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81.发明公开
公开(公告)号：EP1189327A2
公开(公告)日：2002-03-20
申请号：EP01120033.4
申请日：2001-08-20
CPC分类号： B64G1/24 , B64G1/1085 , B64G1/428 , B64G1/443 , H02J17/00 , H02J50/20 , H02J50/40 , H02J50/90
摘要： A method of and a system for receiving microwave beams from a plurality of power satellites (1) in space by way of a receiving antenna (3). By controlling the directions of a plurality of microwave beams (7) to be transmitted from the plurality of power satellites (1), the plurality of power satellites (1) direct the plurality of microwave beams (7) into an aperture surface of the receiving antenna (3), respectively, so that the plurality of microwave beams (7) can be dispersively received at a number of different positions (6) on the aperture surface of the receiving antenna (3), so as to level the energy distribution of the microwaves received on the aperture surface of the receiving antenna (3).
摘要翻译： 一种用于通过接收天线（3）从空间中的多个功率卫星（1）接收微波波束的方法和系统。 通过控制要从多个功率卫星（1）发射的多个微波束（7）的方向，多个功率卫星（1）将多个微波波束（7）引导到接收机 天线（3），使得可以在接收天线（3）的孔径表面上的多个不同位置（6）处分散地接收多个微波束（7），以便使能量分布 接收天线（3）的孔径表面上的微波。
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公开(公告)号：EP1012361A4
公开(公告)日：2001-05-02
申请号：EP97936009
申请日：1997-04-22
申请人： FORWARD ROBERT L , HOYT ROBERT P
发明人： FORWARD ROBERT L , HOYT ROBERT P
CPC分类号： B63B21/502 , B64G1/409 , B64G1/421 , B64G1/648 , B64G9/00
摘要： A tether (Figure 6) having the special technical feature of multiple primary load-bearing lines (601, 603) and normally slack secondary lines (605, 603). These primary and secondary lines are connected together with knotless, slipless interconnections so the tether maintains high strength and some of the lines can be cut without failure of the tether when it is operated near the ultimate failure load of the material from which it is constructed. This tether can safely carry (Figure 31) load hundreds of times longer than prior art tethers in harsh environments where a single-line tether experiences a substantial risk of failure. The specific industrial applications of an electrodynamic tether system to deorbit satellites and a low Earth orbit to lunar surface tether transport system are all part of the general innovative concept of the invention.
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公开(公告)号：EP0970884A2
公开(公告)日：2000-01-12
申请号：EP99113212.7
申请日：1999-07-08
发明人： Krause, Stanley J.
CPC分类号： H02J7/35 , B64G1/425 , B64G1/428 , B64G1/443 , H02J7/0024
摘要： A spacecraft, such as a satellite (20) in geosynchronous orbit, is powered using at least two independently controllable batteries (30), such as lithium ion batteries, operably connected to the power-consuming components (22) of the spacecraft (20). Each battery (30) is operable in a higher-temperature range and inactivated in a lower-temperature range. The first battery (30a) and the second battery (30b) are operated in the higher-temperature range during a first period of time. The first battery (30a) is thereafter operated in the higher-temperature range during a second period of time, with the second battery (30b) being non-operational and in the lower-temperature range during the second period of time. The first battery (30a) and the second battery (30b) are thereafter operated in the higher-temperature range during a third period of time. The second battery (30b) is thereafter operated in the higher-temperature range during a fourth period of time, with the first battery (30a) being non-operational and in the lower-temperature range during the fourth period of time. The operable battery or batteries (30) may be operated through a partial charging/discharging cycle. This alternating operation prolongs the lifetimes of the batteries (30).
摘要翻译： 诸如地球同步轨道中的卫星（20）之类的航天器使用至少两个可操作地连接到航天器（20）的功率消耗部件（22）的可独立控制的电池（30）例如锂离子电池来供电， 。 每个电池（30）可在较高温度范围内操作并在较低温度范围内不激活。 第一电池（30a）和第二电池（30b）在第一时间段内在较高温度范围内运行。 之后，在第二时间段期间，在第二时间段期间第二电池（30b）不可操作并且处于较低温度范围的情况下，第一电池（30a）在较高温度范围内操作。 此后，第一电池（30a）和第二电池（30b）在第三时间段内在较高温度范围内运行。 之后，在第四时间段内，第二电池（30b）在较高温度范围内工作，其中第一电池（30a）不工作，并且在第四时间段内处于较低温度范围内。 可操作的一个或多个电池（30）可以通过部分充电/放电循环来操作。 这种交替操作延长了电池（30）的寿命。
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公开(公告)号：EP0897863A3
公开(公告)日：1999-11-24
申请号：EP98306145.8
申请日：1998-07-31
申请人： Pall Corporation
发明人： Stallard, Paul
CPC分类号： B64G1/402 , B01D19/0031 , F02K9/54 , F02M37/22
摘要： A vehicle, such as a missile, includes a propulsion unit (44) and a fuel system (42,45,10,43) supplying fuel to the propulsion unit (44). The fuel system (42,45,10,43) includes a filter assembly (10) through which the fuel passes to the propulsion unit (44). The filter assembly (10) includes a filter element (12) having a first bubble point with the fuel sufficient to prevent the passage of gas through the element (12) when the fuel and a gas are passed to the filter element (12) and the vehicle is subjected to accelerations of between ± 1g and ± 10g. The first bubble point will generally be at least 40 mbar. The element helps to prevent the passage of gas to the propulsion unit so as to maximise the amount of fuel passed to the unit (44) before operation of the unit (44) is affected by air.
