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公开(公告)号：US06938679B1
公开(公告)日：2005-09-06
申请号：US09153118
申请日：1998-09-15
申请人： Calvin H. Ito , Nigel C. Rowe
发明人： Calvin H. Ito , Nigel C. Rowe
CPC分类号： F28D15/0266 , B64D47/00 , B64D2013/0614 , B64G1/506 , F28D15/0275
摘要： A heat transport apparatus comprises an evaporator saddle having a pair of bores for housing two evaporators. The apparatus also comprises a condenser saddle having a pair of bores defining two condensers. One embodiment comprises a first loop heat pipe having a first condenser in fluid communication with a first evaporator, and a second loop heat pipe having a second condenser in fluid communication with a second evaporator. The two loop heat pipes share a single evaporator saddle and a single condenser saddle. A continuous conductance heat pipe may be placed in contact with either the evaporator saddle or the condenser saddle.
摘要翻译： 热传输装置包括具有一对用于容纳两个蒸发器的孔的蒸发器鞍座。 该装置还包括具有限定两个冷凝器的一对孔的冷凝器鞍座。 一个实施例包括具有与第一蒸发器流体连通的第一冷凝器的第一回路热管和具有与第二蒸发器流体连通的第二冷凝器的第二回路热管。 两个回路热管共享一个蒸发器鞍座和一个单一的冷凝器鞍座。 连续传导热管可以放置成与蒸发器鞍座或冷凝器鞍座接触。
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152.发明授权Solar torque control using thin film directionally reflective, emissive, absorptive and transmissive surfaces 失效使用薄膜定向反射，发射，吸收和透射表面的太阳能转矩控制公开(公告)号：US06921050B2
公开(公告)日：2005-07-26
申请号：US10346888
申请日：2003-01-17
摘要： Controlling the solar torque imposed on a spacecraft (10) in flight by providing a film (52) with variable absorptive, reflective, emissive and/or transmissive properties on the sun side of a thermal shield (50) of the spacecraft (10). As the orientation of the thermal shield (50) changes relative to the sun line, the absorptive, reflective, emissive and/or transmissive properties of the shield (50) change to cause the shield's (50) center of solar pressure to change, thus aligning it with the spacecraft (10) center of mass (24) as viewed from the direction of the sun line. In accordance with another embodiment of the invention, the spacecraft (100) is provided with a plurality of control vanes (110-116) that have a variable absorptive, transmissive, reflective and emissive property to maintain the spacecraft (100) stably pointed towards the sun.
摘要翻译： 通过在太空飞船（10）的热屏蔽（50）的太阳侧上提供具有可变吸收，反射，发射和/或透射特性的薄膜（52）来控制飞行中施加在航天器（10）上的太阳能转矩。 随着热屏蔽（50）的取向相对于太阳线变化，屏蔽（50）的吸收，反射，发射和/或透射特性改变，从而使屏蔽（50）的太阳压力中心发生变化，因此 将其与太阳线方向观察时的航天器（10）质心（24）对准。 根据本发明的另一个实施例，航天器（100）设置有多个控制叶片（110-116），其具有可变的吸收性，透射性，反射性和发射性，以将航天器（100）稳定地朝向 太阳。
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153.发明授权Geopositionable expendable sensors and the use therefor for monitoring surface conditions 失效地质消耗传感器及其用于监测表面状况的用途公开(公告)号：US06885299B2
公开(公告)日：2005-04-26
申请号：US10196646
申请日：2002-07-16
摘要： A sensor system for monitoring for the presence of contamination with one or more contaminating biological, chemical and/or radioactive agents on a terrain surface, and creating a contamination map thereof. The sensor system includes a plurality of sensor pods, a ground station, an airborne dispensing portion, and an airborne monitoring portion. The sensor pods include a pod housing, a descent slowing airfoil, a detector unit for detection of the contaminating agent and outputting contaminating agent data, a processor for processing the contaminating agent data, a GPS unit for determining the position of the sensor, and a transmitter for transmitting contamination agent data and position data to the airborne monitoring portion. The airborne monitoring portion receives the transmitted data from the sensor pods, and relays the data to the ground station, where the contamination map is made available.
摘要翻译： 一种传感器系统，用于监测在地形表面上存在一种或多种污染的生物，化学和/或放射性物质的污染物，并产生污染物图。 传感器系统包括多个传感器盒，地面站，机载分配部分和机载监视部分。 传感器盒包括荚壳体，下降减速翼型，用于检测污染物并输出污染物数据的检测器单元，用于处理污染物数据的处理器，用于确定传感器位置的GPS单元，以及 发送器，用于将污染物数据和位置数据传送到机载监视部分。 机载监视部分从传感器盒接收发送的数据，并将数据中继到地面站，在该地点可以获得污染图。
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公开(公告)号：US06883588B1
公开(公告)日：2005-04-26
申请号：US09624151
申请日：2000-07-24
CPC分类号： F25B27/005 , B64G1/50 , B64G1/503 , B64G1/506 , F25B9/002 , Y02A40/966
摘要： Heat dissipating apparatus or system for dissipating heat generated by a payload on a spacecraft having a plurality of surfaces. The system includes at least one radiator-condenser coupled to one or more of the surfaces of the spacecraft and a heat pump including an evaporator, a compressor, and an expansion valve coupled in a closed-loop manner to the radiator-condenser. The system components are coupled together using small diameter, thin- and smooth-walled tubing. The system enables the radiator-condenser to be elevated above the source or payload temperature, and, along with the use of thin walled tubing, reduces the mass of the spacecraft. Because the radiator-condenser temperatures are elevated, multiple surfaces of the spacecraft (west, east, earth and aft) can be effectively used as radiating surfaces.
