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    HIGH CAPACITY COMMUNICATION SATELLITE
    61.
    发明公开
    HIGH CAPACITY COMMUNICATION SATELLITE 审中-公开

    公开(公告)号：EP3418204A1

    公开(公告)日：2018-12-26

    申请号：EP18178440.6

    申请日：2018-06-19

    申请人： Space Systems/Loral, LLC

    发明人： WU, Gordon ,  ALLEY, Philip ,  MARLOW, David

    IPC分类号： B64G1/10 ,  B64G1/22 ,  B64G1/66 ,  H01Q1/08 ,  H01Q1/28 ,  H01Q15/16

    摘要： A spacecraft (100) includes a structural interface adapter for mating to a launch vehicle, an aft surface disposed proximate thereto, and a forward surface disposed opposite thereto, a main body structure, including a plurality of sidewalls (116,117), disposed between the aft surface and the forward surface and a plurality of unfurlable antenna reflectors (130). At least one unfurlable antenna reflector is configured to be illuminated, in an on-orbit configuration, by a respective feed array.(160). The spacecraft is reconfigurable from a launch configuration to the on-orbit configuration. In the launch configuration, the at least one unfurlable antenna reflector (130) is disposed, undeployed, forward of the respective feed array (160), proximate to and outboard of one of the plurality of sidewalls (116, 117). In the on-orbit configuration, the forward surface is substantially earth-facing and the at least one unfurlable antenna reflector is disposed, deployed, so as to be earth-facing from a position aft of the respective feed array.

    SATELLITE REFUELLING SYSTEM AND METHOD
    63.
    发明公开
    SATELLITE REFUELLING SYSTEM AND METHOD 审中-公开

    公开(公告)号：EP3351354A1

    公开(公告)日：2018-07-25

    申请号：EP18159861.6

    申请日：2008-03-10

    申请人： MacDonald, Dettwiler and Associates Inc.

    发明人： GRYNIEWSKI, Lawrence ,  CRYMBLE, Derry

    IPC分类号： B25J11/00 ,  B64G1/14 ,  B64G4/00 ,  B64G5/00 ,  B64G1/10 ,  B64G1/40 ,  B67D7/04

    CPC分类号： B25J11/00 ,  B64G1/1078 ,  B64G1/14 ,  B64G1/402 ,  B64G4/00 ,  B64G5/00 ,  B67D2007/0403 ,  B67D2007/0405 ,  B67D2007/0417 ,  B67D2007/0432

    摘要： The present invention provides a method, system and apparatus for robotic refuelling of satellites. The system may include a dedicated refuelling satellite launched directly from either earth, or alternatively it could be launched from another larger mother spacecraft or space station in which the refuelling satellite is ferried into space in the case of the larger space craft or it may be stored on the space station until needed from which it can be launched. The system includes a robotic arm, suitable tools which can be affixed to the end effector of the robotic arm required for accessing, opening and closing the fuel fill valve on the satellite being serviced, storage and retrieval stations on a tool caddy on which the tools and various fuel fill valve caps are stored. The system is under teleoperation by a remotely located operator, for example located on earth, in the mother station or in the space station. Cameras are included focussed on the robotic arm and end effector and images are transmitted to the operator to allow the operator to direct and control the refuelling procedure. The system may also be configured to be operated autonomously under computer control.

    RADAR SATELLITE AND RADAR SATELLITE SYSTEM USING SAME
    64.
    发明公开
    RADAR SATELLITE AND RADAR SATELLITE SYSTEM USING SAME 审中-公开

    公开(公告)号：EP3222531A4

    公开(公告)日：2018-06-20

    申请号：EP15861404

    申请日：2015-11-09

    申请人： KAWASAKI HEAVY IND LTD

    发明人： KUROSE TOYOTOSHI

    IPC分类号： B64G1/66 ,  B64G1/10 ,  B64G1/22 ,  B64G1/26 ,  B64G1/64 ,  G01S7/02 ,  G01S7/03 ,  G01S13/89

    CPC分类号： B64G1/26 ,  B64G1/222 ,  B64G1/648 ,  B64G2001/1035 ,  G01S7/02 ,  G01S7/03 ,  G01S13/89

    摘要： A radar satellite of the present invention comprises a radar unit (20) including a plurality of radar panels (21) coupled to each other in a single flat plate shape, each of the plurality of radar panels including a plurality of antennas which transmit and receive radar waves, and a solar cell (241); and a communication/control unit (50) which performs communications with a spot on an earth or a spacecraft. The radar unit (20) includes: a radar panel array (201) which is a plate-shaped structure including the plurality of radar panels (21); and a deployable truss structure (202) including a plurality of side frame members (204) supporting the plurality of radar panels (21), respectively, and coupled to each other in such a manner that the side frame members are foldable and deployable.

    ADAPTIVE SCAN RATE SPACE SURVEILLANCE SENSOR FOR SUPER-GEO ORBITS
    70.
    发明公开
    ADAPTIVE SCAN RATE SPACE SURVEILLANCE SENSOR FOR SUPER-GEO ORBITS 审中-公开
    RAUMÜBERWACHUNGSSENSORMIT ADAPTIVER ABTASTRATEFÜRSUPER-GEO-UMLAUFBAHNEN

    公开(公告)号：EP3135591A1

    公开(公告)日：2017-03-01

    申请号：EP16178200.8

    申请日：2016-07-06

    申请人： The Boeing Company

    发明人： GERWE, David R. ,  WILLIAMS, Keith R. ,  LAMBERT, John ,  TARBUCK, Paul D. ,  ESTRADA, Edward A.

    IPC分类号： B64G1/10 ,  B64G1/24

    CPC分类号： B64D47/08 ,  B64G1/1021 ,  B64G1/242 ,  B64G2001/1028 ,  B64G2001/1035 ,  G06K9/4661 ,  G06K9/52 ,  G06K9/6201 ,  G06T7/60 ,  G06T2207/10032

    摘要： Systems, methods, and apparatus for space surveillance are disclosed herein. In one or more embodiments, the disclosed method involves scanning, by at least one sensor on at least one satellite in super-geostationary earth orbit (super-GEO), a raster scan over a field of regard (FOR). In one or more embodiments, the scanning is at a variable rate, which is dependent upon a target dwell time for detecting a target of interest. In at least one embodiment, the target dwell time is a function of a characteristic brightness of the target. (Fig. 13)

    摘要翻译： 本文公开了用于空间监视的系统，方法和装置。 在一个或多个实施例中，所公开的方法包括通过超对地静止地球轨道（超级GEO）中的至少一个卫星上的至少一个传感器扫描通过视域（FOR）的光栅扫描。 在一个或多个实施例中，扫描是可变速率，其取决于用于检测感兴趣的目标的目标停留时间。 在至少一个实施例中，目标停留时间是目标的特征亮度的函数。 （图13）