公开(公告)号：US20110108670A1

公开(公告)日：2011-05-12

申请号：US12912515

申请日：2010-10-26

申请人： Silvain Legrand ,  Yannick Baudasse

发明人： Silvain Legrand ,  Yannick Baudasse

IPC分类号： B64G1/42 ,  B64G1/44

CPC分类号： B64G1/222 ,  B64G1/443 ,  B64G1/645

摘要： The present invention consists of an active tie-rod device making it possible to hold and smoothly release space appendages. The active tie-rod device includes a fixed base, an active tie-rod screwed into the said fixed base, a retractable release mechanism for the active tie-rod making it possible, in the stowed position, to hold the said active tie-rod in place, and a nut for tensioning the assembly. The active tie-rod includes an internal heater, and consisting at least partially of a material with a high coefficient of thermal expansion, so that, under the action of the internal heater, the active tie-rod can expand, retracting the retractable release mechanism for the active tie-rod, and consequently allowing the smooth release of the said space appendages.

摘要翻译： 本发明包括一种主动式拉杆装置，其可以保持和平稳地释放空间附件。 主动式拉杆装置包括固定底座，螺纹连接到所述固定底座中的活动连杆，用于主动式拉杆的可伸缩释放机构，使得在收起位置可以将所述主动拉杆 到位，以及用于张紧组件的螺母。 有源连杆包括内部加热器，并且至少部分地由具有高热膨胀系数的材料构成，使得在内部加热器的作用下，主动拉杆可以膨胀，缩回可伸缩释放机构 用于主动式拉杆，从而允许所述空间附件的平稳释放。

公开(公告)号：US07832688B2

公开(公告)日：2010-11-16

申请号：US12559246

申请日：2009-09-14

申请人： Neil E. Goodzeit

发明人： Neil E. Goodzeit

IPC分类号： B64G1/42

CPC分类号： B64G1/24 ,  B64G1/1007 ,  G05D1/0883

摘要： A spacecraft may include a receive antenna, a transmit antenna having an antenna attitude adjuster, and a spacecraft attitude adjustor. The spacecraft may have a nominal orientation in which a yaw axis of the spacecraft, a roll axis of the spacecraft, and the radiator panels are substantially parallel to Earth's equatorial plane, in which the pitch axis of the spacecraft is substantially parallel to Earth's polar axis, in which the Nadir vector is in a yaw-pitch plane of the spacecraft, and in which the transmit antenna and receive antenna are oriented at angle φnom. The antenna attitude adjustor and the spacecraft attitude adjustor may correct an attitude of the transmit antenna to maintain a desired degree of the receive antenna and the transmit antenna steered toward a coverage region on Earth's surface.

摘要翻译： 航天器可以包括接收天线，具有天线姿态调节器的发射天线和航天器姿态调节器。 航天器可以具有标称方向，其中航天器的偏转轴，航天器的滚动轴线和散热器面板基本上平行于地球的赤道平面，其中航天器的俯仰轴线基本上平行于地球的极轴 ，其中天底矢量位于航天器的偏航螺距平面中，并且其中发射天线和接收天线以角度＆amp;角度定向。 天线姿态调节器和航天器姿态调节器可以校正发射天线的姿态，以将接收天线和发射天线的期望程度保持朝向地球表面的覆盖区域。

公开(公告)号：US07588213B2

公开(公告)日：2009-09-15

申请号：US11703287

申请日：2007-02-07

申请人： Robert F. D'Ausilio ,  James R. Stuart ,  Bari M. Southard ,  Franklin H. Williams, Jr.

发明人： Robert F. D'Ausilio ,  James R. Stuart ,  Bari M. Southard ,  Franklin H. Williams, Jr.

IPC分类号： B64G1/40 ,  B64G1/42

CPC分类号： B64G1/1078 ,  B64G1/007 ,  B64G1/222 ,  B64G1/242 ,  B64G1/283 ,  B64G1/288 ,  B64G1/363 ,  B64G1/405 ,  B64G1/406 ,  B64G1/408 ,  B64G1/422 ,  B64G1/44 ,  B64G1/503 ,  B64G1/646 ,  B64G1/66

摘要： A preferred In Orbit Transportation & Recovery System (IOSTAR™) (10) includes 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.

公开(公告)号：US07410129B2

公开(公告)日：2008-08-12

申请号：US10895337

申请日：2004-07-21

申请人： Silvain Legrand ,  Rodolphe Chaix

发明人： Silvain Legrand ,  Rodolphe Chaix

IPC分类号： B64G1/42

CPC分类号： B64G1/645 ,  B64G1/222 ,  B64G1/443

摘要： The invention relates to devices for releasing the stacking tie-rods that are used for holding deployable structures, in particular solar panels of artificial satellites. The device of the invention is self-releasing in order to enable such deployable structures to be released via the top portion of the stacking column. The invention consists in holding together the members (101) that are to be deployed by means of a tie-rod (102) having a nut (111) screwed onto its free end. The force for holding the stack together is transmitted by modules (106, 107) which are themselves held together by said force. When the stacking tension is reduced, resilient means, such as two flat spring blades (112, 113), cause the modules to move away from the tie-rod, thus enabling the members of the deployable structure to be released.

