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    POWER ARCHITECTURE FOR SOLAR ELECTRIC PROPULSION APPLICATIONS
    51.
    发明公开
    POWER ARCHITECTURE FOR SOLAR ELECTRIC PROPULSION APPLICATIONS 审中-公开
    太阳能推进器的功率架构应用

    公开(公告)号：EP3218265A1

    公开(公告)日：2017-09-20

    申请号：EP15859330.1

    申请日：2015-07-15

    申请人： Aerojet Rocketdyne, Inc.

    发明人： LU, Cheng-Yi

    IPC分类号： B64G1/44

    CPC分类号： B64G1/406 ,  B64G1/405 ,  B64G1/428 ,  B64G1/44 ,  F03H1/0018

    摘要： Systems and methods for powering an electrical thruster (112) of a vehicle (100). The methods comprise providing an unregulated high voltage output current of a high voltage solar array (122) directly to an electric propulsion system (104) of the vehicle. The electric propulsion system generates a converted high voltage current by converting a voltage level of the unregulated high voltage output current. The converted high voltage current is supplied directly to an anode of the electrical thruster. A regulated low voltage current is also generated by regulating a low voltage output of a low voltage solar array (124). The regulated low voltage current is used to supply power to at least one electronic component of the electrical thruster.

    摘要翻译： 用于为车辆（100）的电推进器（112）供电的系统和方法。 该方法包括将高压太阳能电池阵列（122）的未经调节的高电压输出电流直接提供给车辆的电力推进系统（104）。 电力推进系统通过转换未经调节的高电压输出电流的电压电平来产生经转换的高电压电流。 转换后的高压电流直接供应到电推进器的阳极。 通过调节低电压太阳能电池阵列（124）的低电压输出也生成经调节的低电压电流。 调节的低电压电流用于向电推进器的至少一个电子部件供电。

    DOCKING SYSTEM AND METHOD FOR SATELLITES
    52.
    发明公开
    DOCKING SYSTEM AND METHOD FOR SATELLITES 审中-公开
    用于卫星的对接系统和方法

    公开(公告)号：EP3186151A1

    公开(公告)日：2017-07-05

    申请号：EP15835340.9

    申请日：2015-08-26

    申请人： Effective Space Solutions Ltd

    发明人： HALSBAND, Arie ,  TAASEH, Nevo ,  PARIENTE, Meidad ,  REITMAN, Michael

    IPC分类号： B64G1/64 ,  B64G1/40

    CPC分类号： B64G1/646 ,  B64G1/1078 ,  B64G1/222 ,  B64G1/242 ,  B64G1/26 ,  B64G1/405 ,  B64G1/44 ,  B64G1/641 ,  B64G1/66 ,  B64G4/00 ,  B64G2004/005

    摘要： The present invention relates to a service satellite having a body, a controller and a docking unit. The docking unit includes at least two foldable, adjustable gripping arms pivotally mounted on the satellite body, each gripping arm being pivotable relative to the satellite body, and a gripping end at each free end of the gripping arms, wherein the gripping ends are adapted and configured to capture and grip a target portion of an orbiting satellite. Each gripping arm is controllable independently by the controller, which coordinates the motion of the arms. The service satellite also includes a propulsion unit including a first thruster mounted adjacent a Nadir end of the service satellite body, and a balance thruster, the balance thruster being distanced from the first thruster and facing a different direction than the first thruster, propellant for the thruster and the balance thruster; and means for aligning the thrusters so that a thrusting vector passes through a joint center of gravity of the service satellite and the serviced satellite.

    摘要翻译： 本发明涉及一种具有本体，控制器和对接单元的服务卫星。 对接单元包括至少两个可枢转地安装在卫星本体上的可折叠的可调整的夹持臂，每个夹持臂可相对于卫星本体枢转并且在夹持臂的每个自由端处具有夹持端，其中夹持端适配于 被配置为捕获并抓住轨道卫星的目标部分。 每个夹臂可由控制器独立控制，该控制器协调臂的运动。 服务卫星还包括推进单元，该推进单元包括邻近服务卫星主体的天底端安装的第一推进器和平衡推进器，平衡推进器与第一推进器隔开并且面向与第一推进器不同的方向，推进剂用于 推进器和平衡推进器; 以及用于对齐推力器的装置，使得推力向量穿过服务卫星和服务卫星的联合重心。

    FOIL DEPLOYMENT MECHANISM
    55.
    发明公开
    FOIL DEPLOYMENT MECHANISM 审中-公开
    扩展机制WING

    公开(公告)号：EP3063068A1

    公开(公告)日：2016-09-07

    申请号：EP13783943.7

    申请日：2013-10-30

    申请人： European Space Agency (ESA)