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85.发明公开Verteilungs- und Schaltungssystem für Mittelspannungsgleichstrom-Netze 失效Verteilungs- und SchaltungssystemfürMittelspannungsgleichstrom-Netze
公开(公告)号：EP0821456A1
公开(公告)日：1998-01-28
申请号：EP97101200.0
申请日：1997-01-27
发明人： Retat, Ingo, Dr. , Schmitz, Burkhard , Köhler, Horst , Meyer, Thomas , von Öhsen, Rolf , Schneegans, Joachim , Tölken, Manfred , Weber, Karl-Heinz, Dr. , Börchers, Heinz G.
CPC分类号： B64G1/428 , H02B1/36 , H05K7/1432
摘要： Es wird ein modulares Schaltungs-, Sicherungs- und Aufbereitungssystem für Mittelspannungsgleichstrom-Netze beschrieben, daß durch ein modulares Konzept charakterisiert ist und bei dem ein fest installierbares Basisgehäuse für passive Bauelemente und mindestens ein standardisiertes Einschubelement für aktive Bauelemente zum austauschbaren Einsetzen in das Basisgehäuse vorgesehen ist. Dieses Schaltungssystem ist insbesondere zur Verwendung in der Raumfahrt vorgesehen, es kann jedoch auch überall dort eingesetzt werden, wo eine hohe Zuverlässigkeit und lange Lebensdauer bei einfacher Wartung gefordert.
摘要翻译： 分配和切换系统具有用于无源部件的固定基座壳体（10）和用于有源部件的至少一个可插拔插入元件（20），其插入基座壳体中。 插入式插入件可以具有用于与基座壳体电气和机械接触的夹具系统，具有标准化的开关和熔断器，用于在插座更换时将基座壳体中的集成编码插头自动切换到特定应用的特性 - 元素。
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公开(公告)号：EP0641065B1
公开(公告)日：1997-11-26
申请号：EP94109377.5
申请日：1994-06-17
申请人： ROBERT BOSCH GMBH
发明人： Ohms, Franz
CPC分类号： H02M3/3374 , B64G1/428 , Y02B70/1433
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87.发明公开Device and method for equalizing heat dissipation between multiple radiators on a spacecraft 失效装置和方法用于在航天器均衡多个辐射体之间的散热
公开(公告)号：EP0780302A1
公开(公告)日：1997-06-25
申请号：EP96120403.9
申请日：1996-12-18
发明人： Caplin, Glenn N.
摘要： A device for equalizing thermal dissipation between radiator panels (28, 30) of a satellite comprises a plurality of radiator panels (28, 30) mounted on said satellite. A plurality of power sources (32, 36) is mounted on said radiator panels (28, 30) such that each radiator panel (28, 30) has at least one power source (32, 36) mounted thereon. Further, a load (34) is mounted adjacent one of said power sources (32, 36). The load (34) is capable of inhibiting said adjacent power sources (32, 36) from supplying power to the load (34) and causing said nonadjacent power sources (32, 36) to supply power to the load. Alternatively, the load is capable of controlling current supplied by said power sources (32, 36) such that said thermal dissipation of said radiator panels (28, 30) is equalized.
摘要翻译： 一种用于均衡卫星的辐射板（28，30）之间的热耗散装置包括（28，30）安装在所述卫星辐射板的复数。 的动力源（32，36）的多个安装在所述辐射板（28，30）进行测试做具有至少一个动力源（32，36）安装在其上的每个散热器面板（28，30）。 的所述功率源进一步，负载（34）安装成邻近一个（32，36）。 负载（34）是能够所述抑制从将电力供应到负载（34）和使所述非相邻的电源（32,36），以将电力提供给负载的相邻电源（32，36）。 可替换地，负载能够控制由所述功率源供应的电流（32，36）检测所述辐射板的所述散热（28，30）被均衡。
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88.发明公开Satellite géostationnaire à accumulateurs d'énergie électrique 失效GeostationärerSatellit mit elektrischen Akkumulatorenzellen。
公开(公告)号：EP0647559A1
公开(公告)日：1995-04-12
申请号：EP94402233.4
申请日：1994-10-05
CPC分类号： H01M2/10 , B64G1/226 , B64G1/425 , B64G1/503 , B64G1/506 , H01M10/617 , H01M10/643 , H01M10/6551 , H01M10/6552 , H01M10/6554
摘要： Le satellite ayant une charge utile, destiné à être stabilisé à poste autour de trois axes sur une orbite géostationnaire, comporte une structure qui a des parois faisant face au Nord et au Sud lorsque le satellite est à poste et qui porte au moins une batterie d'accumulateurs. La batterie, ou chaque batterie d'accumulateurs (24) est constituée de cellules (32) montées sur un châssis ayant une semelle (31) orientée Nord-Sud et solidaire mécaniquement de flancs (33) faisant face au Nord et au Sud lorsque le satellite est à poste, lesdits flancs (33) portant ou constituant des radiateurs thermiques reliés thermiquement entre eux et avec les cellules (32).