摘要翻译： 本发明涉及用于释放用于保持可部署的结构，特别是人造卫星的太阳能电池板的堆叠连杆的装置。 本发明的装置是自动释放的，以便能够通过堆叠塔的顶部释放这种可展开的结构。 本发明通过将具有拧在自由端上的螺母（111）的拉杆（102）保持在待部署构件（101）上。 将堆叠在一起的力由模块（106,107）传递，模块（106,107）本身通过所述力保持在一起。 当堆叠张力减小时，诸如两个扁平弹簧叶片（112,113）的弹性装置使得模块远离拉杆移动，从而使可部署结构的构件能够被释放。

公开(公告)号：US06979986B2

公开(公告)日：2005-12-27

申请号：US10862460

申请日：2004-06-08

申请人： Bruno Ghislain Liegeois

发明人： Bruno Ghislain Liegeois

IPC分类号： B64G1/42 ,  B64G1/44 ,  G05F1/40

CPC分类号： B64G1/428 ,  B64G1/44 ,  B64G1/443

摘要： A Sequential Shunt Switching Regulation cell [S3R] adapted to connect a power source, such as a solar array panel (SAi), to a users bus (Vbus) under control of a signal (INCTRi). The cell (S3R) comprises a phase anticipator circuit (PAC) adapted to reduce the delay between the moment the control signal is received and the moment the power source is connected to the bus, modifying thereby the hysteresis due to parasitic capacitances of the cell and the solar array. Several such cells are included in a power supply arrangement including a power conditioning and distribution unit (PCDU) comprising also a mean error amplifier (MEA) adapted to detect the voltage (OUTS3R) at the user bus and to provide corresponding control signals to the cells. Owing to the phase anticipator circuits in the cells, double sectioning is avoided. In other words, a power source (SAi) is connected to the bus before the mean error amplifier requires the connection of a second one (SAj).

摘要翻译： 顺序分流开关调节单元[S 3 R]适于在诸如太阳能阵列面板（SAi）之类的电源（INC）的控制下连接到用户总线（Vbus）。 小区（S 3 R）包括相位预测器电路（PAC），其适于减小接收到控制信号的时刻与电源连接到总线的时刻之间的延迟，从而修改由于寄生电容的寄生电容引起的滞后 电池和太阳能阵列。 在包括功率调节和分配单元（PCDU）的电源装置中包括若干这样的单元，该功率调节和分配单元（PCDU）还包括适于检测用户总线上的电压（OUTS 3 R）的平均误差放大器（MEA），并且提供相应的控制信号 细胞。 由于电池中的相位预测电路，避免了双重切片。 换句话说，在平均误差放大器需要连接第二个（SAj）之前，电源（SAi）连接到总线。

公开(公告)号：US06923249B1

公开(公告)日：2005-08-02

申请号：US10447971

申请日：2003-05-28

申请人： Harry H. Porter ,  Jose Valenzuela ,  James D. Williams ,  Timothy W. Harvey

发明人： Harry H. Porter ,  Jose Valenzuela ,  James D. Williams ,  Timothy W. Harvey

IPC分类号： B64G1/42 ,  B64G1/44 ,  B64G1/50 ,  B64G1/66 ,  H01M10/0525 ,  H01M10/46 ,  H01M10/50

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。

公开(公告)号：US20050151022A1

公开(公告)日：2005-07-14

申请号：US10755200

申请日：2004-01-09

申请人： Robert D'Ausilio ,  Roger Lenard ,  Chauncey Uphoff ,  Franklin Williams

发明人： Robert D'Ausilio ,  Roger Lenard ,  Chauncey Uphoff ,  Franklin Williams

IPC分类号： B64C27/22 ,  B64G1/00 ,  B64G1/40 ,  B64G1/42 ,  B64G1/50 ,  B64G1/64 ,  F03H1/00

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。

公开(公告)号：US6098930A

公开(公告)日：2000-08-08

申请号：US123136

申请日：1998-07-27

申请人： Howard S. Eller ,  Ramon Coronel

发明人： Howard S. Eller ,  Ramon Coronel

IPC分类号： B64G1/10 ,  B64G1/28 ,  B64G1/32 ,  B64G1/36 ,  B64G1/40 ,  B64G1/42 ,  B64G1/44 ,  B64G1/22

CPC分类号： B64G1/10 ,  B64G1/28 ,  B64G1/32 ,  B64G1/36 ,  B64G1/40 ,  B64G1/425 ,  B64G1/443

摘要： A compact spacecraft (10, 22) having a potentially long life in orbit as a result of its use of non-moving and solid-state components entirely or wherever possible. Amorphous silicon arrays (14, 24, 44) are used for solar energy collection. Because the arrays are not limited to a flat panel configuration, no movement is needed except for possible initial deployment. Phased arrays (12, 26) are used wherever possible for antenna arrays, in combination with torque rods (18, 3) for coarse attitude control of the spacecraft. Avionics modules (30, 50) are fabricated using large wafer-scale techniques and energy storage using long life battery or a solid-state capattery (52) technology. Propulsion is also effected with no moving parts, using waffle propulsion modules (20, 28, 54), which use elemental containers of propellant that is selectively ignited to supply propulsive force. This combination of features extends the useful life of the spacecraft beyond limits imposed primarily by mechanical moving parts, and by high levels of redundancy.

