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公开(公告)号：US06073888A
公开(公告)日：2000-06-13
申请号：US203710
申请日：1998-12-02
摘要： In one embodiment, a thermal radiative system for an earth orbiting satellite including a plurality of faces intermittently exposed to maximum solar illumination comprises a thermal radiator is mounted on a face for discharging heat from a thermal load to deep space. A heat conductor extends between the thermal load and the thermal radiator. Thermal switches are operable for connecting the thermal load to the thermal radiator for cooling when the temperature of the thermal load is above a predetermined level and for disconnecting the thermal load from the thermal radiator when the temperature of the thermal load falls below the predetermined level. A shield including phase change management (PCM) material is thermally connected to the thermal load for drawing heat away therefrom. In another embodiment, first and second thermal radiators are mounted on first and second faces, respectively, of the satellite for discharging heat from the thermal load and the thermal load is sequentially connected to the first and second thermal radiators to achieve optimum discharge of heat from the thermal load. To this end, the thermal load is thermally connected to the first radiator so long as the first radiator is exothermic and thermally disconnected from the first radiator when the first radiator becomes endothermic and is thermally connected to the second radiator so long as the second radiator is exothermic and thermally disconnected from the second radiator when the second radiator becomes endothermic.
摘要翻译： 在一个实施例中，用于地球轨道卫星的热辐射系统包括间歇地暴露于最大太阳照射的多个面包括热辐射器安装在用于将热量从热负载释放到深空间的面上。 热导体在热负载和散热器之间延伸。 当热负荷的温度高于预定水平时，热开关可操作用于将热负荷连接到散热器以进行冷却，并且当热负荷的温度降到预定水平以下时，将热负荷与热辐射器断开。 包括相变管理（PCM）材料的屏蔽件热连接到热负载以将热量从其中吸出。 在另一个实施例中，第一和第二热辐射器分别安装在卫星的第一和第二面上，用于从热负荷排出热量，并且热负载依次连接到第一和第二热辐射器，以实现从 热负荷。 为此，热负荷与第一散热器热连接，只要第一散热器与第一散热器放热并与第一散热器热断开时，第一散热器变热吸热并且热连接到第二散热器，只要第二散热器是 当第二辐射体成为吸热时，与第二散热器放热并热断开。
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公开(公告)号：US06196501B1
公开(公告)日：2001-03-06
申请号：US09168029
申请日：1998-10-07
申请人： John C. Hall , Walter S. Gelon , Robert E. Helmer
发明人： John C. Hall , Walter S. Gelon , Robert E. Helmer
IPC分类号： B64G150
摘要： A spacecraft comprises a first module including a first assembly of components and a second module including a second assembly of components and a thermal radiator. The second module is movable between a stowed position proximate the first module whereat the thermal radiator is only partially operative and a deployed position distant from the first module whereat the thermal radiator means is fully operative for dissipating waste heat to deep space for at least one of the first and second assemblies of components. In one embodiment, the first module includes a housing defining an interior cavity, the second module including a casing so shaped and dimensioned as to be telescopically received within the internal cavity of the first module and the second module being translationally movable along a deploying axis between the stowed position and the deployed position but incapable of mutual rotation about the deploying axis. In another embodiment, a spacecraft includes a plurality of discrete faces and comprises an equipment panel including an assembly of heat generating components which require cooling, a thermal radiator, and a connecting hinge mounting the equipment panel for pivotal movement between a stowed position proximate one of said faces whereat the thermal radiator is only partially operative and a deployed position distant from the face whereat said thermal radiator means is fully operative for dissipating waste heat from the assembly to deep space.