摘要翻译： 用于耗散由具有多个表面的航天器上的有效载荷产生的热的散热装置或系统。 该系统包括耦合到航天器的一个或多个表面的至少一个散热器 - 冷凝器，以及包括蒸发器，压缩机和以闭环方式耦合到散热器 - 冷凝器的膨胀阀的热泵。 系统部件使用小直径，薄壁和平滑的管道连接在一起。 该系统使散热器 - 冷凝器升高到源或有效载荷温度以上，并且与使用薄壁管一起降低了航天器的质量。 由于散热器 - 冷凝器的温度升高，所以航天器的多个表面（西，东，土，船尾）可以有效地用作辐射表面。
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公开(公告)号：US6131646A
公开(公告)日：2000-10-17
申请号：US8758
申请日：1998-01-19
申请人： Lawrence R. Kelley
发明人： Lawrence R. Kelley
CPC分类号： F28F13/00 , B64G1/50 , B64G1/58 , B64G1/66 , H01L23/3672 , B64G1/503 , H01L2924/0002 , H01L2924/3011
摘要： There is provided a technique for removing unwanted heat from a heat generating device 12 operating aboard a space vehicle orbiting in outer space by placing a heat conductive interface 10 between the device and a support platform 14. The interface 10 comprises an array of spaced apart strips 16 made of aluminum aligned in spaced apart relationship so that the array covers the heat dissipating surface 20 at the underside of the device, the strips 16 are configured by deformable protuberances, such corrugations 22 which flatten under compression forces forming a heat conductive interface between the device 12 and the platform 14.
摘要翻译： 提供了一种用于通过在该设备和支撑平台14之间放置导热接口10来从在外部空间中行驶的空间车辆上操作的发热设备12去除不想要的热的技术。接口10包括间隔开的条带 16由铝制成，以间隔开的方式对准，使得阵列覆盖在装置下侧的散热表面20，条带16由可变形的突起构成，这种波纹22在压缩力下变平，在压缩力之间形成导热界面 设备12和平台14。
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156.发明授权
公开(公告)号：US6119573A
公开(公告)日：2000-09-19
申请号：US789111
申请日：1997-01-27
摘要： Carbon fiber material and carbon fiber material that is saturated with hydrocarbon solid-liquid phase change material may be used as thermal management materials for providing a thermally conductive interface between a heat source and its housing. Such carbon fiber material may also be used for mechanical isolation of the heat source from its housing. Carbon fibers used in the carbon fiber material may be unidirectionally oriented to provide for low friction, thus optimizing critically controlled friction tolerances. Additionally the carbon fiber material saturated with hydrocarbon solid-liquid phase change material may be used to transfer heat into the an inherently nonconductive medium.
摘要翻译： 碳氢化合物固体 - 液体相变材料饱和的碳纤维材料和碳纤维材料可用作热管理材料，用于在热源和其壳体之间提供导热界面。 这种碳纤维材料也可用于将热源与其壳体机械隔离。 碳纤维材料中使用的碳纤维可以单向取向以提供低摩擦，从而优化严格控制的摩擦公差。 此外，用烃固体 - 液相变材料饱和的碳纤维材料可用于将热量传递到固有的非导电介质中。
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157.发明授权
公开(公告)号：US6092590A
公开(公告)日：2000-07-25
申请号：US851593
申请日：1997-05-05
申请人： Friedemann Suttrop
发明人： Friedemann Suttrop
CPC分类号： B64G1/50 , F02C7/224 , F17C13/10 , F17C9/02 , F28D7/026 , F28D7/106 , F17C2203/012 , F17C2221/012 , F17C2223/0153 , F17C2223/033 , F17C2225/0123 , F17C2227/0393 , F17C2260/032 , F17C2270/0189 , F28D2021/0033 , F28D2021/0047 , Y02E60/321
摘要： In a method and evaporator device for evaporating a low temperature liquid medium, such as hydrogen for example, the hydrogen is first evaporated and at least partially superheated in a forward-flowing first channel, and is then directed to flow back in the opposite direction in a second return-flowing channel. The second channel is especially interposed between the first channel and a passage through which flows a heat-providing medium such as a hot exhaust gas. Thus, the superheated hydrogen flowing in the second channel serves as an intermediate layer for heat transfer from the heat-providing medium through the hydrogen in the second channel to the low temperature, initially liquid hydrogen in the first channel. The heat exchange surfaces in contact with the heat-providing medium are not directly adjacent the extremely cold surfaces in contact with the in-flowing low temperature liquid hydrogen, and the superheated hydrogen acts as a buffer between the hot side and the cold side of the evaporator. As a result, the evaporator has a very low structural weight, and condensation and icing problems can be avoided even when using a hot medium and a cold medium having extremely different temperatures.
