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公开(公告)号：US5253701A
公开(公告)日：1993-10-19
申请号：US940471
申请日：1992-09-04
申请人： Bernhard Leidinger
发明人： Bernhard Leidinger
CPC分类号： F28F9/22 , B01D1/04 , B64G1/50 , F28D5/00 , F28F2009/226
摘要： Heat generated, for example, in a spacecraft under zero gravity conditions and different accelerations is discharged through an evaporation heat exchanger connected to at least one active coolant circulation circuit. The heat exchanger has a bundle of tubes axially arranged inside a cylindrical processing chamber. An evaporant passes through these tubes. A coolant flows into heat exchange contact with outer surfaces of said tubes. The outlet cross-sectional flow area for the evaporant, or rather its vapor, is variable so that the pressure of the evaporated medium, and thereby also its evaporation temperature are adjustable. The adjustment of the cross-sectional flow area for the vapor is controlled in response to the temperature of the cooling liquid or coolant where it enters into a processing chamber of the heat exchanger. Selectively closable apertures in an end plate (52) serve for changing the outlet cross-section flow area for the vapor. The apertures are, at least partially, closable by flaps which are controlled by bimetal springs responsive to the temperature of the entering coolant.
摘要翻译： 例如，在零重力条件下的航天器中产生的热量和不同的加速度通过连接到至少一个主动冷却剂循环回路的蒸发热交换器排出。 热交换器具有轴向布置在圆柱形处理室内的一束管。 蒸发器通过这些管。 冷却剂流入与所述管的外表面的热交换接触。 蒸发器或其蒸气的出口横截面流动面积是可变的，使得蒸发介质的压力以及由此蒸发介质的蒸发温度是可调节的。 响应于其进入热交换器的处理室的冷却液体或冷却剂的温度来控制蒸汽的横截面流动面积的调节。 端板（52）中的可选择闭合的孔用于改变蒸气的出口横截面流动面积。 至少部分地，所述孔可以通过响应于进入的冷却剂的温度的双金属弹簧控制的襟翼来关闭。
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公开(公告)号：US5246061A
公开(公告)日：1993-09-21
申请号：US921345
申请日：1992-07-29
申请人： Edgar P. Zalite
发明人： Edgar P. Zalite
摘要： Water coolant circulating in a closed loop may be cooled by passing it through a heat exchanger coil embedded within a block of heavy water ice. The ice will maintain the water, passing through the coil, at a temperature approximately 39.degree. F. Maintenance of the working fluid at this temperature prevents it from freezing in coolant tubes. The system is particularly adapted for a liquid cooling space garment which must effectively conduct away heat from an astronaut's body when an astronaut exerts himself during physical activity.
摘要翻译： 在闭环中循环的水冷却剂可以通过将其通过嵌入在重水冰块内的热交换器盘管来冷却。 在大约39°F的温度下，冰将保持水通过线圈。工作流体在此温度下的维护防止其在冷却剂管中冻结。 该系统特别适用于液体冷却空间服装，当航天员在身体活动期间发挥自身时，必须有效地从宇航员的身体散发热量。
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公开(公告)号：US5176326A
公开(公告)日：1993-01-05
申请号：US627334
申请日：1990-12-14
IPC分类号： B64G1/50
摘要： A fluid ejection nozzle is disclosed which facilitates a wide distribution of fluid therefrom and which permits the fluid flow rate to be easily adjustable. The nozzle is particularly adapted to a heat rejection system useful in a space environment. The nozzle includes a flow distributor positioned within an orifice of the nozzle housing which is comprised of a tongue member and an attached flow control block. Adjustment screws mounted through the nozzle housing permit axial movement of the flow distributor within the housing, thus controlling the flow rate of the fluid even to the extent of total shut-off. The tongue member is shaped to widely disperse the fluid, and includes turbulence generators such as roughening or ridges for facilitating its dispersion.