摘要翻译： 航天器包括第一模块，其包括部件的第一组件和包括部件的第二组件和散热器的第二模块。 第二模块可以在靠近第一模块的收起位置之间移动，其中热散热器仅部分地操作，并且远离第一模块的展开位置，其中散热器装置完全可操作，以将废热散发到深空，用于至少一个 组件的第一和第二组件。 在一个实施例中，第一模块包括限定内腔的壳体，第二模块包括壳体，其形状和尺寸设计成可伸缩地容纳在第一模块的内腔内，并且第二模块可沿着展开轴线平移移动， 收起位置和部署位置，但不能围绕部署轴线相互旋转。 在另一个实施例中，航天器包括多个离散面，并且包括设备面板，其包括需要冷却的发热组件的组件，散热器和安装设备面板的连接铰链，用于在靠近其中之一的收起位置之间枢转运动 所述的表面，其中散热器仅仅部分地操作，并且远离所述散热器装置的表面的展开位置完全可操作以将废热从组件散发到深空。
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公开(公告)号：US06207315B1
公开(公告)日：2001-03-27
申请号：US09097556
申请日：1998-06-15
申请人： Walter S. Gelon , John C. Hall
发明人： Walter S. Gelon , John C. Hall
IPC分类号： H01M210
CPC分类号： H01M2/10 , B64G1/425 , B64G1/503 , B64G1/506 , H01M10/345 , H01M10/613 , H01M10/617 , H01M10/627 , H01M10/6551 , H01M10/6552 , Y02E10/542 , Y02E60/124
摘要： A spacecraft battery system arranges battery cells in two planes with a common mounting plate between them allowing for a more compact arrangement so the battery assembly can be removed from a limited mounting area resource of the spacecraft such as the north/south faces and placed remotely. Accordingly, a first battery assembly comprised of a plurality of battery cells in electrical continuity are mounted on and spread in a single plane over a first mounting surface of a planar mounting panel and a similarly constructed second battery assembly is mounted on and spread in a single plane over a second, opposed, mounting surface of that same planar mounting panel, the plane of the second battery assembly being spaced from the plane of the first battery assembly. The system includes a plurality of heat pipes embedded in the planar mounting panel and thermally connected with each of the battery cells for distributing heat uniformly across the planar mounting panel. The system also desirably includes a thermal radiator for radiating heat to deep space and heat conducting means thermally connecting the planar mounting panel to the thermal radiator means for drawing heat away from the planar mounting panel and to the thermal radiator means.
摘要翻译： 航天器电池系统将电池单元布置在两个平面之间，其间具有公共安装板，从而允许更紧凑的布置，使得电池组件可以从诸如北/南面的航天器的有限的安装区域资源移除并远程放置。 因此，由具有电连续性的多个电池单元组成的第一电池组件安装在平面安装面板的第一安装表面上并在单个平面上展开，并且类似构造的第二电池组件安装在单个面 平面在同一平面安装面板的第二相对的安装表面上，第二电池组件的平面与第一电池组件的平面间隔开。 该系统包括嵌入在平面安装面板中并与每个电池单元热连接的多个热管，用于均匀地分布在平面安装面板上。 该系统还期望地包括用于将热量散发到深空间的热辐射器和将平面安装面板热连接到散热器装置的热传导装置，用于将热量从平面安装板和散热器装置吸走。
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公开(公告)号：US5957408A
公开(公告)日：1999-09-28
申请号：US985452
申请日：1997-12-05
申请人： John C. Hall , Walter S. Gelon
发明人： John C. Hall , Walter S. Gelon
CPC分类号： B64G1/503 , B64G1/425 , B64G1/428 , B64G1/50 , F28D15/06 , H01M10/465 , H01M10/613 , H01M10/625 , H01M10/633 , H01M10/6551 , H01M10/6554
摘要： A battery system for an body stabilized satellite traveling in a geosynchronous orbit comprises east and second battery modules and similarly facing radiators for discharging beat to deep space. Heat conduction arteries connect each battery module to its associated radiator. An east thermal switch is operable for thermally connecting the first battery module to and from the east facing radiator. Similarly, a west thermal switch is operable for thermally connecting the second battery module to and from the west facing radiator. A computer selectively operates the east and west thermal switches such that, in one instance, for a time between the satellite's emergence from the earth's shadow and its position nearest the sun, the respective thermal switches thermally connect the first battery module to its radiator while thermally disconnecting the second battery module from its radiator. In another instance, beginning when the satellite is nearest the sun and ending as it enters the earth's shadow, the east thermal switch thermally disconnects the first battery module from its radiator while the west thermal switch thermally connects the second battery module to its radiator. In still another instance, beginning when the satellite is in the shadow of the earth, the battery modules are simultaneously thermally connected to their associated radiators. Charging of each battery proceeds while it is thermally connected to its respective radiator.
