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公开(公告)号：US20100327108A1
公开(公告)日：2010-12-30
申请号：US12745177
申请日：2008-11-21
申请人： Marco Prampolini
发明人： Marco Prampolini
摘要： An afterbody device for a spacecraft fitted with at least one rocket engine at the rear of the craft includes at least one movable cover element designed to take a first position, masking and reducing the vehicle's rear drag, where it prolongs the vehicle's fuselage around at least one part of a rocket engine nozzle of the vehicle and extends beyond the rear of the vehicle's fuselage, and to take a second position fully deployed, increasing the vehicle's aerodynamic drag.
摘要翻译： 用于在飞行器后部配备有至少一个火箭发动机的航天器的后体装置包括设计成采取第一位置的至少一个可移动盖元件，掩蔽并减少车辆的后阻力，其中至少延长了车辆的机身 车辆的火箭发动机喷嘴的一部分并且延伸超出车辆机身的后部，并且进行完全展开的第二位置，增加车辆的空气动力学阻力。
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公开(公告)号：US07762499B1
公开(公告)日：2010-07-27
申请号：US11528768
申请日：2006-09-28
申请人： David J. Hentosh , John Lafergola
发明人： David J. Hentosh , John Lafergola
IPC分类号： B64G1/50
摘要： A satellite thermal management system for dissipating excess heat generated within a satellite. The thermal management system includes a central platform for mounting heat dissipating components. A first thermal radiator panel and a second thermal radiator panel are mounted to the central platform. The first thermal radiator panel is arranged to face East when the satellite is in orbit. The second thermal radiator panel is arranged to face West when the satellite is in orbit. The first and second thermal radiator panels are thermally coupled to the central platform and are configured to radiate heat dissipated by the heat dissipating component mounted on the central platform.
摘要翻译： 用于消散卫星内产生的多余热量的卫星热管理系统。 热管理系统包括一个用于安装散热部件的中心平台。 第一散热器面板和第二散热器面板安装在中央平台上。 当卫星进入轨道时，第一个散热板面向东面。 卫星进入轨道时，第二个散热器散热板面向西面。 第一和第二散热器面板热耦合到中心平台并且被配置为辐射由安装在中心平台上的散热部件散发的热量。
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公开(公告)号：US06923249B1
公开(公告)日：2005-08-02
申请号：US10447971
申请日：2003-05-28
CPC分类号： B64G1/443 , B64G1/425 , B64G1/50 , B64G1/503 , B64G1/66 , H01M10/0525 , H01M10/465 , H01M10/625 , H01M10/647 , H01M10/6551 , H01M10/6554 , H01M10/658 , H01M10/667 , Y02E60/122
摘要： A passive thermal control system maintains the operating temperature range of protected equipment within desired limits by controlling the conductive attributes of thermal interfaces and physical relationships within the system so as to achieve a desired thermal balance. In one embodiment, an integrated cell unit (100) includes a solar array (102), a Lithium ion cell (108) and an antenna assembly (114) such as a phased array antenna. In operation, a thermal gradient (116) is defined between the array (102) and the assembly (114) as the assembly (114) radiates heat from the array (102) into space. The operating temperature range of the cell (108) is controlled by appropriate design of the thermal interfaces between the cell (108) and the assembly (114) and/or interfaces within the assembly (114), such as a thermal interface associated with dielectric spacers provided between emitter pairs of the assembly (114).
