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公开(公告)号：US12078154B1
公开(公告)日：2024-09-03
申请号：US16153297
申请日：2018-10-05
CPC分类号： F03H1/0087 , B64G1/405 , F03H1/0018 , H01J1/025
摘要： The present disclosure generally pertains to devices and methods for generating thrust in vehicles, for instance in space applications. A heaterless, insertless hollow cathode utilizes AC and pulsed DC electric fields to ionize the propellant gas and generate a plasma plume. The cathode uses an argon microplasma generated in a quartz tube with a tungsten filament and brass ion collector. Free electrons are then drawn from the plasma plume and supplied to a thruster engine.
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公开(公告)号：US09181934B2
公开(公告)日：2015-11-10
申请号：US13683688
申请日：2012-11-21
申请人： The Boeing Company
发明人： John F. Stickelmaier , John Ziavras , Julie Marie Perkins , Kurt B. Kreiner , Glenn N. Caplin , Brian K. Smith , Peter S. Lauenstein
CPC分类号： F03H1/0043 , B64G1/405 , B64G1/42 , B64G1/428 , F03H1/0018 , H01H19/50 , H01H19/64
摘要： A gridded ion propulsion system comprising two power controllers, four ion thrusters, and two switch assemblies. One switch assembly is connected to the two power controllers and to two of the four ion thrusters. The other switch assembly is connected to the two power controllers and to the other two ion thrusters. Each switch assembly has first and second switching states which can be selected to enable either power controller to supply power to any one of the four ion thrusters. