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    A SPACECRAFT, A SYSTEM AND A METHOD FOR DEPLOYING A SPACECRAFT
    1.
    发明公开
    A SPACECRAFT, A SYSTEM AND A METHOD FOR DEPLOYING A SPACECRAFT 审中-公开

    公开(公告)号：EP3385173A1

    公开(公告)日：2018-10-10

    申请号：EP18162501.3

    申请日：2018-03-19

    申请人： Space Systems/Loral, LLC

    发明人： CHIANG, Jason J.

    IPC分类号： B64G1/00 ,  B64G1/64

    CPC分类号： B64G1/645 ,  B64G1/002 ,  B64G1/401 ,  B64G1/403 ,  B64G1/405 ,  B64G1/641 ,  B64G2001/643

    摘要： A spacecraft includes payload equipment and bus equipment, each of the payload equipment and the bus equipment being coupled with a secondary structure arrangement. The spacecraft is configured to structurally interface with a launch vehicle upper stage only by way of an exoskeletal launch support structure (ELSS) that provides a first load path between a launch vehicle upper stage and the secondary structure arrangement. The spacecraft is configured to deploy from the launch vehicle upper stage by separating from the ELSS. In some implementations, the first load path is the only load path between the spacecraft and the launch vehicle upper stage, and substantially all of the ELSS remains with the launch vehicle upper stage. Because the secondary structure may be substantially less massy then the ELSS, subsequent orbit raising maneuvers may then be executed with a spacecraft having a reduced dry mass.

    SATELLITE ARTIFICIEL ET PROCÉDÉ DE REMPLISSAGE D'UN RÉSERVOIR DE GAZ PROPULSIF DUDIT SATELLITE ARTIFICIEL
    2.
    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。

    DEVICE FOR THE HOLD-DOWN AND CONTROLLED RELEASE OF SPACE SATELLITES INSTALLED ON LAUNCHERS AND OF LOADS INSTALLED ON SPACE SATELLITES
    3.
    发明公开
    DEVICE FOR THE HOLD-DOWN AND CONTROLLED RELEASE OF SPACE SATELLITES INSTALLED ON LAUNCHERS AND OF LOADS INSTALLED ON SPACE SATELLITES 审中-公开
    用于在发射器上安装的空间卫星以及在空间卫星上安装的负载的下压和受控释放的装置

    公开(公告)号：EP3184439A1

    公开(公告)日：2017-06-28

    申请号：EP16203665.1

    申请日：2016-12-13

    申请人： AEREA S.p.A.

    发明人： CASSANELLI, Ruggero ,  ALIVERTI, Ivo ,  PERNECHELE, Luca Andrea

    IPC分类号： B64G1/64 ,  F16B37/08

    CPC分类号： B64G1/645 ,  B64G1/641 ,  F16B37/0864

    摘要： Device for the hold-down and controlled release of space satellites installed on launchers and loads installed on space satellites, comprising a blocking member (5) made up of segments (4) radially displaceable from a mutually approached retaining position to a mutually spaced-apart release position of a connecting screw (6). In order to control the radial displacement of the segments (4) between the retaining position and the release position there are provided a rotatable element (16) coaxial with the blocking member (5), an articulated mechanism (3) which operatively connects the rotatable element(16) with the segments (4) of the blocking member (5), and linear motors (23, 24) for driving the controlled rotation of the rotatable element (16) and, through the articulated mechanism (3), the simultaneous displacement of the segments (4) of the blocking member (5).

