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1. 发明公开

EP4353601A3 SATELLITE 审中-实审
公开(公告)号：EP4353601A3
公开(公告)日：2024-06-05
申请号：EP24160200.2
申请日：2019-11-08
申请人： Iceye Oy
发明人： MODRZEWSKI, Rafal , NEEROT, Martin
IPC分类号： B64G1/10 , B64G1/44 , B64G1/42 , B64G1/22 , B64G1/50 , B64G1/66 , H04B7/185
CPC分类号： B64G1/428 , H04B7/18515 , B64G1/10 , B64G1/66 , B64G1/50 , B64G1/1007 , B64G1/1021 , B64G1/1035 , B64G1/223
摘要： A satellite comprises a body and a generally planar structure extending from the body One or more radio frequency "RF" antennas, an amplification system for rf signals, and a power distribution system for the amplification system are mounted on the generally planar structure. Two or all of the power distribution system, the one or more RF antennas and the amplification system are arranged on respective parallel boards forming part of the generally planar structure One or more of the parallel boards and the components mounted thereon may b connected to another similar board to form, respectively a larger power distribution system, antenna array or amplification system, for example arranged in a plurality of modules, each comprising at least one antenna, at least one power distribution system and at least one amplifier supported on at least two respective boards. A satellite may be manufactured by assembling the modules to form a generally planar structure; and attaching the planar structure to a satellite body

2. 发明授权

EP3672018B1 AUTONOMOUS CONTROL OF ELECTRIC POWER CONSUMPTION BY AN APPARATUS 有权转让
公开(公告)号：EP3672018B1
公开(公告)日：2024-05-22
申请号：EP19202923.9
申请日：2019-10-14
IPC分类号： B64G1/42 , H02J7/00 , H02J7/35 , B64G1/44 , B64G1/40
CPC分类号： H02J7/35 , H02J7/00712 , H02J7/005 , H02J7/0048 , B64G1/428 , B64G1/44 , B64G1/425 , B64G1/405 , H02J2310/4020200101

3. 发明公开

EP4353601A2 SATELLITE 审中-实审
公开(公告)号：EP4353601A2
公开(公告)日：2024-04-17
申请号：EP24160200.2
申请日：2019-11-08
申请人： Iceye Oy
发明人： MODRZEWSKI, Rafal , NEEROT, Martin
IPC分类号： B64G1/22
CPC分类号： B64G1/428 , H04B7/18515 , B64G1/10 , B64G1/66 , B64G1/50 , B64G1/1007 , B64G1/1021 , B64G1/1035 , B64G1/223
摘要： A satellite comprises a body and a generally planar structure extending from the body One or more radio frequency "RF" antennas, an amplification system for rf signals, and a power distribution system for the amplification system are mounted on the generally planar structure. Two or all of the power distribution system, the one or more RF antennas and the amplification system are arranged on respective parallel boards forming part of the generally planar structure One or more of the parallel boards and the components mounted thereon may b connected to another similar board to form, respectively a larger power distribution system, antenna array or amplification system, for example arranged in a plurality of modules, each comprising at least one antenna, at least one power distribution system and at least one amplifier supported on at least two respective boards. A satellite may be manufactured by assembling the modules to form a generally planar structure; and attaching the planar structure to a satellite body

4. 发明授权

EP2347958B1 DEVICE FOR SUPPRESSING SUSTAINED DISCHARGE ON SOLAR BATTERY ARRAY 有权
公开(公告)号：EP2347958B1
公开(公告)日：2018-09-05
申请号：EP09825903.9
申请日：2009-11-11
申请人： Kyushu Institute of Technology
发明人： TOYODA, Kazuhiro , CHO, Meng , KAYANO, Hikaru
IPC分类号： B64G1/42 , B64G1/44 , H01L31/042 , H01L31/02
CPC分类号： B64G1/443 , B64G1/428 , H01L31/02021 , Y02E10/50
摘要： A sustained-arc control system is constituted with a capacitance which is placed between a gap on a solar battery array, working to control or inhibit the sustained arc. A solar battery array (3) has a plurality of solar cells (1) to provide a power source onboard an artificial satellite (4). A plurality of series circuits (2) each of which composed of the solar cells (1) connected in series is connected in parallel. The sustained-arc control system on the solar battery array is constituted with a capacitance lying between a positive line and a negative line to be charged with a voltage oscillation arising from the sustained arc. Electrostatic capacity of the capacitance is in a range of from at least 33nF to 10µF.

