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1.发明申请公开(公告)号：US20160129862A1
公开(公告)日：2016-05-12
申请号：US14895779
申请日：2014-06-06
发明人： Pierre Henrard , Nicolas Carre , Bruno Chapotin
CPC分类号： B60R16/03 , B64D47/00 , B64D2221/00 , H01H47/04 , H01H47/22 , H02H7/06 , H02J1/00 , H02J3/00 , H02J4/00
摘要： The invention relates to an assistance device (17) for an electrical power generation system (11) of an aircraft, said system (11) comprising a generator (13), a regulator (14) and a contactor (15) comprising contacts and an actuator for opening/closing the contacts which is controlled by said regulator (14) and arranged between the generator (13) and a distribution architecture (12), the assistance device being characterised in that it is connected to at least one power source (18) which is separate from the generator (13) and the regulator (14), and in that it comprises means for closing the contactor which are suitable for connecting the power source (18) to the actuator (23) of the contactor (15) in order to provide the current necessary for closing said contactor (15).
摘要翻译： 本发明涉及一种用于飞行器的发电系统（11）的辅助装置（17），所述系统（11）包括发电机（13），调节器（14）和接触器（15），其包括触点和 致动器，其用于打开/关闭由所述调节器（14）控制并且布置在所述发电机（13）和分配架构（12）之间的所述触点，所述辅助装置的特征在于，所述辅助装置连接到至少一个电源 ），其与发电机（13）和调节器（14）分离，并且其包括用于闭合适于将电源（18）连接到接触器（15）的致动器（23）的接触器的装置， 以便提供关闭所述接触器（15）所需的电流。
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公开(公告)号：US09969341B2
公开(公告)日：2018-05-15
申请号：US14895779
申请日：2014-06-06
发明人： Pierre Henrard , Nicolas Carre , Bruno Chapotin
IPC分类号： B60L1/00 , B60R16/03 , H01H47/04 , H02J1/00 , H02J3/00 , B64D47/00 , H02H7/06 , H02J4/00 , H01H47/22
CPC分类号： B60R16/03 , B64D47/00 , B64D2221/00 , H01H47/04 , H01H47/22 , H02H7/06 , H02J1/00 , H02J3/00 , H02J4/00
摘要： The invention relates to an assistance device (17) for an electrical power generation system (11) of an aircraft, said system (11) comprising a generator (13), a regulator (14) and a contactor (15) comprising contacts and an actuator for opening/closing the contacts which is controlled by said regulator (14) and arranged between the generator (13) and a distribution architecture (12), the assistance device being characterized in that it is connected to at least one power source (18) which is separate from the generator (13) and the regulator (14), and in that it comprises means for closing the contactor which are suitable for connecting the power source (18) to the actuator (23) of the contactor (15) in order to provide the current necessary for closing said contactor (15).
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公开(公告)号：US09698651B2
公开(公告)日：2017-07-04
申请号：US14402794
申请日：2013-05-14
发明人： Eric De Wergifosse , Cedric Duval
IPC分类号： H02K7/18 , F01D15/10 , F01D25/02 , F01D7/00 , H02K11/00 , H02K16/02 , H02K17/42 , B64D15/12 , H01F38/18
CPC分类号： H02K7/1823 , B64D15/12 , B64D2221/00 , F01D7/00 , F01D15/10 , F01D25/02 , H01F38/18 , H02K11/0094 , H02K16/02 , H02K17/42
摘要： An electrical power supply including an asynchronous machine, an arrangement for driving a rotor of the asynchronous machine in rotation by a rotor of an engine, and an electrical connection for powering electrical equipment by the rotor of the asynchronous machine. The asynchronous machine is configured to receive AC electrical power via a stator of the asynchronous machine, and it presents, over a predetermined range of drive speeds of the rotor of the asynchronous machine under drive by the rotor of the engine, efficiency in transferring electrical power from the stator to the rotor that is privileged relative to the efficiency with which rotary mechanical power is converted into electrical power.
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4.发明授权Electric power supply for apparatuses supported by the rotor of an aircraft engine 有权用于由飞机发动机的转子支撑的装置的电力供应公开(公告)号：US09458729B2
公开(公告)日：2016-10-04
申请号：US13704462
申请日：2011-06-08
申请人： Eric De Wergifosse , Cedric Duval
发明人： Eric De Wergifosse , Cedric Duval
CPC分类号： F01D7/00 , B64C11/306 , B64D15/12 , B64D2027/005 , Y02T50/66
摘要： An aircraft engine including: a stator; a main shaft; a first rotor; a second rotor; a transmission mechanism; a first electrical apparatus supported by the first rotor and a second electrical apparatus supported by the second rotor; at least one first field winding supported by the stator; a control unit configured to circulate direct electric current in the first field winding; at least one first armature winding supported by the first rotor and connected to the first electrical apparatus and at least one second armature winding supported by the second rotor and connected to the second electrical apparatus.