摘要翻译： 公开了一种流体喷射喷嘴，其有利于流体的广泛分布，并且允许流体流速容易调节。 喷嘴特别适用于在空间环境中有用的散热系统。 喷嘴包括位于喷嘴壳体的孔口内的流量分配器，该喷嘴壳体由舌片构件和附接的流量控制块组成。 通过喷嘴壳体安装的调节螺钉允许流动分配器在壳体内的轴向运动，从而控制流体的流速甚至达到全关闭的程度。 舌部件成形为使流体广泛分散，并且包括湍流发生器，例如粗糙化或脊部，以便于其分散。
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公开(公告)号：US5117901A
公开(公告)日：1992-06-02
申请号：US649603
申请日：1991-02-01
申请人： Brent A. Cullimore
发明人： Brent A. Cullimore
CPC分类号： F28D15/043 , B64G1/50 , B64G1/503 , F28D15/0208
摘要： A two-phase capillary pumped loop heat transfer system adapted primarily for use on space vehicles, includes a wickless condenser tube which receives gaseous phase working fluid from the evaporator capillaries, rejects heat from the working fluid to a heat sink (e.g. outer space) and thereby converts the gaseous phase working fluid to its liquid phase, and returns the liquid phase working fluid to the evaporator to complete the thermal cycle. A portion of the condenser tube is supported by a rigid radiator structure external to the spacecraft. At least a portion of the condenser tube is deformable to permit the radiator structure to be deployed from a first predetermined position to a second predetermined position with respect to the spacecraft. The deformable segment of the condenser tube can be formed into a helical coil used as a spring to assist deployment of the radiator panel.
摘要翻译： 主要适用于太空车辆的两相毛细管泵浦回路传热系统包括一个无烟冷凝器管，其从蒸发器毛细管接收气相工作流体，将热量从工作流体排除到散热器（例如外部空间），以及 从而将气相工作流体转化为液相，并将液相工作流体返回到蒸发器以完成热循环。 冷凝器管的一部分由在航天器外部的刚性散热器结构支撑。 冷凝器管的至少一部分是可变形的，以允许散热器结构相对于航天器从第一预定位置展开到第二预定位置。 冷凝器管的可变形部分可以形成为用作弹簧的螺旋线圈，以帮助散热器面板的展开。
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公开(公告)号：US5062472A
公开(公告)日：1991-11-05
申请号：US356055
申请日：1989-05-23
IPC分类号： B64G1/50
CPC分类号： F28D15/00 , B64G1/50 , B64G1/503 , Y10S165/904
摘要： Disclosed is an advantageous system for heat rejection especially useful in the space environment.
摘要翻译： 公开了一种在空间环境中特别有用的散热的有利系统。
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公开(公告)号：US5038693A
公开(公告)日：1991-08-13
申请号：US410576
申请日：1989-09-21
CPC分类号： B32B15/04 , B32B5/26 , B64G1/58 , D02G3/46 , F16L59/026 , B64G1/503 , Y10S57/903 , Y10T428/2933 , Y10T428/2936 , Y10T442/138 , Y10T442/159 , Y10T442/654 , Y10T442/682
摘要： Composite flexible multilayer insulation systems (MLI) were evaluated for thermal performance and compared with currently used fibrous silica (baseline) insulation system. The systems described are multilayer insulations consisting of alternating layers of metal foil and scrim ceramic cloth or vacuum metallized polymeric films quilted together using ceramic thread. A silicon carbide thread for use in the quilting and the method of making it are also described. These systems are useful to provide lightweight thermal insulation for a variety of uses, particularly on the surface of aerospace vehicles subject to very high temperatures during flight.
