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401 条记录 (耗时 0.02 秒)

    SATELLITE REFUELLING SYSTEM AND METHOD
    4.
    发明授权
    SATELLITE REFUELLING SYSTEM AND METHOD 有权
    卫星加油系统和方法

    公开(公告)号：EP2134606B1

    公开(公告)日：2018-05-09

    申请号：EP08733557.6

    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 refueling of satellites. The system may include a dedicated refueling satellite launched directly from either earth, or alternatively it could be launched from another larger mother spacecraft or space station in which the refueling 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 refueling procedure. The system may also be configured to be operated autonomously under computer control.

    DISPOSITIF ET PROCEDE DE REGULATION DE DEBIT
    5.
    发明公开
    DISPOSITIF ET PROCEDE DE REGULATION DE DEBIT 审中-公开
    流量控制装置和方法

    公开(公告)号：EP3274782A1

    公开(公告)日：2018-01-31

    申请号：EP16717984.5

    申请日：2016-03-24

    申请人： SAFRAN AIRCRAFT ENGINES

    发明人： ZURBACH, Stéphan ,  RABIN, Julien ,  ÖBERG, Michael

    IPC分类号： G05D7/06 ,  F03H1/00 ,  F02K9/58

    CPC分类号： F03H1/0012 ,  B64G1/402 ,  B64G1/405 ,  G05D7/0652 ,  G05D7/0694

    摘要： The invention relates to the field of regulation of fluid flow rates, and in particular to a flow-rate-regulating device (109) comprising: an upstream chamber (206); a downstream chamber (207); a plurality of electrically conductive capillary ducts (201-205) fluidically connecting the upstream chamber (206) and the downstream chamber (207) in parallel; first and second electrical terminals (208, 209) able to be connected to an electrical current source; and at least one electrical switch (210a, 210b, 211a, 211b) placed so as to selectively connect one or more of said capillary ducts (201-205) between the electrical terminals (208, 209). The invention furthermore relates to a system for supplying propellant gas to a spatial electric thruster (101), comprising at least one such flow-rate-regulating device (109) for regulating a propellant gas flow rate, and to a method for regulating flow rate using such a flow-rate-regulating device (109).

    SATELLITE ARTIFICIEL
    6.
    发明公开
    SATELLITE ARTIFICIEL 有权

    公开(公告)号：EP3259189A1

    公开(公告)日：2017-12-27

    申请号：EP16733161.0

    申请日：2016-06-01

    申请人： Airbus Defence and Space SAS

    发明人： WALKER, Andrew

    IPC分类号： B64G1/22 ,  B64G1/50 ,  B64G1/10 ,  B64G1/42 ,  B64G1/58

    CPC分类号： B64G1/503 ,  B64G1/10 ,  B64G1/226 ,  B64G1/283 ,  B64G1/402 ,  B64G1/425 ,  B64G1/58

    摘要： The invention relates to an artificial satellite comprising an accumulator (62) apt to dissipate heat, at least one radiator (64) able to remove to space the heat dissipated by the accumulator (62), and a piece of equipment (52) that is said to be not very dissipative and that possesses an individual power density per unit area lower than 250 watts/m
    2 , characterised in that it includes a thermally insulating cover (66) bounding, with said radiator (64), an isothermal interior zone (68) in which temperature is controlled by radiation, said accumulator (62) and said piece of not very dissipative equipment (52) being arranged under said thermally insulating cover (66), and in that said accumulator (62) has an operating range comprised between 0°C and 50°C and, preferably, between 10°C and 30°C.