摘要翻译： 由于其全部或任何可能的地方使用非移动和固态部件，所以具有潜在的长寿命的紧凑型航天器（10,22）。 非晶硅阵列（14,24,44）用于太阳能收集。 因为阵列不限于平板配置，除了可能的初始部署之外，不需要移动。 天线阵列（12,26）尽可能地用于天线阵列，结合用于航天器的粗略姿态控制的扭矩杆（18,3）。 使用大型晶片级技术和使用长寿命电池或固态电容（52）技术的能量存储来制造航空电子模块（30,50）。 使用华夫饼推进模块（20,28,54）也可以使用无选择性点燃的推进剂元素容器来提供推进力，推动力也不受运动部件的影响。 这种特征的组合延长了航天器的使用寿命，超出了主要由机械运动部件施加的限制，以及高度的冗余。

公开(公告)号：US6036143A

公开(公告)日：2000-03-14

申请号：US993028

申请日：1997-12-18

申请人： Klaus W. Biber

发明人： Klaus W. Biber

IPC分类号： B64G1/26 ,  B64G1/40 ,  B64G1/42 ,  B64G1/44 ,  F03H1/00

CPC分类号： B64G1/406 ,  B64G1/26 ,  B64G1/405 ,  F03H1/00

摘要： A spacecraft includes a thruster coupled to an outward-facing portion of each solar array such that the thruster plume faces outward from the spacecraft. With the thruster located outboard of any erosion-sensitive surfaces on the spacecraft, the thruster exhaust is directed away from the spacecraft. Since canting of the thrusters is no longer required, the mounting of the thruster in the outward-facing portion of each solar array increases the effective Isp of the thruster. A thruster drive assembly is coupled to each solar array, adjacent to the thruster, for positioning the thruster such that any thruster exhaust is directed away from the spacecraft. A central supply tank is conveniently coupled to a central body portion of the spacecraft for providing a common propellant supply to each of the thrusters.

摘要翻译： 航天器包括联接到每个太阳能阵列的向外部分的推进器，使得推进器羽流面向飞行器的外部。 当推进器位于航天器上任何侵蚀敏感表面的外侧时，推进器排气被引导离开航天器。 由于不再需要推进器的旋转，因此推进器在每个太阳能阵列的朝外部分的安装增加了推进器的有效Isp。 推进器驱动组件联接到与推进器相邻的每个太阳能阵列，用于定位推进器，使得任何推进器排气被引导离开航天器。 中央供应罐方便地联接到航天器的中心主体部分，以向每个推进器提供共同的推进剂供应。

公开(公告)号：US5957409A

公开(公告)日：1999-09-28

申请号：US54303

申请日：1998-04-02

申请人： David Castiel ,  John Draim ,  Kenneth F. Manning

发明人： David Castiel ,  John Draim ,  Kenneth F. Manning

IPC分类号： B64G1/10 ,  B64G1/24 ,  B64G1/42 ,  H04B7/185 ,  H04B7/19 ,  H04B7/195

CPC分类号： B64G1/1007 ,  B64G1/10 ,  B64G1/1085 ,  B64G1/242 ,  H04B7/18576 ,  H04B7/19 ,  H04B7/195 ,  B64G1/428

摘要： An elliptical satellite system which carries out communication. The satellite orbits a height above the earth less than that necessary for geosynchronous orbits. When the satellite is near the apogee portion of its orbit, its velocity approximates the rotational velocity of the earth, and during that period it appears to hover over the earth. Each ground station on the earth always communicates a satellite within a predetermined position of its apogee, and hence that satellite appears to the ground station to hover over the earth. The satellite hence does not communicate with any earth station when it is outside of that apogee portion. During the times when the satellite is outside the apogee portion, its communication is therefore shut off to prevent any possibility of interfering with geosynchronous satellites. During this time, the power supply on the satellite is also used to charge a battery on the satellite. This enables the power supply to be made smaller by an amount equivalent to the duty cycle of the satellite: during the time which it is on.

摘要翻译： 执行通信的椭圆卫星系统。 卫星在地球上方高于地球同步轨道所需的高度。 当卫星靠近其轨道的远地点时，其速度接近于地球的旋转速度，在此期间它似乎悬停在地球上。 地球上的每个地面站总是将卫星通信在其远地点的预定位置内，因此该卫星在地面站上出现在地球上。 因此，当卫星在远地点之外时，卫星不与任何地球站通信。 在卫星在远地点之外的时候，它的通信被关闭，以防止干扰地球同步卫星的任何可能性。 在此期间，卫星上的电源也用于对卫星上的电池充电。 这使得电源能够减小与卫星的占空比相当的量：在其开启的时间。