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    POSITIONING SYSTEM FOR GEOSTATIONARY ARTIFICIAL SATELLITE
    4.
    发明公开
    POSITIONING SYSTEM FOR GEOSTATIONARY ARTIFICIAL SATELLITE 审中-公开
    地球物理学家地球物理学

    公开(公告)号：EP2549287A1

    公开(公告)日：2013-01-23

    申请号：EP10847942.9

    申请日：2010-03-19

    申请人： Sky Perfect JSAT Corporation

    发明人： SATO Eiji ,  ICHIE Yasuhide ,  NAGAI Hiroaki

    IPC分类号： G01S5/12 ,  B64G5/00

    摘要： Ground stations 20, 21 receive any signal transmitted by a geostationary artificial satellite 10, and store the reception signal together with the reception time thereof. A difference Δt in reception time of a same signal between the ground station 20 and the ground station 21 is calculated by performing correlation processing of the reception signal of the ground station 20 and the reception signal of the ground station 21. A distance R20 between the ground station 20 and the geostationary artificial satellite 10 is measured by a distance measurement device. A distance R21 between the ground station 21 and the geostationary artificial satellite 10 is calculated on the basis of the distance R20 obtained by measurement and the difference Δt in reception times, as obtained by correlation processing.

    摘要翻译： 地面站20,21接收由地球静止人造卫星10发送的任何信号，并将接收信号与其接收时间一起存储。 通过对地面站20的接收信号和地面站21的接收信号进行相关处理，来计算地面站20与地面站21之间相同信号的接收时间的差“t。 地面站20和对地静止人造卫星10由距离测量装置测量。 基于通过测量获得的距离R20和通过相关处理获得的接收时间差“t”来计算地面站21和对地静止人造卫星10之间的距离R21。

    SPACECRAFT, METHOD FOR BUILDING SUCH A SPACECRAFT, AND ADAPTOR TO BE USED IN SUCH A SPACECRAFT
    6.
    发明公开
    SPACECRAFT, METHOD FOR BUILDING SUCH A SPACECRAFT, AND ADAPTOR TO BE USED IN SUCH A SPACECRAFT 有权
    飞船，方法建设这样的航天器这类空间车辆的情况下使用SANTANDER ADAPTER

    公开(公告)号：EP1492706A1

    公开(公告)日：2005-01-05

    申请号：EP03745477.4

    申请日：2003-03-26

    申请人： Dutch Space B.V.

    发明人： CRUIJSSEN, Johan, Hendrik ,  NUGTEREN, Paul, Robert ,  SCHOLTEN, Johannes, Reinoldus, Maria

    IPC分类号： B64G1/64 ,  B64G5/00

    CPC分类号： B64G1/641 ,  B64G1/002 ,  B64G5/00

    摘要： The invention relates to a method of assembling a spacecraft (1), comprising a carrier rocket (2) and at least a first payload (3), such as a satellite or the like, wherein the first payload is placed on the carrier rocket employing an adapter (4) between the carrier rocket and the first payload, wherein a two-part adapter is used, wherein a first relatively light part (5) of the adapter is mounted under the first payload, and a second relatively heavy part (6) of the adapter is placed on the carrier rocket, after which the first part of the adapter together with the first payload is placed on the second part of the adapter and the first part of the adapter is secured is a permanent connection on the second part of the adapter so as to bring the same into the completed form.

    PROCEDE ET DISPOSITIF D'INTEGRATION DE SATELLITES SUR UN LANCEUR
    7.
    发明授权
    PROCEDE ET DISPOSITIF D'INTEGRATION DE SATELLITES SUR UN LANCEUR 有权
    方法和装置卫星对运载火箭FIXING

    公开(公告)号：EP1196326B1

    公开(公告)日：2004-07-28

    申请号：EP01938321.5

    申请日：2001-05-23

    申请人： EADS SPACE Transportation SA

    发明人： D'HUBERT, Philippe ,  ACKET, Gaetan

    IPC分类号： B64G1/64 ,  B64G5/00

    CPC分类号： B64G1/641 ,  B64G1/002 ,  B64G1/1085 ,  B64G5/00

    摘要： The invention concerns a method and a device for integrating satellites on a launcher. The method aims at simultaneously integrating several satellites (14) on a common launcher and consists in equipping the latter with a support (10) such as a mast. Each satellite (14) is linked to the mast by several fixing mechanisms (22), independent of one another. Each mechanism (22) comprises a first interface member fixed on the satellite and a second interface member linked to the first interface member through a linking device capable of being disconnected. When docking, a streamlined cowl covering the linking device is received in a corresponding slot (18) of the mast (10). The second interface member is then fixed on the mast (10), from inside the latter, and then the cowl is removed.