摘要翻译： 被动热控制系统通过控制系统内的热界面和物理关系的导电属性来将受保护设备的工作温度范围保持在期望的范围内，以达到所需的热平衡。 在一个实施例中，集成单元单元（100）包括太阳能阵列（102），锂离子电池（108）和诸如相控阵天线的天线组件（114）。 在操作中，随着组件（114）将热量从阵列（102）辐射到空间中，热梯度（116）被定义在阵列（102）和组件（114）之间。 电池（108）的工作温度范围通过电池（108）和组件（114）之间的热界面和/或组件（114）内的接口的适当设计来控制，例如与电介质相关的热界面 间隔件设置在组件（114）的发射极对之间。
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公开(公告)号：US20050151022A1
公开(公告)日：2005-07-14
申请号：US10755200
申请日：2004-01-09
CPC分类号： B64G1/007 , B64G1/405 , B64G1/422 , B64G1/503 , B64G1/506 , B64G1/646 , G21D5/02 , G21Y2002/203 , G21Y2002/304 , G21Y2004/30
摘要： An In Orbit Transportation & Recovery System (IOSTAR™) (10) is disclosed. One preferred embodiment of the present invention comprises a space tug powered by a nuclear reactor (19). The IOSTAR™ includes a collapsible boom (11) connected at one end to a propellant tank (13) which stores fuel for an electric propulsion system (12). This end of the boom (11) is equipped with docking hardware (14) that is able to grasp and hold a satellite (15) and as a means to refill the tank (13). Radiator panels (16) mounted on the boom (11) dissipate heat from the reactor (19). A radiation shield (20) is situated next to the reactor (19) to protect the satellite payload (15) at the far end of the boom (11). The IOSTAR™ (10) will be capable of accomplishing rendezvous and docking maneuvers which will enable it to move spacecraft between a low Earth parking orbit and positions in higher orbits or to other locations in our Solar System.
摘要翻译： 公开了轨道运输和恢复系统（IOSTAR（TM））（10）。 本发明的一个优选实施例包括由核反应堆（19）供电的空间拖船。 IOSTAR TM包括在一端连接到储存用于电力推进系统（12）的燃料的推进剂罐（13）的可折叠起重臂（11）。 起重臂（11）的这一端配备有能够把持和固定卫星（15）的对接硬件（14），并且作为重新装满水箱（13）的装置。 安装在起重臂（11）上的散热器面板（16）从反应器（19）散热。 辐射屏蔽（20）位于反应器（19）旁边，以保护在悬臂（11）的远端处的卫星有效载荷（15）。 IOSTAR（TM）（10）将能够实现会合和对接机动，这将使其能够在低地球停放轨道和较高轨道位置或太阳系中其他位置之间移动航天器。
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公开(公告)号：US20050029404A1
公开(公告)日：2005-02-10
申请号：US10489678
申请日：2002-09-18
CPC分类号： F16B5/0642 , B64C1/40 , F16L59/028
摘要： System for fixing an insulation blanket (2) to a panel (1). It comprises buttons (8), loops (9) with ends twisted together, and hooks (12) that can easily accommodate the loops (9) when the blanket (2) is already laid.
摘要翻译： 用于将绝缘层（2）固定到面板（1）的系统。 它包括按钮（8），端部扭曲在一起的环（9）和当毯子（2）已经铺设时可以容易地容纳环（9）的钩子（12）。
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公开(公告)号：US6111190A
公开(公告)日：2000-08-29
申请号：US040733
申请日：1998-03-18
申请人： Mark Joseph O'Neill
发明人： Mark Joseph O'Neill
IPC分类号： B64G1/44 , B64G1/50 , F24S23/30 , H01L31/052 , H01L31/045 , F24J2/36
CPC分类号： F24J2/085 , B64G1/443 , H01L31/0543 , H01L31/0547 , B64G1/503 , Y02E10/43 , Y02E10/52 , Y10S126/909
摘要： A novel, high-efficiency, extremely light-weight, inflatable refractive solar concentrator for space power is described. It consists of a flexible Fresnel lens, flexible sides, and a back surface, together enclosing a volume of space which can be filled with low pressure gas to deploy the concentrator on orbit. The back surface supports the energy receiver/converter located in the focal region of the Fresnel lens. The back surface can also serve as the waste heat radiator. Prior to deployment, the deflated flexible lens and sides are folded against the back surface to form a flat, low-volume package for efficient launch into space. The inflatable concentrator can be configured to provide either a line focus or a point focus of sunlight. The new inflatable concentrator approach will provide significant advantages over the prior art in two different space power areas: photovoltaic concentrator arrays and high-temperature solar thermal conversion systems. Photovoltaic concentrator arrays using the new inflatable lens will be much lighter than prior space concentrator arrays. In addition, for photovoltaic concentrator arrays, the new inflatable lens will eliminate the need for a fragile glass superstrate to support the lens, substantially improving robustness of the lens. Solar thermal concentrator arrays using the new inflatable lens will be much lighter than prior art space concentrators which used parabolic mirrors. In addition, for solar thermal applications in space, the new inflatable lens will eliminate the need for high surface accuracy, which has been a significant problem for prior art concentrators.