    发明人： HODGETTS, Paul

    IPC分类号： B64G1/22 ,  B64G1/44

    CPC分类号： B64G1/222 ,  B64G1/44 ,  H02S40/22 ,  Y02E10/52

    摘要： A foil deployment mechanism comprises a first drum rotatable about a first longitudinal axis, and a second drum rotatable about a second longitudinal axis. The foil deployment mechanism further comprises a cable, the cable comprising a first section which extends from a lower part of the second drum to an upper part of the first drum, a second section which is wound around a part of the first drum facing away from the second drum, a third section which extends from a lower part of the first drum to an upper part of the second drum, and a fourth section which is wound around a part of the second drum facing away from the first drum, wherein the first section and the third section intersect each other between the first drum and the second drum when being viewed along the first longitudinal axis.

    LOW VOLUME MICRO SATELLITE WITH FLEXIBLE WINDED PANELS EXPANDABLE AFTER LAUNCH
    56.
    发明公开
    LOW VOLUME MICRO SATELLITE WITH FLEXIBLE WINDED PANELS EXPANDABLE AFTER LAUNCH 审中-公开
    KLEINVOLUMIGER MIKROSATELLIT MIT FLEXIBLEN GEWICKELTEN，NACH DEM ABSCHUSS EXPANDIERBAREN PLATTEN

    公开(公告)号：EP2882649A4

    公开(公告)日：2016-04-20

    申请号：EP13827451

    申请日：2013-08-08

    申请人： HALSBAND ARIE

    发明人： HALSBAND ARIE

    IPC分类号： B64G1/44 ,  B64G1/10 ,  B64G1/22 ,  B64G1/24 ,  B64G1/64 ,  H02S30/20

    CPC分类号： B64G1/222 ,  B64G1/10 ,  B64G1/242 ,  B64G1/44 ,  B64G1/443 ,  B64G1/646 ,  H02S30/20

    摘要： Micro satellite is disclosed with foldable solar panels that may be winded around the body of the micro satellite so that the growth in outer dimensions of the satellite is no more than 10-20 mm along each one of the length, width and height of the microsatellite so that the micro satellite may be launched in an auxiliary payload volume of a launcher. The foldable solar panels may be deployed to employ area that exceeds 9 times the product of the length by the width of the satellite and 6 times the product of the height by the length. The solar power produced by the solar panel and their light weight enable carrying of cargo that is at least 0.6 of the of the total mass of the satellites.

    摘要翻译： 微型卫星公开了可折叠的太阳能电池板，其可以围绕微卫星的主体缠绕，使得卫星的外部尺寸的增长沿着微卫星的长度，宽度和高度的每一个不超过10-20mm 使得微卫星可以在发射器的辅助有效载荷体积中发射。 可折叠的太阳能电池板可以部署以使用超过卫星宽度乘以9倍乘积的高度乘以长度的乘积的6倍。 由太阳能电池板产生的太阳能发电及其重量轻，可承载至少为卫星总质量0.6的货物。

    HEAT GENERATING TRANSFER ORBIT SHIELD
    58.
    发明公开
    HEAT GENERATING TRANSFER ORBIT SHIELD 审中-公开
    热生成转移轨道盾构

    公开(公告)号：EP2983992A2

    公开(公告)日：2016-02-17

    申请号：EP14782713.3

    申请日：2014-04-08

    申请人： Lockheed Martin Corporation

    发明人： WONG, Hamilton

    IPC分类号： B64G1/58

    CPC分类号： B64G1/44 ,  B64G1/222 ,  B64G1/50 ,  B64G1/503

    摘要： A system and apparatus are provided for preventing heat loss in a spacecraft during the upper stage launch phase and transfer orbit. A thermal control panel can be provided that can be positioned adjacent to exposed areas of radiator panels on the spacecraft in a collapsed configuration. The outer surface of the panel can have a high absorptivity, and the inner surface can have a high emissivity. During upper stage launch phase and transfer orbit, the panel can tend to emit heat toward the radiator panels on an inboard side of the spacecraft, thus reducing heat loss from the radiator panels to reduce the need for onboard electronic heaters and thereby preserve battery power for other onboard systems.

    摘要翻译： 提供了一种系统和装置，用于防止航天器在上级发射阶段和转移轨道期间的热损失。 可以提供热控制面板，其可以以折叠配置定位在航天器上的散热器面板的暴露区域附近。 面板的外表面可以具有高吸收率，并且内表面可以具有高发射率。 在上段发射阶段和传输轨道期间，面板可能倾向于向航天器内侧的散热器面板散发热量，从而减少散热器面板的热量损失，从而减少对机载电子加热器的需求，从而保持电池电力供 其他车载系统。