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公开(公告)号：US20100223942A1
公开(公告)日：2010-09-09
申请号：US12718748
申请日：2010-03-05
申请人： Anne-Sophie Merino , Julien Hugon , Valérie Canton , Patrick Hugonnot , Thierry Dargent , Isabelle Nann
发明人： Anne-Sophie Merino , Julien Hugon , Valérie Canton , Patrick Hugonnot , Thierry Dargent , Isabelle Nann
CPC分类号： B64G1/1007 , B64G1/50 , B64G1/503 , B64G1/506 , F28D15/00 , F28D15/0266 , F28D15/0275
摘要： The invention relates to a thermal management device intended to collect the heat dissipated by a group of dissipative equipment of a spacecraft in an evaporation zone before discharging this heat to cold space via a condensation zone, situated in the region of the radiators. The evaporation zone and the condensation zone each consist of at least one heat-exchange part comprising a network of a plurality of compact heat-exchange elements distributed over their respective heat-exchange surface and connected in series and/or in parallel by the tubes of the thermal fluid circulation means.A device such as this is particularly intended for telecommunications satellites.
摘要翻译： 本发明涉及一种热管理装置，其用于在通过位于散热器的区域中的冷凝区将该热量排放到冷空气之前收集由蒸发区中的一组飞行器的耗散设备消散的热量。 蒸发区和冷凝区各自包括至少一个热交换部分，该热交换部分包括分布在它们各自的热交换表面上的多个紧凑的热交换元件的网络，并且由管的串联和/或并联连接 热流体循环装置。 诸如此类的设备特别适用于通信卫星。
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公开(公告)号：US08616271B2
公开(公告)日：2013-12-31
申请号：US12037186
申请日：2008-02-26
申请人： Julien Hugon , Thierry Dargent , Isabelle Nann , Paul De Larminat
发明人： Julien Hugon , Thierry Dargent , Isabelle Nann , Paul De Larminat
摘要： The invention relates to a thermal control device intended to dissipate the heat generated by a payload on a spacecraft, comprising a number of surfaces and including means for circulating a refrigerant. An evaporation zone (Z1) comprises means for circulating the refrigerant, a compression zone (Z2), a condensation zone (Z3) comprising at least one radiating panel, linked to a part of the means for circulating the refrigerant, including several branches and comprising means to allow or inhibit the circulation of the refrigerant within these branches so as to vary the area of the heat exchange surface in the condensation zone, a pressure reduction zone (Z4) comprising means for circulating the refrigerant. Such a device is particularly well adapted to thermal problems encountered in telecommunications satellites.
摘要翻译： 本发明涉及一种热控制装置，其旨在消散由有效载荷在航天器上产生的热量，包括多个表面并且包括用于循环制冷剂的装置。 蒸发区（Z1）包括用于使制冷剂循环的装置，压缩区（Z2），包括至少一个散热板的冷凝区（Z3），其连接到用于循环制冷剂的装置的一部分，包括多个分支，并且包括 允许或禁止在这些分支中的制冷剂的循环以便改变冷凝区中的热交换表面的面积的装置，包括使制冷剂循环的装置的减压区（Z4）。 这种装置特别适用于电信卫星遇到的热问题。
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公开(公告)号：US20080217483A1
公开(公告)日：2008-09-11
申请号：US12037186
申请日：2008-02-26
申请人： Julien HUGON , Thierry Dargent , Isabelle Nann , Paul De Larminat
发明人： Julien HUGON , Thierry Dargent , Isabelle Nann , Paul De Larminat
摘要： The invention relates to a thermal control device intended to dissipate the heat generated by a payload on a spacecraft, comprising a number of surfaces and including means for circulating a refrigerant. An evaporation zone (Z1) comprises means for circulating the refrigerant, a compression zone (Z2), a condensation zone (Z3) comprising at lEast one radiating panel, linked to a part of the means for circulating the refrigerant, including several branches and comprising means to allow or inhibit the circulation of the refrigerant within these branches so as to vary the area of the heat exchange surface in the condensation zone, a pressure reduction zone (Z4) comprising means for circulating the refrigerant. Such a device is particularly well adapted to thermal problems encountered in telecommunications satellites.
摘要翻译： 本发明涉及一种热控制装置，其旨在消散由有效载荷在航天器上产生的热量，包括多个表面并且包括用于循环制冷剂的装置。 蒸发区（Z 1> 1）包括用于循环制冷剂，压缩区（Z 2/2），冷凝区（Z 3 3））的装置， 包括在第一个辐射面板上，连接到用于循环制冷剂的装置的一部分，包括多个分支，并且包括允许或抑制制冷剂在这些分支内的循环的装置，以便改变在这些分支中的热交换表面的面积 冷凝区，包括用于循环制冷剂的装置的减压区（Z 4 S 4）。 这种装置特别适用于电信卫星遇到的热问题。
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公开(公告)号：US08032325B2
公开(公告)日：2011-10-04
申请号：US12535819
申请日：2009-08-05
CPC分类号： G01D5/2013 , G01B7/144 , G01B7/312
摘要： The invention produces contactless radial position sensors having an equivalent angular aperture greater than 90°, and substantially eliminates the spurious microvibrations due to the imperfections of the current sensors. For this, the invention uses at least four independent sensors and an electronic device capable of virtually placing in series said sensors in groups of two or three in order to spread the equivalent angular aperture of said groups of sensors.