摘要翻译： 用于在地球同步轨道中行进的身体稳定的卫星的电池系统包括东电池模块和第二电池模块以及用于将节拍放到深空间的类似的面对的散热器。 热传导动脉将每个电池模块连接到其相关散热器。 东部热开关可操作用于将第一电池模块与东面散热器热连接。 类似地，西热开关可操作用于将第二电池模块与西面向散热器热连接。 计算机选择性地操作东西热电开关，使得在一种情况下，在卫星从地球的阴影出现到最靠近太阳的位置之间的时间内，相应的热开关将第一电池模块热连接到其散热器，同时热 从其散热器断开第二个电池模块。 在另一种情况下，当卫星离太阳最近并且随着进入地球的阴影而结束时，东热交换器将第一电池模块与其散热器热断开，而西热交换器将第二电池模块热连接到其散热器。 在另一种情况下，当卫星处于地球阴影时，电池模块同时热连接到它们相关联的散热器。 每个电池在与其各自的散热器热连接时进行充电。
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公开(公告)号：US08789796B2
公开(公告)日：2014-07-29
申请号：US13101944
申请日：2011-05-05
申请人： Joel Francis Boccio , Gerrit Van Ommering , Walter S. Gelon , Steven Daniel Perez , Eric V. Werner
发明人： Joel Francis Boccio , Gerrit Van Ommering , Walter S. Gelon , Steven Daniel Perez , Eric V. Werner
CPC分类号： H01Q1/288 , B64G1/1007 , B64G1/222 , B64G1/641 , B64G1/66 , H01Q1/08 , H01Q15/161 , H01Q19/132
摘要： A high capacity broadband service is provided from an Earth orbiting satellite having a payload that includes multiple large antennas, the satellite having an inverted configuration when deployed on orbit. The satellite has an aft surface proximate to a launch vehicle structural interface, a forward surface opposite to said aft surface, and a structure disposed therebetween. In a launch configuration, two or more deployable antennas are disposed, undeployed, on or proximate to and forward of the forward surface; on-orbit, the payload is operable when the satellite is disposed with the aft surface substantially Earth facing while the forward surface is substantially facing in an anti-Earth direction. Each deployable antenna is disposed, so as to be Earth facing, when deployed, in a position substantially forward and outboard of the forward surface.
摘要翻译： 来自具有包括多个大天线的有效载荷的地球轨道卫星提供高容量宽带服务，该卫星在部署在轨道上时具有倒置配置。 卫星具有靠近运载火箭结构界面的后表面，与所述后表面相对的前表面，以及设置在其间的结构。 在发射配置中，两个或多个可展开的天线被放置在前表面上或靠近和向前的前表面上，未被部署; 在轨道上，当卫星被设置成具有大致面向地面的后表面时，有效载荷可操作，同时前表面基本上面向反地球方向。 每个可部署的天线被布置成在部署时面向地面，位于前表面的大致向前和向外的位置。
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公开(公告)号：US09248922B1
公开(公告)日：2016-02-02
申请号：US13215932
申请日：2011-08-23
IPC分类号： B64G1/22
CPC分类号： B64G1/222
摘要： A high capacity satellite having a launch configuration in which one or more antenna reflectors may be stored forward of a forward surface of the spacecraft and an on-orbit configuration in which a reflector boom may be rotated to displace the one or more antenna reflectors a substantial distance from the main body in the yaw axis direction and in a direction orthogonal to the yaw axis direction.