摘要翻译： 卫星具有旨在在站内稳定在地球静止轨道上的三个轴的有效载荷，包括当卫星在站内时具有面向北和南的壁并且携带至少一个蓄电池（存储单元）的结构， 。 蓄电池或每个蓄电池蓄电池（24）由安装在底座上的电池（32）组成，底座（31）朝向南北方向并机械地固定在卫星进入车站时朝向北面和南面的法兰（33） 所述凸缘（33）承载或构成彼此热连接并且连接到所述电池（32）的热辐射器。
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89.发明公开
公开(公告)号：EP0603869A1
公开(公告)日：1994-06-29
申请号：EP93120730.2
申请日：1993-12-22
摘要： A magnetic torquing system for a spacecraft using conducting coils is disclosed. In one embodiment, the conductors (44, 46) on a spacecraft's (10) solar wing (28, 30) which connect the solar cell strings (38) to the voltage controller (48) are wired to produce a magnetic torque which can be regulated by shunting individual strings to ground (52) or by opening a string circuit. This embodiment does not require the extra weight of a coil because the panel's solar string produces the torque normally produced by an additional coil. In another embodiment, a coil (44, 46) is wired between a shunting switch (54) in the spacecraft voltage controller (48) and a ground (32) so that shunting a string to ground (52) supplies current first to the coil to generate a magnetic torque in the desired direction.
摘要翻译： 公开了一种使用导电线圈的航天器的磁力扭矩系统。 在一个实施例中，将太阳能电池串（38）连接到电压控制器（48）的航天器（10）太阳能翼（28,30）上的导体（44,46）被布线以产生磁力矩，其可以是 通过将单个线分流到地（52）或通过打开串电路来调节。 该实施例不需要额外的线圈重量，因为面板的太阳能串产生通常由附加线圈产生的扭矩。 在另一个实施例中，线圈（44,46）被布线在航天器电压控制器（48）中的分流开关（54）和接地（32）之间，从而将串联到地（52）将线路首先提供给线圈 以在期望的方向上产生磁力矩。
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90.发明公开
公开(公告)号：EP0602668A1
公开(公告)日：1994-06-22
申请号：EP93120423.4
申请日：1993-12-17
CPC分类号： B64G1/402
摘要： A propellant immobilizing system and method in which propellant motion in the propellant storage tanks (22) is reduced or eliminated during velocity change maneuvers to reduce disturbance torques acting upon the spacecraft (10) and improving the spacecraft attitude pointing performance. The thrusters (14, 16, 18 or 20) are fired to produce a small impulse in the direction of the desired velocity change to begin motion of the propellant within the fuel tank in the opposite direction. After the fuel has moved within the tank to a location in which the propellant center of mass is aligned with the propellant tank (22) center of curvature in the direction of the desired velocity change, thrusters (14, 16, 18 or 20) are again fired to produce a force in the direction of the current velocity of the propellant center of mass to stop the propellant center of mass relative to the propellant tank (22). With the center mass of the propellant now aligned with the propellant tank center of curvature in the direction of the desired velocity change, the thrusters (14, 16, 18 or 20) are again fired to produce the desired velocity change with the propellant center of mass now being trapped in the propellant tank such that additional motion of the propellant is inhibited. After completion of the maneuver, the propellant gradually migrates back to its original position due to the influence of a propellant management device within the propellant tank.
摘要翻译： 推进器（14,16,18或20）被点燃以产生所需速度变化方向的小冲量，以使燃料箱内的推进剂沿相反方向开始运动。 在燃料已经在罐内移动到推进剂中心与推进剂罐（22）在所需速度变化方向上的曲率中心对准的位置之后，推进器（14,16,18或20）是 再次开火。 这在推进剂质心的当前速度方向产生一个力，以相对于推进剂罐（22）停止推进剂质心。 随着推进剂的中心质量现在与推进剂罐在所需速度变化方向上的曲率中心对准，再次点燃推进器（14,16,18或20）以产生所需的速度变化。
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