摘要翻译： 一种飞机发动机，包括：定子; 主轴; 第一转子; 第二转子 传输机制; 由第一转子支撑的第一电气设备和由第二转子支撑的第二电气设备; 由定子支撑的至少一个第一场绕组; 控制单元，被配置为在第一场绕组中循环直流电; 由所述第一转子支撑并连接到所述第一电气设备的至少一个第一电枢绕组和由所述第二转子支撑并连接到所述第二电气设备的至少一个第二电枢绕组。
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5.发明授权公开(公告)号：US09350094B2
公开(公告)日：2016-05-24
申请号：US14402181
申请日：2013-05-30
发明人： Tony Lhommeau , Stephane Sorel
CPC分类号： H01R12/616 , H01R12/57 , H01R12/592
摘要： An electrical circuit including at least one electrical component, such as a power component, and an electrical flex circuit, and at least one electrical conductor part connecting the electrical component to the flex circuit, the electrical conductor part including at least a first contact portion configured to receive in contact a contact element of the electrical power component and a second contact portion configured to receive in contact a conductive layer of the electrical flex circuit, the extent of the width of the second contact portion corresponding to the width of the flex circuit, and the extent of the length of same being adjusted to provide a contact surface that one of transmitting a density of electrical current of between 4.5 and 5.5 A/mm2 and allowing the electrical circuit to support a current specific to the power component, i.e. between 30 and 80 A.
摘要翻译： 包括至少一个电气部件（例如功率部件）和电柔性电路的电路以及将电气部件连接到柔性电路的至少一个电导体部分，所述电导体部分至少包括配置在第一接触部分 以接触电力部件的接触元件和被配置为接触电柔性电路的导电层的第二接触部分，第二接触部分的宽度对应于柔性电路的宽度的程度， 并且其长度的范围被调整以提供接触表面，其中发送电流密度在4.5和5.5A / mm 2之间的电流，并允许电路支持特定于功率部件的电流，即在30 和80 A.
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6.发明授权公开(公告)号：US09711925B2
公开(公告)日：2017-07-18
申请号：US14396592
申请日：2013-04-18
IPC分类号： H01R43/048 , H01B7/04 , H01R43/16 , H01R4/24 , H01R4/20 , H01B7/06 , H01R4/64 , H01R12/69 , H01B5/00 , H01B7/00 , H01R43/042 , H01R4/18 , H01R4/62 , H01R31/08 , H01R101/00
CPC分类号： H01R43/048 , H01B5/00 , H01B7/0045 , H01B7/04 , H01B7/06 , H01R4/182 , H01R4/20 , H01R4/206 , H01R4/24 , H01R4/2404 , H01R4/62 , H01R4/64 , H01R4/646 , H01R12/69 , H01R31/085 , H01R43/042 , H01R43/0482 , H01R43/16 , H01R2101/00 , Y10T29/49181 , Y10T29/49222 , Y10T29/53209 , Y10T29/53217 , Y10T29/53235 , Y10T29/53239
摘要： A method electrically connects by crimping electrical conductors in a connector for equipotential connection of a planar and flexible layer formed by the conductors, to metal components. The method includes positioning the electrical conductors in individual longitudinal and parallel cells which are formed between two planar walls of the connector, crimping the conductors crimped in a crimping zone by simultaneous transverse punching of at least one wall of the connector, and forming by the transverse punching at least one corresponding transverse groove line on the at least one connector wall and, by load transfer, on each of the conductors to electrically connect the conductors.
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7.发明申请A DEVICE FOR PROVIDING PROTECTION AGAINST SHORT CIRCUITS UPSTREAM FROM A POWER MODULE 有权用于向电源模块提供短路短路保护的设备公开(公告)号：US20160276920A1
公开(公告)日：2016-09-22
申请号：US15030170
申请日：2014-10-15
摘要： The protection device for providing protection against short-circuits upstream from an electrical power supply module having an inlet filter with at least one capacitor and an inductor and having a converter with components associated with a plurality of freewheel diodes includes at least one auxiliary winding and a dissipator element associated with the inlet filter, thereby making it possible to provide an inlet filter of small size without over dimensioning the freewheel diodes.