摘要翻译： 评估复合柔性多层绝缘系统（MLI）的热性能，并与目前使用的纤维二氧化硅（基线）绝缘系统进行比较。 所描述的系统是由金属箔和稀松布陶瓷布的交替层或使用陶瓷线绗缝在一起的真空金属化聚合物膜组成的多层绝缘体。 还描述了用于绗缝的碳化硅线及其制造方法。 这些系统可用于为各种用途提供轻质的隔热材料，特别是在飞行中受极高温度影响的航空航天飞机表面。
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公开(公告)号：US4957157A
公开(公告)日：1990-09-18
申请号：US337774
申请日：1989-04-13
申请人： Mack W. Dowdy , Doanld J. Benko
发明人： Mack W. Dowdy , Doanld J. Benko
CPC分类号： F28D15/043 , B64G1/50 , B64G1/506 , B64G1/503 , F28F2200/005
摘要： A closed-loop two-phase thermal control loop includes an evaporator which receives subcooled coolant liquid from a condenser and heat from a source, and vaporizes the coolant to form coolant vapor. A condenser which is coupled to a thermal radiator accepts the coolant vapor and radiates thermally to space, thereby condensing the coolant vapor to liquid and subcooling the liquid. As the temperature of the environment surrounding the condenser radiator changes, the mass of vapor within the system tends to change, thereby causing undesirable pressure changes. A spherical wicked coolant reservoir is coupled to the liquid side of the closed thermal control loop. The reservoir is exposed foro thermal radiation and electrically heated, so that the temperature is thereby controlled in order to control vapor pressure within the reservoir. By controlling the reservoir vapor pressure, small pressure differentials are generated, which cause coolant liquid to be accepted or expelled while maintaining the closed loop pressure. The reservoir includes a wick for maintaining liquid coolant adjacent heat transfer areas, and also includes a standpipe supporting shaped vanes. The coolant adheres to the vanes and to the wick under zero-gravity conditions in a manner which allows at least partial simulation in an Earth gravity.
摘要翻译： 闭环两相热控制回路包括一个蒸发器，该蒸发器从冷凝器接收过冷却的冷却剂液体和来自源的热量，并蒸发冷却剂以形成冷却剂蒸气。 耦合到散热器的冷凝器接收冷却剂蒸汽并且热辐射到空间，从而将冷却剂蒸汽冷凝成液体并使液体过冷。 随着冷凝器散热器周围环境的温度变化，系统内的蒸汽质量趋于变化，从而导致不希望的压力变化。 球形的邪恶的冷却剂储存器联接到闭合的热控制回路的液体侧。 储存器暴露于热辐射和电加热，从而控制温度以控制储存器内的蒸汽压力。 通过控制储层蒸汽压力，产生小的压力差，这导致冷却剂液体在保持闭环压力的同时被接受或排出。 储存器包括用于将液体冷却剂保持在传热区域附近的芯，并且还包括支撑成形叶片的立管。 在零重力条件下，冷却剂以能够在地球重力中至少部分模拟的方式粘附到叶片和油绳。
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78.发明授权Method and composition for providing electrostatic discharge protection for spacecraft 失效为航天器提供静电放电保护的方法和组成
公开(公告)号：US4910050A
公开(公告)日：1990-03-20
申请号：US228370
申请日：1988-08-04
申请人： Susan L. Oldham , Desiree S. Prior
发明人： Susan L. Oldham , Desiree S. Prior
IPC分类号： B64G1/50 , B64G1/52 , C08K3/22 , C08K3/34 , C08K3/38 , C08K5/05 , C08K5/057 , C08K5/09 , C08K5/098 , C08K5/54 , C08K5/5419
CPC分类号： C08K5/54 , B64G1/52 , C08K3/38 , C08K5/057 , C08K5/098 , Y10T428/31511 , Y10T428/3154 , Y10T428/31663 , Y10T428/31721 , Y10T428/31786
摘要： A method and composition which provides both thermal; control and electrostatic discharge protection to bodies in the space environment. The composition comprises: (a) a chosen polymer or resin that forms a polymer that is an electronic insulator and is suitable for space applications; and (b) a selected lithium salt as a dopant wherein said composition, when formed into a film or coating, provides a semiconductive film or coating having a volume resistivity of about 10.sup.6 to 10.sup.11 ohm-centimeter and a value of solar absorptance/total normal emittance within the range of about 0.305 to 0.595. In an alternative embodiment, the composition may optionally include tantalum pentoxide.