摘要翻译： 本发明产生具有大于90°的等效角孔径的非接触径向位置传感器，并且基本上消除了由于电流传感器的缺陷引起的杂散微振动。 为此，本发明使用至少四个独立的传感器和电子装置，其能够将两个或三个组中的所述传感器实际上串联实现，以扩展所述传感器组的等效角孔。
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5.发明申请SYSTEM FOR CONTROLLING THE DEPLOYMENT OF SPACECRAFT REQUIRED TO FLY IN FORMATION, BY SIMULTANEOUS AND HIGH-PRECISION DETERMINATION OF THEIR POSITIONS 有权用于控制需要飞行形成的飞行器的部署的系统，通过同时和高精度确定其位置公开(公告)号：US20100032528A1
公开(公告)日：2010-02-11
申请号：US12293694
申请日：2007-03-23
申请人： Roland Frenkiel , Thierry Dargent
发明人： Roland Frenkiel , Thierry Dargent
IPC分类号： B64G1/10
CPC分类号： G01S5/0072 , B64G1/1085 , B64G2001/643 , G01S13/9303
摘要： A system is dedicated to the control of the deployment of at least two spacecraft (ES1, ES2) which are provided with maneuvering means (MD1, MD2) and are intended to move according to a chosen formation. This system includes a control device (MM11, MM12, MT, MC1) comprising i) first measurement means (MM11, MM12, MT) responsible for determining substantially simultaneously and with high precision the orbital positions of the spacecraft (ES1, ES2), and ii) first calculation means (MC1) responsible for determining for each of the spacecraft, as a function of their orbital positions, maneuvers intended to position each of them at a chosen instant substantially in a chosen position with respect to a reference trajectory, having regard to the time law of a reference craft (ES1) on this reference trajectory (TR), so as to place the formation in a chosen configuration.
摘要翻译： 一个系统专门用于控制至少两个设有操纵装置（MD1，MD2）的航空器（ES1，ES2）的部署，并根据所选择的地层进行移动。 该系统包括控制装置（MM11，MM12，MT，MC1），其包括i）第一测量装置（MM11，MM12，MT），负责基本上同时且高精度地确定航天器（ES1，ES2）的轨道位置，以及 ii）负责根据其轨道位置确定每个航天器的第一计算装置（MC1），其旨在将它们中的每一个基本上相对于参考轨迹基本上在选定位置中定位，考虑到 到基准轨迹（TR）上的参考飞行器（ES1）的时间规律，以便将地层放置在选定的构型中。
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6.发明授权公开(公告)号：US08096511B2
公开(公告)日：2012-01-17
申请号：US12293694
申请日：2007-03-23
申请人： Roland Frenkiel , Thierry Dargent
发明人： Roland Frenkiel , Thierry Dargent
IPC分类号： B64G1/10
CPC分类号： G01S5/0072 , B64G1/1085 , B64G2001/643 , G01S13/9303
摘要： A system is dedicated to the control of the deployment of at least two spacecraft (ES1, ES2) which are provided with maneuvering means (MD1, MD2) and are intended to move according to a chosen formation. This system includes a control device (MM11, MM12, MT, MC1) comprising i) first measurement means (MM11, MM12, MT) responsible for determining substantially simultaneously and with high precision the orbital positions of the spacecraft (ES1, ES2), and ii) first calculation means (MC1) responsible for determining for each of the spacecraft, as a function of their orbital positions, maneuvers intended to position each of them at a chosen instant substantially in a chosen position with respect to a reference trajectory, having regard to the time law of a reference craft (ES1) on this reference trajectory (TR), so as to place the formation in a chosen configuration.
摘要翻译： 一个系统专门用于控制至少两个设有操纵装置（MD1，MD2）的航空器（ES1，ES2）的部署，并根据所选择的地层进行移动。 该系统包括控制装置（MM11，MM12，MT，MC1），其包括i）第一测量装置（MM11，MM12，MT），负责基本上同时且高精度地确定航天器（ES1，ES2）的轨道位置，以及 ii）负责根据其轨道位置确定每个航天器的第一计算装置（MC1），其旨在将它们中的每一个基本上相对于参考轨迹基本上在选定位置中定位，考虑到 到基准轨迹（TR）上的参考飞行器（ES1）的时间规律，以便将地层放置在选定的构型中。
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公开(公告)号：US20100036640A1
公开(公告)日：2010-02-11
申请号：US12535819
申请日：2009-08-05
IPC分类号： G01B7/30
CPC分类号： G01D5/2013 , G01B7/144 , G01B7/312
摘要： The invention produces contactless radial position sensors having an equivalent angular aperture greater than 90°, and substantially eliminates the spurious microvibrations due to the imperfections of the current sensors. For this, the invention uses at least four independent sensors and an electronic device capable of virtually placing in series said sensors in groups of two or three in order to spread the equivalent angular aperture of said groups of sensors.