    Methods and apparatus for liquid densification
    9.
    发明公开
    Methods and apparatus for liquid densification 有权
    Verfahren und Vorrichtung zum Verdichten einerFlüssigkeit

    公开(公告)号：EP1116926A1

    公开(公告)日：2001-07-18

    申请号：EP01200056.8

    申请日：2001-01-10

    申请人： The Boeing Company

    发明人： Lak, Tibor I. ,  Leblanc, John C. ,  Yoshinaga, Jay K. ,  Lozano, Martin E.

    IPC分类号： F25J1/02 ,  F17C13/08 ,  B64G5/00

    CPC分类号： B64G5/00 ,  F17C13/008 ,  F17C13/083 ,  F17C2201/0109 ,  F17C2201/056 ,  F17C2205/0323 ,  F17C2205/0397 ,  F17C2221/011 ,  F17C2221/012 ,  F17C2221/014 ,  F17C2223/0153 ,  F17C2227/0341 ,  F17C2250/0636 ,  F17C2260/056 ,  F17C2270/0197 ,  Y02E60/321

    摘要： An improved and simplified system for densifying a cryogenic liquid for space vehicles is provided, which includes a heat exchanger (102) having heat exchange tubes (104) therein for receiving a flow of liquid from a storage tank, for example a liquid propellant (22) in a vehicle storage tank (20). The heat exchanger (102) is filled around the exchange tubes (104) with a two-component bath (112), the volume of a primary component substantially exceeding the volume of a secondary component. The secondary component has a boiling temperature that is lower than the boiling temperature of the primary component, and both are lower than the boiling temperature of the cryogenic liquid. In one example, the liquid to be densified is oxygen, the primary component is liquid nitrogen, and a secondary component is liquid hydrogen. The secondary component is preferably injected into the heat exchanger (102) in separate flows to prevent localized freezing of the first component. A manifold having a plurality of injectors may be used for introducing the second component to the heat exchanger (102). A control system (116) receives inputs from one or more sensors within the heat exchanger (102) and operates valves that control the flow of the first and second components of the heat exchange bath (112).

    摘要翻译： 提供了一种改进和简化的用于密封用于太空车辆的低温液体的系统，其包括其中具有热交换管（104）的热交换器（102），用于接收来自储罐例如液体推进剂（22）的液体流 ）在车辆储罐（20）中。 热交换器（102）用双组分浴（112）填充在交换管（104）周围，主组分的体积基本上超过次要组分的体积。 次要组分的沸点温度低于初级组分的沸点温度，二者均低于低温液体的沸点温度。 在一个实例中，待致密化的液体是氧，主要组分是液氮，次要组分是液态氢。 次要组分优选以单独的流注入到热交换器（102）中，以防止第一组分的局部冻结。 可以使用具有多个喷射器的歧管以将第二部件引入热交换器（102）。 控制系统（116）接收来自热交换器（102）内的一个或多个传感器的输入并且操作控制热交换浴（112）的第一和第二部件的流动的阀。

    SATELLITE FUELING SYSTEM AND METHOD THEREFOR
    10.
    发明公开
    SATELLITE FUELING SYSTEM AND METHOD THEREFOR 失效
    燃料供给系统卫星和相关方法

    公开(公告)号：EP0804362A4

    公开(公告)日：1999-03-24

    申请号：EP95944030

    申请日：1995-11-17

    申请人： MOTOROLA INC

    发明人： HAMANT JAMES EDWARD ,  MCBRIDE JOHN REECE ,  CUBBAGE DAVID HERSCHEL

    IPC分类号： B64F1/28 ,  B64G1/40 ,  B64G5/00 ,  F02K9/44 ,  F04F1/02 ,  F04F1/14 ,  B64D37/16 ,  B67D5/54 ,  F04F1/00

    CPC分类号： F04F1/14 ,  B64F1/28 ,  B64G1/402 ,  B64G5/00 ,  Y02T50/82 ,  Y10T137/3127

    摘要： A self-contained fueling module (10) provides the exact amount of hydrazine necessary to fuel a satellite (50) prior to launch. The fueling module (10) includes a propellant tank (14), a vacuum tank (12) and a pressurant tank (16). The propellant tank (14), filled with hydrazine, is shipped to the launch site where it is installed in the fueling module (10). Prior to launch, the fueling module is connected to the satellite and hydrazine is driven with Helium pressurant into the satellite fuel tank (52). The Helium also pressurizes the satellite fuel tank (52) to flight pressure. Any remaining fuel is evacuated from connection (45) and fuel transfer lines (42) with the vacuum tank. Personnel do not have to wear self-contained atmospheric pressurized environment (SCAPE) suits because there is no risk of hydrazine exposure.