    摘要翻译： 用于压缩和受控释放安装在太空卫星上的发射器和负载上的太空卫星的装置，包括由片段（4）组成的阻挡件（5），所述片段（4）可从相互接近的保持位置径向移动到相互间隔开的 连接螺钉（6）的释放位置。 为了控制节段（4）在保持位置和释放位置之间的径向位移，设置有与阻挡构件（5）同轴的可旋转元件（16），铰接机构（3），其可操作地连接可旋转元件 具有阻挡构件（5）的段（4）的元件（16）;以及用于驱动可旋转元件（16）的受控旋转并且通过铰接机构（3）同时驱动的线性电动机（23,24） 所述阻挡构件（5）的区段（4）的位移。

    DUAL PORT PAYLOAD ATTACH RING COMPATIBLE SATELLITE
    4.
    发明公开
    DUAL PORT PAYLOAD ATTACH RING COMPATIBLE SATELLITE 审中-公开
    BEFESTIGUNGSRINGKOMPATIBLER SATELLIT MIT DOPPELANSCHLUSSNUTZLAST

    公开(公告)号：EP3153412A1

    公开(公告)日：2017-04-12

    申请号：EP16191822.2

    申请日：2016-09-30

    申请人： The Boeing Company

    发明人： COOK, Timothy Scott ,  FRIEND, Robert Bruce

    IPC分类号： B64G1/64

    CPC分类号： B64G1/641 ,  B64G1/64 ,  B64G1/645 ,  B64G1/646 ,  B64G2001/643

    摘要： Systems, methods, and apparatus for dual port ring compatible satellites are disclosed. In one or more embodiments, a method for removably attaching at least one spacecraft (220) to a payload attach ring (310) on a launch vehicle (140) involves attaching a strongback (215) of each of the spacecrafts to two respective payload ports (320) of the payload attach ring on the launch vehicle. In one or more embodiments, the strongback of each of the spacecrafts is attached to each of the two respective payload ports via a respective beam mounted to a respective port adaptor plate. The method further involves separating the strongback of each of the spacecrafts from the two respective payload ports of the payload attach ring on the launch vehicle by using at least one mechanical actuator on each of the beams.

    摘要翻译： 公开了用于双端口环兼容的卫星的系统，方法和装置。 在一个或多个实施例中，用于将至少一个航天器（220）可移除地附接到运载火箭（140）上的有效载荷附着环（310）的方法包括将每个航天器的强力（215）附接到两个相应的有效载荷端口 （320）的有效载荷附着环在运载火箭上。 在一个或多个实施例中，每个航天器的强力通过安装到相应的端口适配器板的相应梁连接到两个相应的有效载荷端口中的每一个上。 该方法还包括通过使用每个梁上的至少一个机械致动器将每个航天器的强力与有效载荷附着环的两个相应的有效载荷端口分离在运载火箭上。

    DISPOSITIF DE LIAISON PROVISOIRE ET DE SÉPARATION PYROTECHNIQUE DE DEUX ENSEMBLES
    9.
    发明公开
    DISPOSITIF DE LIAISON PROVISOIRE ET DE SÉPARATION PYROTECHNIQUE DE DEUX ENSEMBLES 有权
    DEVICE FOR临时连接和断开烟火双测度

    公开(公告)号：EP2435716A1

    公开(公告)日：2012-04-04

    申请号：EP10724019.4

    申请日：2010-05-26

    申请人： Astrium SAS

    发明人： KISTER, Thomas ,  CLAUDEL, Sylvain

    IPC分类号： F15B15/19 ,  F16B31/00 ,  B64G1/64 ,  F42B15/38

    CPC分类号： F42B15/38 ,  B64G1/645 ,  F16B31/005

    摘要： The invention relates to a device for temporary connection with a longitudinal axis (X) and for pyrotechnic separation, including a pyrotechnic expansion tube (14) mounted in a space (11) arranged in a connection area between a first (2) and a second (4) assembly to be separated, the second assembly (4) consisting of a stack of layers (12.1, 12.2) adhered to one another, the two assemblies (2, 4) being connected together by two metal parts (10.1, 10.2), said metal parts being attached to the first assembly and adhered to the outer layers (12.1) of the second assembly (4), wherein the adhesion surface between said outer layer (12.1) and the adjacent inner layer (12.2) is smaller than the adhesion surface between two inner layers (12.2) forming a fusible layer, such that, when the pyrotechnic expansion tube (14) is used, the outer layer (12.1) separates from the adjacent inner layer.