5. 发明公开

EP3325347A1 LARGE-AREA STRUCTURES FOR COMPACT PACKAGING 有权
公开(公告)号：EP3325347A1
公开(公告)日：2018-05-30
申请号：EP16828571.6
申请日：2016-07-21
申请人： California Institute of Technology
发明人： LEE, Nicolas , PELLEGRINO, Sergio , ARYA, Manan , HAJIMIRI, Seyed, Ali , LECLERC, Christophe , ATWATER, Harry, A.
IPC分类号： B64G1/44 , B64G1/10 , H02S10/40 , H02S20/30
CPC分类号： B64G1/428 , B64G1/1085 , B64G1/222 , B64G1/288 , B64G1/36 , B64G1/443 , B64G1/66 , B65B63/04 , H01L31/042 , H02J3/383 , H02J50/20 , H02S10/40 , H02S30/20 , Y02E10/563
摘要： A space-based solar power station, a power generating satellite module and/or a method for collecting solar radiation and transmitting power generated using electrical current produced therefrom, and/or compactible structures and deployment mechanisms used to form and deploy such satellite modules and power generation tiles associated therewith are provided. Each satellite module and/or power generation tile may be formed of a compactable structure and deployment mechanism capable of reducing the payload area required to deliver the satellite module to an orbital formation within the space-based solar power station and reliably deploy it once in orbit.

6. 发明公开

EP3322058A1 ELECTRIC POWER SYSTEM FOR A SPACE VEHICLE 有权
标题翻译：空间车辆电力系统
公开(公告)号：EP3322058A1
公开(公告)日：2018-05-16
申请号：EP17196097.4
申请日：2017-10-12
申请人： Hamilton Sundstrand Corporation
发明人： ROZMAN, Gregory I. , FUTRELL, Michael Anthony
IPC分类号： H02J1/08 , H02J1/10 , H02J7/35 , H02J7/34 , G05F1/10 , B64G1/42
CPC分类号： H02J3/385 , B64G1/425 , B64G1/428 , B64G1/443 , G05F1/10 , H02J1/08 , H02J1/102 , H02J3/14 , H02J3/36 , H02J7/345 , H02J7/35 , H02J9/061 , Y02E10/566 , Y02E10/58
摘要： An electrical power system for a space vehicle may comprise a first plurality of power sources (102), a first collector bus configured to receive power from the plurality of power sources (102), an unregulated DC bus (120) configured to receive power from the first collector bus, a regulated high voltage direct current (HVDC) bus (140) configured to receive power from the unregulated DC bus (120), and a first power distribution unit (PDU) (150) configured to receive power from the regulated HVDC bus (140). The regulated HVDC bus (140) may be configured to supply power to a high voltage load. The first plurality of power sources (102) may comprise a first solar array, a first supercapacitor, and/or a first battery.
摘要翻译：一种用于航天器的电力系统可以包括第一多个电源（102），被配置为从该多个电源（102）接收电力的第一收集器总线，被配置为从该多个电源（102）接收电力的未调节DC总线（120）所述第一集电器总线，被配置为从所述未经调节的DC总线（120）接收功率的经调节的高压直流（HVDC）总线（140），以及被配置为从所述经调节的 HVDC总线（140）。调节的HVDC总线（140）可以被配置为向高压负载供电。第一多个电源（102）可以包括第一太阳能电池阵列，第一超级电容器和/或第一电池。

7. 发明公开

EP3224512A1 ACTUATOR CONTROLLER 审中-公开
标题翻译：执行器控制器
公开(公告)号：EP3224512A1
公开(公告)日：2017-10-04
申请号：EP14907002.1
申请日：2014-11-25
申请人： Aerojet Rocketdyne, Inc.
发明人： SWANSON, Jon, Darel , DAREJEH, Hadi
IPC分类号： F16K31/00
CPC分类号： F16K31/0675 , B64G1/40 , B64G1/402 , B64G1/428 , F02K9/58 , H01F7/064
摘要： Systems (100) and methods (300, 500) for controlling an electromechanical valve element (116). The methods involve: building up a magnetic flux through a valve (206) of the electromechanical valve element by supplying a PWM signal to an electromechanically inductive coil (202) of the electromechanical valve element at a power level lower than a power level needed to actuate the valve. When the valve needs to be opened, an amplitude of the PWM signal is increased such that the power provided to the electromechanically inductive coil rises to a power level sufficient to actuate the valve. Notably, the valve opens when a power cycling time of the PWM signal increases beyond a minimum power required to open the valve.
摘要翻译：用于控制机电阀元件（116）的系统（100）和方法（300,500）。该方法包括：通过以低于驱动所需的功率水平的功率水平向机电阀元件的机电感应线圈（202）提供PWM信号来建立通过机电阀元件的阀（206）的磁通量阀门。当阀需要打开时，PWM信号的幅度增加，使得提供给机电感应线圈的功率上升到足以致动阀的功率水平。值得注意的是，当PWM信号的功率循环时间增加超过打开阀门所需的最小功率时，阀门打开。