摘要翻译： 描述了一种用于空间动力的新颖，高效，极轻重量的充气折射式太阳能聚光器。 它由柔性菲涅尔透镜，柔性侧面和后表面组成，共同包围一定量的空间，可以充满低压气体以将集中器部署在轨道上。 后表面支撑位于菲涅尔透镜焦点区域的能量接收器/转换器。 背面也可以作为废热散热器。 在展开之前，放气的柔性透镜和侧面折叠在背面上以形成平坦的低容量包装，以有效地发射到太空中。 可充气聚光器可以被配置成提供阳光的线焦点或点聚焦。 在两个不同的空间电力领域中，新的充气聚光器方法将比现有技术显着优点：光伏聚光器阵列和高温太阳能热转换系统。 使用新的充气镜头的光伏集中器阵列将比以前的空间集中器阵列轻得多。 此外，对于光伏聚光器阵列，新的充气镜头将不需要一个易碎的玻璃底板来支撑透镜，从而显着改善透镜的坚固性。 使用新的充气镜头的太阳能集热器阵列将比使用抛物面镜的现有技术的空间集中器轻得多。 另外，对于空间太阳能热应用，新的充气镜头将消除对高表面精度的需要，这对于现有技术的聚光器来说是一个重大的问题。
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47.发明授权Sun-synchronous sun ray blocking device for use in a spacecraft having a directionally controlled main body 失效用于具有定向控制主体的航天器的太阳同步太阳光线阻挡装置
公开(公告)号：US6102339A
公开(公告)日：2000-08-15
申请号：US62594
申请日：1998-04-17
申请人： Albert T. Wu , Linchih O. Liu
发明人： Albert T. Wu , Linchih O. Liu
摘要： A sun-synchronous sun ray blocking device for use in a spacecraft having a directionally controlled main body, such as a low inclination angle earth (as well as other planets) orbit spacecraft, that is, a three axis stabilized spacecraft having north, south, east, west, earth and anti-earth panels defining a spacecraft main body. The north and south panels, on which the spacecraft equipment with high heat dissipation is usually mounted, have their planar normal axes relatively parallel to the spinning axis of the earth. Normal to each of the north and south panel, a solar panel loaded with solar cells is extended and is directly rotating about the same axis. The solar panels are controlled in such a way that the solar cells side of the panels always faces the sun. Each solar panel's blocking device is situated between the solar panel and sun, attached to its solar panel and rotated therewith, to block the sunlight from the north and south panels, providing a stable, benign thermal environment for those panels.
摘要翻译： 一种用于具有定向控制主体的太阳同步太阳光线阻挡装置，例如低倾角地球（以及其它行星）轨道航天器，即具有北，南， 东，西，土和反对面板，定义了航天器主体。 通常安装有高散热的航天器设备的北面和南面的平面法线与地球的旋转轴线相对平行。 正常到北面和南面的每一个，装有太阳能电池的太阳能电池板被延伸并且绕同一个轴线直接旋转。 太阳能电池板的控制方式使得面板的太阳能电池板面总是面向太阳。 每个太阳能电池板的阻挡装置位于太阳能电池板和太阳之间，连接到其太阳能电池板并与其一起旋转，以阻挡来自北面和南面的太阳光，为这些面板提供稳定的良性热环境。
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48.发明授权(Zinc,cadmium,magnesium) aluminate-gallate-containing paints and their use on spacecraft 有权（锌，镉，镁）铝酸盐 - 没食子酸酯的油漆及其在航天器上的应用
公开(公告)号：US6099637A
公开(公告)日：2000-08-08
申请号：US145697
申请日：1998-09-02
申请人： James F. Cordaro
发明人： James F. Cordaro
CPC分类号： C09D7/1216 , B64G1/226 , B64G1/50 , B64G1/503 , B64G1/58 , C09C1/40 , C09D1/02 , C09D5/24 , C01P2002/32 , C01P2002/54 , C01P2004/61 , C01P2004/62 , C01P2006/60 , C08K3/22
摘要： A paint is a liquid or solid mixture of a plurality of particles and an inorganic binder such as a silicate. The particles have a composition A[xAl(1-x)Ga].sub.2 O.sub.4.+-..gamma. (.delta.In), wherein A is zinc, magnesium and/or cadmium, the value of x is from 0 to 1, the value of .delta. is from 0 to about 0.2, and the value of .gamma. is less than about 0.2. In the liquid mixture, a paint vehicle is also typically present to impart the desired fluidity to the mixture. The solid paint made using this material is white, has very low solar absorptance, and may be made electrically conductive by doping the particles with indium or other appropriate dopant.