    EINSPRITZUNG IN ROHRE EINES ROHRBÜNDELWÄRMETAUSCHERS
    9.
    发明公开
    EINSPRITZUNG IN ROHRE EINES ROHRBÜNDELWÄRMETAUSCHERS 审中-公开

    公开(公告)号：EP3244154A2

    公开(公告)日：2017-11-15

    申请号：EP17156954.4

    申请日：2017-02-20

    申请人： Airbus-Safran Launchers GmbH

    发明人： Isselhorst, Armin

    IPC分类号： F28D7/16 ,  F28F9/02 ,  F25B39/02 ,  F02K9/44 ,  B64G1/40 ,  F28F9/18 ,  F28F9/16 ,  F28D21/00

    CPC分类号： F28D7/16 ,  B64G1/402 ,  F02K9/40 ,  F02K9/44 ,  F05D2260/20 ,  F25B19/005 ,  F28D2021/0021 ,  F28D2021/0064 ,  F28D2021/0071 ,  F28F9/0282 ,  F28F9/182

    摘要： Ein erfindungsgemäßes Einspritzelement 10 für einen Rohrbündelwärmetauscher weist zum Aufteilen eines Fluidstroms in eine Mehrzahl an Fluidströmen eine Mehrzahl an Durchlässen 11 auf, die sich zu einer Seite des Einspritzelements hin jeweils kegelartig verengen. Ein erfindungsgemäßer Rohrbündelwärmetauscher 100 umfasst ein erfindungsgemäßes Einspritzelement.
    Ein erfindungsgemäßes Verfahren dient einem Kühlen von Treibstoff für ein Triebwerk. Es umfasst
    ein Durchleiten des Treibstoffs durch ein Außenrohr 120 eines Rohrbündelwärmetauschers 100 und
    ein Zuleiten eines Flüssiggases durch eine Zuleitung 130 bis an ein Einspritzelement 10 für ein im Inneren des Außenrohrs 120 angeordnetes Rohrbündel. Das Verfahren umfasst weiter ein Umwandeln des Flüssiggases in ein Verdampfungsgas durch Hindurchleiten des Flüssiggases durch sich jeweils kegelartige verengende Durchlässe 11 des Einspritzelements in Rohre 110a, 110b des Rohrbündels hinein sowie ein Abführen des Verdampfungsgases aus dem Rohrbündel.

    SATELLITE ARTIFICIEL ET PROCÉDÉ DE REMPLISSAGE D'UN RÉSERVOIR DE GAZ PROPULSIF DUDIT SATELLITE ARTIFICIEL
    10.
    发明公开
    SATELLITE ARTIFICIEL ET PROCÉDÉ DE REMPLISSAGE D'UN RÉSERVOIR DE GAZ PROPULSIF DUDIT SATELLITE ARTIFICIEL 有权
    SATELLITE ARTIFICIEL ETPROCÉDÉDE REMPLISSAGE D'UNRÉSERVOIRDE GAZ PROPULSIF DUDIT SATELLITE ARTIFICIEL

    公开(公告)号：EP3212503A1

    公开(公告)日：2017-09-06

    申请号：EP16705226.5

    申请日：2016-01-22

    申请人： Airbus Defence and Space SAS

    发明人： WALKER, Andrew, Nicholas

    IPC分类号： B64G1/40 ,  B64G1/50 ,  B64G1/64

    CPC分类号： B64G1/506 ,  B64G1/402 ,  B64G1/503 ,  B64G1/641 ,  B64G1/645

    摘要： The invention relates to an artificial satellite which includes: a mounting structure supporting equipment-bearing walls; a launcher-adapter rigidly connected to the mounting structure; a first radiator (26); and at least one first system (42) for transporting heat by a fluid, including at least one duct (44) having a first heat-exchange section (50) and a second heat-exchange section (52), said second heat-exchange section (52) being capable of being in thermal contact with said first radiator (26), characterised in that said first heat-exchange section (50) is in thermal contact with at least one portion of the launcher-adapter (16). The invention also relates to a method for filling a tank of propellent gas of said artificial satellite.

    摘要翻译： 本发明涉及一种人造卫星，其包括：支撑设备承载壁的安装结构; 刚性地连接到安装结构的发射器适配器; 第一散热器（26）; 和至少一个用于通过流体输送热量的第一系统（42），所述第一系统包括具有第一热交换部分（50）和第二热交换部分（52）的至少一个管道（44），所述第二热交换器 （52）能够与所述第一散热器（26）热接触，其特征在于，所述第一热交换部分（50）与发射器适配器（16）的至少一部分热接触。 本发明还涉及一种用于填充所述人造卫星的推进气体罐的方法。