摘要翻译： 提供热量的方法和组合物; 控制和静电放电保护到空间环境中的物体。 该组合物包括：（a）选择的形成聚合物的聚合物或树脂，其是电子绝缘体并且适用于空间应用; 和（b）选择的锂盐作为掺杂剂，其中当形成膜或涂层时，所述组合物提供具有约106至1011欧姆厘米的体积电阻率和太阳吸收率/总正常值的半导体膜或涂层 发射率在约0.305至0.595的范围内。 在替代实施方案中，组合物可以任选地包括五氧化二钽。
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公开(公告)号：US4880050A
公开(公告)日：1989-11-14
申请号：US208440
申请日：1988-06-20
CPC分类号： F28D15/0233 , B64G1/50 , B64G1/503 , B64G1/506 , F28D15/0266
摘要： A thermal management system for a spacecraft includes a plurality of T-shaped pallets each having a radiator panel and mounting panel. The radiator panels are connected end to end to enclose an interior space including the mounting panels. The mounting panels have electronic equipment mounted thereon. L-shaped external heat pipes contact both the mounting panel and radiator panel of each pallet to provide heat transfer from the electronic equipment to the radiator panel when the radiator panel is facing away from the sun. In order to cool the electronic equipment mounted on a pallet facing the sun, a closed-loop heat pipe is disposed in the interior space and each pallet inclues L-shaped internal heat pipes contacting the closed-loop heat pipe and the mounting panel. Heat generated in the electronic equipment of the pallet facing the sun is transferred to the internal heat pipes via the mounting panel and then to the closed-loop heat pipe. The heat then is transferred to the radiator panels facing away from the sun via the closed-loop heat pipe, the internal heat pipes, the mounting panels, and the external heat pipes. In one embodiment, the mounting panels are comprised of a pair of spaced-apart mounting plates, and the legs of the external and internal L-shaped heat pipes contacting the mounting panel are disposed within this space separating the mounting plates.
摘要翻译： 用于航天器的热管理系统包括多个具有散热器面板和安装面板的T形托盘。 散热器面板端对端连接以包围包括安装面板的内部空间。 安装面板上安装有电子设备。 L型外部热管接触每个托盘的安装面板和散热器面板，以在散热器面板远离太阳时提供从电子设备到散热器面板的热传递。 为了冷却安装在面向太阳的托盘上的电子设备，在内部空间设置闭环热管，每个托盘包括与闭环热管和安装面板接触的L形内部热管。 在面向太阳的托盘的电子设备中产生的热量经由安装面板传递到内部热管，然后传递到闭环热管。 然后，热量经由闭环热管，内部热管，安装面板和外部热管传递到面向远离太阳的散热器面板。 在一个实施例中，安装面板由一对间隔开的安装板组成，并且与安装面板接触的外部和内部L形热管的腿设置在分离安装板的该空间内。
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公开(公告)号：US4756493A
公开(公告)日：1988-07-12
申请号：US904325
申请日：1986-09-08
申请人： Timothy L. Camaret
发明人： Timothy L. Camaret
CPC分类号： B64G1/503 , B64G1/50 , Y10T29/49355
摘要： A deployment system for controlling unfolding kinematics of radiator panels 26 of a space power system. The deployment system includes a plurality of forming mandrels 30 associated with a housing 38 of opposing generally triangular plates 40. Within the housing, a drive wheel 52 and two additional guide wheels 50 interact with the mandrels to effect predetermined deflection and deployment of the multiple radiator panels.
摘要翻译： 一种用于控制空间电力系统的散热器面板26的展开运动的部署系统。 展开系统包括与相对的大致三角形板40的壳体38相关联的多个成形芯轴30.在壳体内，驱动轮52和两个额外的导向轮50与心轴相互作用以实现多个散热器的预定偏转和展开 面板。
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