摘要翻译： 用于提供对具有具有至少一个电容器和电感器的入口滤波器的电源模块上游的短路保护的保护装置，并且具有与多个续流二极管相关联的元件的转换器包括至少一个辅助绕组和 与入口过滤器相关联的散热器元件，从而使得可以提供小尺寸的入口过滤器，而不会使续流二极管过大。
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公开(公告)号：US09233759B2
公开(公告)日：2016-01-12
申请号：US13703497
申请日：2011-06-06
摘要： An aircraft electrical supply circuit including: a power distribution network, onboard the aircraft, for electrical devices located in an engine of the aircraft or near the engine; and a power supply generator built into the engine of the aircraft to supply AC voltage power to a deicing or anti-icing system. The power supply generator is connected to a thrust reverser electromechanical actuator by a rectifier for supplying DC voltage power to the actuator.
摘要翻译： 一种飞机供电电路，包括：飞机上的配电网，位于飞机发动机或发动机附近的电气设备; 以及内置于飞行器发动机中的电源发生器，以向除冰或防冰系统提供交流电压。 电源发生器通过用于向致动器提供直流电压电力的整流器连接到推力反向器机电致动器。
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9.发明申请公开(公告)号：US20150377715A1
公开(公告)日：2015-12-31
申请号：US14767270
申请日：2014-02-13
发明人： Philippe Poret , Tony Lhommeau
CPC分类号： G01K7/16 , G01K7/183 , G01K7/223 , G01K13/00 , H01F27/008 , H01F27/2823 , H01F27/29
摘要： The invention relates to a method of measuring the temperature of a coiled component comprising the injection of a known DC current into a gauge wire (1) made of resistive material, the resistance of the gauge wire varying with temperature according to a known law, the measurement of potential difference between the terminals (7a, 7b) of said gauge wire, and a step of calculation transforming the potential difference into a mean temperature of the gauge wire, said gauge wire (1) being wound inside the coil, and arranged as a series of “outbound” turns (5) and a series of “inbound” turns (6) associated pairwise with a geometry and a position that are substantially equal. It also relates to a component made in order to be able to implement this method and the measurement device as a whole.
摘要翻译： 本发明涉及一种测量卷绕部件的温度的方法，包括将已知的直流电流注入到由电阻材料制成的量规线（1）中，根据已知的规律测量线的电阻随温度变化， 测量所述量规线的端子（7a，7b）之间的电位差，以及计算将电位差转换为量规线的平均温度的步骤，所述量规线（1）缠绕在线圈内，并且被布置为 一系列“出站”转弯（5）和一系列“入站”转弯（6），其几何形状和位置基本相等。 它还涉及为了能够实现该方法和整个测量装置而制造的部件。
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10.发明授权Module for converting voltage between a high-voltage electrical network of an aircraft and an energy storage element 有权用于在飞机的高压电力网络和能量存储元件之间转换电压的模块公开(公告)号：US09197088B2
公开(公告)日：2015-11-24
申请号：US13976215
申请日：2011-12-22
CPC分类号： H02J7/0068 , H02J4/00 , H02J7/345 , H02M3/1584
摘要： A module converting voltage between a high-voltage electrical network and at least one energy storage element an aircraft, the conversion module configured to reversibly convert between a DC voltage of the high-voltage electrical network and a DC voltage of the energy storage element, the DC voltage of the energy storage element floating relative to the DC voltage of the high-voltage electrical network and centered relative to the mass of the aircraft, the module including an input module including two filters each capable of receiving a DC voltage, a first arm and a second arm including switches, and a mechanism controlling the switches, operating per cycle of a switching period and capable of controlling at least one first switch and at least one second switch identically but offset by a half-period, whereby the first switch is open when the second switch is closed and vice versa.
摘要翻译： 一种将高压电网和至少一个能量存储元件之间的电压转换成飞行器的模块，所述转换模块被配置为在高压电网的直流电压和能量存储元件的直流电压之间可逆地转换， 能量存储元件的直流电压相对于高压电网的直流电压而相对于飞行器的质量而相对于所述质量浮动，该模块包括一个包括两个能够接收直流电压的滤波器的输入模块，第一臂 以及包括开关的第二臂，以及控制开关的机构，每个开关周期的周期操作，并且能够同时控制至少一个第一开关和至少一个第二开关，但偏移半个周期，由此第一开关是 当第二个开关闭合时打开，反之亦然。
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