摘要翻译： 本发明产生具有大于90°的等效角孔径的非接触径向位置传感器，并且基本上消除了由于电流传感器的缺陷引起的杂散微振动。 为此，本发明使用至少四个独立的传感器和电子装置，其能够将两个或三个组中的所述传感器实际上串联实现，以扩展所述传感器组的等效角孔。
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8.发明申请Electromagnetic Device for Generating a Force and a Torque for Positioning a Body 审中-公开用于产生力的电磁装置和用于定位身体的扭矩公开(公告)号：US20070295865A1
公开(公告)日：2007-12-27
申请号：US11569314
申请日：2005-04-25
摘要： An action device comprises first electromagnetic means installed on a first body and defining a first magnetic moment and a magnetic field and second electromagnetic means installed on a second body, distant from the first body, and defining a second magnetic moment able to interact with the magnetic field. It further comprises i) means for varying the first magnetic moment in accordance with a chosen first law of variation to cause the magnetic field to vary in time, ii) means for varying the second magnetic moment in accordance with a second law of variation so that a required force and a required torque are induced on the second body, and iii) calculation means adapted to determine the second law of variation as a function at least of the required force and the required torque and the first law of variation.
摘要翻译： 动作装置包括安装在第一主体上并限定第一磁矩和磁场的第一电磁装置，以及安装在远离第一主体的第二主体上的第二电磁装置，并且限定能够与磁性相互作用的第二磁矩 领域。 它还包括：i）根据所选择的第一变化规律改变第一磁矩以使得磁场在时间上变化的装置，ii）根据第二变化定律改变第二磁矩的装置，使得 在第二主体上引起所需的力和所需的扭矩，以及iii）适于确定第二变化定律至少是所需力和所需扭矩和第一变化定律的函数的计算装置。
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公开(公告)号：US5552683A
公开(公告)日：1996-09-03
申请号：US198505
申请日：1994-02-18
申请人： Thierry Dargent
发明人： Thierry Dargent
CPC分类号： H02P7/0094 , H02P7/04
摘要： A reversible electric device M is connected in an H bridge with a first side formed by first top and bottom switches and a second side formed by second top and bottom switches. The current Im flowing in the device from the first side to the second side is determined cyclically with a given constant switching frequency. The difference .DELTA. is determined between Im and an instantaneous set point current. Each cycle is divided with a ratio R into a first part and a second part. R is determined and for each part a set point setting for the switches (diagonal mode or freewheel mode) is chosen according to the sign .DELTA., the sign of the set point current (or of Im) and the value of a preselected correlation law relating to .DELTA. the mean value of the voltage that can be applied to the device during each cycle.
摘要翻译： 可逆电气装置M连接在H桥中，第一侧由第一顶部和底部开关形成，第二侧由第二顶部和底部开关构成。 以给定的恒定切换频率周期性地确定从第一侧向第二侧流动的电流Im。 在Im和瞬时设定点电流之间确定差值DELTA。 每个循环以比例R分成第一部分和第二部分。 确定R，并且对于每个部分，根据DELTA，设定点电流（或Im）的符号和相关的预选相关定律的值来选择开关（对角线模式或续流模式）的设定点设置 以DELTA在每个周期内可以施加到设备的电压的平均值。
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10.发明授权Coating for prevention of electrostatic discharge within an equipment in a spatial environment 有权用于防止在空间环境中的设备内的静电放电的涂层公开(公告)号：US08672272B2
公开(公告)日：2014-03-18
申请号：US11312564
申请日：2005-12-21
申请人： Sébastien Clerc , Thierry Dargent
发明人： Sébastien Clerc , Thierry Dargent
IPC分类号： B64G1/44
CPC分类号： H01L31/042 , B64G1/226 , B64G1/44 , Y02E10/50
摘要： A solar panel (3) having a front face (31) for receiving solar radiation and a rear face (32), for use in a spacecraft (1). The solar panel is covered on the rear face (32) with a coating (4) having negative electric charge emissive property such that in use the coating expels electrons out of the rear face (32) of the solar panel (3), thus reducing the potential difference between the front face (31) and the rear face (32). A method of reducing potential difference between the front face (31) and the rear face (32) of the solar panel (3) by covering the rear face by said coating (4).
摘要翻译： 一种具有用于接收太阳辐射的前表面（31）和用于航天器（1）的后表面（32）的太阳能电池板（3）。 太阳能电池板用背面（32）覆盖有具有负电荷发射特性的涂层（4），使得在使用中涂层将电子从太阳能电池板（3）的背面（32）排出，从而减少 前面（31）与后面（32）之间的电位差。 一种通过用所述涂层（4）覆盖所述背面来减小所述太阳能电池板（3）的所述正面（31）与所述背面（32）之间的电位差的方法。
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