摘要翻译： 涂料是多种颗粒和无机粘合剂如硅酸盐的液体或固体混合物。 颗粒具有组成A [xAl（1-x）Ga] 2O4 +/-γ（δIn），其中A是锌，镁和/或镉，x的值为0至1，δ的值为 从0到约0.2，并且γ值小于约0.2。 在液体混合物中，还通常存在涂料载体以赋予混合物所需的流动性。 使用这种材料制成的固体涂料是白色的，具有非常低的太阳能吸收率，并且可以通过用铟或其它合适的掺杂剂掺杂颗粒而导致导电。
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公开(公告)号：US6098931A
公开(公告)日：2000-08-08
申请号：US104199
申请日：1998-06-25
申请人： Max Bard
发明人： Max Bard
摘要： A satellite, especially a geostationary satellite, which includes: at least one face (5) which is used as a thermal radiator for the equipment carried on board the satellite (1) and is arranged in the path of the solar radiation (9); at least one solar panel (7) which is a generator of electricity, which is pointed continuously toward the sun and projects from the face (5); and a screen (14) secured to the solar panel (7), which is arranged at the periphery of the satellite and which stops the solar radiation (9) directed toward the face (5). The satellite is noteworthy in that the solar panel (7) is arranged centrally with respect to the face (5) and the screen (14) is secured to the solar panel (7) by an arm (15).
摘要翻译： 一种卫星，特别是对地静止卫星，其包括：至少一个面（5），其被用作卫星（1）上携带的设备的散热器，并被布置在太阳辐射（9）的路径中。 至少一个太阳能电池板（7），其是电力发生器，其朝向太阳连续指向并且从所述表面（5）突出; 以及固定到所述太阳能电池板（7）的屏幕（14），所述屏幕布置在所述卫星的周围，并且停止指向所述面部（5）的太阳辐射（9）。 卫星是值得注意的，因为太阳能面板（7）相对于面（5）居中设置，并且屏幕（14）通过臂（15）固定到太阳能面板（7）。
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公开(公告)号：US5833175A
公开(公告)日：1998-11-10
申请号：US577447
申请日：1995-12-22
申请人： Glenn Caplin
发明人： Glenn Caplin
CPC分类号： B64G1/66 , B64G1/10 , B64G1/503 , B64G1/1007 , B64G2001/1092
摘要： A spacecraft body configuration having east and west sides which are greater in length than the body's north and south sides. The east and west sides each have antennas which extend from one end of each of said east and west sides to the other end of each of said east and west sides. The north and south sides have radiators. The longer east-west side configuration may be used not only to accommodate larger east-west side antennas, but also to accommodate deployable radiators on the north and south sides.
摘要翻译： 东，西两侧的航天器身体结构长度大于身体的南北两侧。 东，西两侧各自具有从所述东西两端的每一端延伸到所述东西两侧的另一端的天线。 南北两侧有散热器。 较长的东西侧配置不仅可用于容纳更大的东西侧天线，还可用于在北侧和南侧容纳可部署的散热器。
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