aerodynamic heating in hypersonic aircraft, while at the same time providing structural support for the leading edge of an airfoil or the nose cone in a manner that avoids transmittal of thermal bending loads into the aircraft, a structural cooling unit is formed of a load bearing structure. The load bearing structure is of hollow construction defining a fluid flow path therethrough and has a fluid inlet at one end of the fluid flow path and a fluid outlet at the other end of the fluid flow path which comprises a tortuous path through the load bearing structure. Additionally, for purposes of forming a structural load path, the load bearing structure is formed into an elongated tubular configuration having at least one substantially continuous heat exchanging surface for aerodynamic heat dissipation.
摘要翻译： 为了消除超音速飞机中的空气动力学加热，同时以避免将热弯曲载荷传递到飞行器的方式为翼型件或鼻锥体的前缘提供结构支撑，结构冷却单元由 承重结构。 承载结构具有中空构造，其限定了通过其的流体流动路径，并且在流体流动路径的一端处具有流体入口，并且在流体流动路径的另一端处具有流体出口，该流体出口包括通过承载结构的曲折路径 。 此外，为了形成结构载荷路径，承载结构形成为具有用于空气动力学散热的至少一个基本上连续的热交换表面的细长管状构造。
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公开(公告)号：US4014485A
公开(公告)日：1977-03-29
申请号：US567673
申请日：1975-04-14
IPC分类号： B64C1/38
CPC分类号： B64C1/38
摘要： A cooled nosetip arrangement for a vehicle designed to travel at hypersonic velocities is taught herein. We provide a nosetip having one or more orifices at its forwardmost location, but instead of utilizing an arrangement for expelling a liquid coolant, which would necessitate a considerable amount of plumbing and tankage, we utilize a novel gas generator arrangement enabling a coolant gas to be selectively generated and then expelled from such nosetip orifice(s). In this manner we utilize a coolant that advantageously remains in a chemical form until it is to be actually utilized.
摘要翻译： 本文教导了用于以超音速行驶的车辆的冷却的鼻塞装置。 我们提供在其最前面的位置具有一个或多个孔口的鼻塞，但不是利用排出液体冷却剂的装置，这将需要相当数量的管道和容器，我们利用新型的气体发生器装置使冷却剂气体成为 选择性地产生并随后从这种鼻塞孔排出。 以这种方式，我们利用有利地保持化学形式的冷却剂，直到其被实际使用。
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