8. 发明公开

EP3178741A1 DISPOSITIF D'ALIMENTATION DE PUISSANCE D'UN ENGIN AÉROSPATIAL, SYSTÈME DE COMMANDE DE VÉRINS ÉLECTRIQUES D'UN LANCEUR SPATIAL ET LANCEUR SPATIAL ASSOCIÉS 有权
标题翻译：电源装置一空机，相应的系统来控制电动缸运载火箭及相关运载火箭
公开(公告)号：EP3178741A1
公开(公告)日：2017-06-14
申请号：EP15306979.4
申请日：2015-12-10
申请人： THALES
发明人： GLETON, Laurent , GUILLAUME, Michel , GOFFIN, Benoît
IPC分类号： B64G1/42
CPC分类号： B64G1/002 , B64G1/428
摘要： Dispositif d'alimentation de puissance d'un engin aérospatial comprenant une alimentation électrique dont un point de potentiel intermédiaire (9) est configuré pour être relié à la masse mécanique (10) de l'engin aérospatial formant deux domaines de tensions électriques (3, 4) à l'intérieur de chacun desquels la différence maximale de potentiel électrique n'excède pas la tension électrique critique de la loi de Paschen, chaque domaine (3, 4) comprenant une isolation électrique indépendante.

9. 发明公开

EP3149822A1 ELECTRIC PROPULSION POWER CIRCUIT 有权
标题翻译： ELEKTROANTRIEBSLEISTUNGSSCHALTUNG
公开(公告)号：EP3149822A1
公开(公告)日：2017-04-05
申请号：EP14894036.4
申请日：2014-06-02
申请人： Aerojet Rocketdyne, Inc.
发明人： MADIGAN, Michael , KRISTALINSKI, Alexandr , KOCH, Brian
IPC分类号： H02H7/26
CPC分类号： F03H1/0018 , B64G1/405 , B64G1/428
摘要： A circuit (400, 700, 800) comprising: a first power source (402) supplying first current to a load (470) during a first Period of Time (“PoT”); a second power source (416) supplying a second current to the load during a second POT; a Unidirectional Current Valve (“UCV”) in series with the first power source; a current detector (420, 702, 802) in series with the UCV (422); and a switch (424) in parallel with a series combination of the current detector and UCV to bypass the UCV during the second PoT. The current detector determines whether the second period of time has commenced and whether the switch has closed.
摘要翻译：一种电路（400,700,800），包括：在第一时间段（“PoT”）期间向负载（470）提供第一电流的第一电源（402）在第二POT期间向所述负载提供第二电流的第二电源（416）; 与第一电源串联的单向电流阀（“UCV”）; 与UCV（422）串联的电流检测器（420,702,802）; 以及与所述电流检测器和UCV的串联组合并联的开关（424），以在所述第二PoT期间绕过所述UCV。电流检测器确定第二时间段是否已经开始以及开关是否闭合。

10. 发明公开

EP3045395A1 SATELLITE CONTROL SYSTEM 有权
标题翻译： SATELLITENKONTROLLSYSTEM
公开(公告)号：EP3045395A1
公开(公告)日：2016-07-20
申请号：EP15193545.9
申请日：2015-11-06
申请人： Honeywell International Inc.
发明人： SMITH, Douglas Edward , CRIPPEN, Don , STILES, Joshua Matthew , SAYED, Mostafa
IPC分类号： B64G1/28
CPC分类号： B64G1/36 , B64G1/10 , B64G1/286 , B64G1/428
摘要： A vehicle, a satellite control system, and a method for controlling the same are provided. The satellite control system, for example, may include, but is not limited to, a control moment gyroscope having a gimbal, at least one gimbal angle sensor configured to determine an angle of the gimbal, each gimbal angle sensor having an output circuit configured to output the determined angle, a signal conditioner circuit having substantially identical circuit topology as the output circuit, and a common mode error compensation circuit electrically coupled to the signal conditioner, the common mode error compensation circuit configured to determine common mode error in the gimbal angle sensor based upon a voltage output from the signal conditioner circuit and to output a signal to compensate for the common mode error.
摘要翻译：提供车辆，卫星控制系统及其控制方法。例如，卫星控制系统可以包括但不限于具有万向节的至少一个云平面角度传感器的控制力矩陀螺仪，其被配置为确定万向节的角度，每个万向角传感器具有输出电路，该输出电路被配置为输出所确定的角度，具有与输出电路基本相同的电路拓扑的信号调节器电路，以及电耦合到信号调节器的共模误差补偿电路，该共模误差补偿电路被配置为确定万向角传感器中的共模误差基于来自信号调节器电路的电压输出并输出信号以补偿共模误差。

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