摘要翻译： 在用于蒸发例如氢气的低温液体介质的方法和蒸发器装置中，首先在向前流动的第一通道中蒸发氢并且至少部分地过热，然后将氢引导回向相反方向 第二回流通道。 第二通道特别介于第一通道和流过诸如热废气之类的供热介质的通道之间。 因此，在第二通道中流动的过热氢气用作从第二通道中的从供热介质通过氢气到第一通道中的低温初始液态氢的热传递的中间层。 与供热介质接触的热交换表面不直接邻近与流动中的低温液氢接触的极冷的表面，并且过热的氢气作为缓冲区在热侧和冷侧之间的缓冲区 蒸发器。 结果，蒸发器具有非常低的结构重量，并且即使当使用具有极高温度的热介质和冷介质时也可以避免冷凝和结冰问题。
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公开(公告)号：US6080962A
公开(公告)日：2000-06-27
申请号：US771466
申请日：1996-12-20
申请人： David W. Y. Lee
发明人： David W. Y. Lee
摘要： A spacecraft electronics equipment module that is thermally independent of a core spacecraft structure to which it can be mounted. The module takes the form of a thermal radiation panel on which electronic components are directly mounted. The panel is attachable to the core structure and includes its own double-sided radiator for cooling of the electronics components, an integral heater for raising the temperature is needed, a thermal controller, for automatically regulating the temperature of the module components, and heatpipes for distributing the heat more uniformly across the radiating surfaces.
摘要翻译： 与能够安装的核心航天器结构热独立的航空电子设备模块。 该模块采用直接安装电子部件的热辐射面板的形式。 该面板可连接到核心结构，并且包括其自己的用于冷却电子部件的双面散热器，需要用于升高温度的一体式加热器，用于自动调节模块部件的温度的热控制器，以及用于 将热量更均匀地分布在辐射表面上。
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公开(公告)号：US06037909A
公开(公告)日：2000-03-14
申请号：US823788
申请日：1997-03-21
申请人： Alan R. Cherrette
发明人： Alan R. Cherrette
IPC分类号： B64G1/50 , B64G1/66 , H01Q1/00 , H01Q1/08 , H01Q1/28 , H01Q21/00 , H01Q21/06 , H01Q23/00 , H01Q13/10
CPC分类号： H01Q1/002 , H01Q1/288 , H01Q21/0087 , Y10S343/02
摘要： The integration of traveling wave tube amplifiers and multiplexers onto passive transmit array antenna panels deployed out board of a spacecraft bus to simultaneously provide a spacecraft transponder that permits antenna pattern flexibility in orbit, high DC to RF power conversion efficiency, facilitates higher spacecraft power and provides a spacecraft with deployed payload panel architecture having multiple independent beams that can be electronically reconfigured on the ground or in orbit.
摘要翻译： 将行波管放大器和多路复用器集成到被部署在航天器总线上的板的无源发射阵列天线面板上，以同时提供允许轨道中的天线方向图灵活性，高DC到RF功率转换效率的航天器转发器，便于更高的航天器功率并提供 具有部署有效载荷面板结构的航天器具有可在地面或轨道上电子重构的多个独立梁。
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公开(公告)号：US6003817A
公开(公告)日：1999-12-21
申请号：US746587
申请日：1996-11-12
摘要： One or more deployable thermal panels (24, 28, 70) are actively controlled throughout the orbit of a satellite (20) to provide thermal dissipation. Adjusting the incident angle between the panel (24, 28, 70) and the sun and controlling the flow of fluid through optional flexible heat pipes loads and unloads heat to provide thermal stability for components (62) which have special thermal requirements. An optional antenna panel (70) on a nadir side (64) of the satellite (20) offers an antenna side (74) on one surface and a thermal radiating side (72) on an opposing surface. In addition, thermal panel movements are controlled (96) to provide counter-disturbance torques (140).
摘要翻译： 在卫星（20）的整个轨道上主动地控制一个或多个可展开的散热板（24,28,70）以提供散热。 调整面板（24,28,70）与太阳之间的入射角度并通过可选的柔性热管来控制流体的流动，加载并卸载热量，以为具有特殊热量要求的部件（62）提供热稳定性。 在卫星（20）的最低侧（64）上的可选的天线面板（70）在一个表面上提供天线侧（74），在对置的表面上提供热辐射侧（72）。 此外，控制热板运动（96）以提供反扰动力矩（140）。
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