摘要翻译： 具有发射配置的高容量卫星，其中一个或多个天线反射器可以在航天器的前表面的前方存储，并且在轨配置中，反射器臂可以旋转以使一个或多个天线反射器移位， 在偏航轴方向和与偏转轴方向正交的方向上离开主体的距离。
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公开(公告)号：US20120068019A1
公开(公告)日：2012-03-22
申请号：US13101944
申请日：2011-05-05
申请人： Joel Francis Boccio , Gerrit Van Ommering , Walter S. Gelon , Steven Daniel Perez , Eric V. Werner
发明人： Joel Francis Boccio , Gerrit Van Ommering , Walter S. Gelon , Steven Daniel Perez , Eric V. Werner
CPC分类号： H01Q1/288 , B64G1/1007 , B64G1/222 , B64G1/641 , B64G1/66 , H01Q1/08 , H01Q15/161 , H01Q19/132
摘要： A high capacity broadband service is provided from an Earth orbiting satellite having a payload that includes multiple large antennas, the satellite having an inverted configuration when deployed on orbit. The satellite has an aft surface proximate to a launch vehicle structural interface, a forward surface opposite to said aft surface, and a structure disposed therebetween. In a launch configuration, two or more deployable antennas are disposed, undeployed, on or proximate to and forward of the forward surface; on-orbit, the payload is operable when the satellite is disposed with the aft surface substantially Earth facing while the forward surface is substantially facing in an anti-Earth direction. Each deployable antenna is disposed, so as to be Earth facing, when deployed, in a position substantially forward and outboard of the forward surface.
摘要翻译： 来自具有包括多个大天线的有效载荷的地球轨道卫星提供高容量宽带服务，该卫星在部署在轨道上时具有倒置配置。 卫星具有靠近运载火箭结构界面的后表面，与所述后表面相对的前表面，以及设置在其间的结构。 在发射配置中，两个或多个可展开的天线被布置在前表面上或靠近和向前的前表面上，未被部署; 在轨道上，当卫星被设置成具有大致面向地面的后表面时，有效载荷可操作，同时前表面基本上面向反地球方向。 每个可部署的天线被布置成在部署时面向地面，位于前表面的大致向前和向外的位置。
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公开(公告)号：US6032904A
公开(公告)日：2000-03-07
申请号：US27668
申请日：1998-02-23
摘要： A three-axis stabilized spacecraft having roll, pitch, and yaw axes and when on station in orbit about the earth having a north face and a south face is equipped with a first and second thruster which may be electric thrusters. A first support device mounts the first thruster adjacent the north face and the first thruster is positioned a spaced distance away from the north face in a first direction parallel to the pitch axis and spaced from the pitch axis in a second direction normal to the pitch axis. A second support device mounts the second thruster adjacent the south face, the second thruster being positioned a spaced distance away from the south face in a third direction opposite the first direction and spaced from the pitch axis in the second direction. A gimbal mechanism pivotally mounts the first and second thrusters on the first and second support devices, respectively, for selectively positioning the attitude of the first and second thrusters. The spacecraft includes a system for performing one or more operations including the following: thrusting along the yaw axis to assist in reaching a geosynchronous orbit; reducing the stored angular momentum of the momentum wheels; and north-south station keeping of the spacecraft.
摘要翻译： 具有滚动，俯仰和偏航轴的三轴稳定的航天器，并且当在具有北面和南面的地球轨道上的站上配备有可以是电推进器的第一和第二推进器。 第一支撑装置将第一推进器安装在北面附近，并且第一推进器在平行于桨距轴线的第一方向上与北面隔开距离定位，并且在垂直于桨距轴线的第二方向上与俯仰轴线间隔开 。 第二支撑装置将第二推进器安装在南面附近，第二推进器在与第一方向相反的第三方向上与南面隔开距离定位，并且在第二方向上与俯仰轴线间隔开。 万向架机构将第一和第二推进器分别枢转地安装在第一和第二支撑装置上，用于选择性地定位第一和第二推进器的姿态。 航天器包括用于执行包括以下的一个或多个操作的系统：沿着偏航轴线推进以帮助达到地球同步轨道; 减少动量轮存储的角动量; 和航天器的南北站。
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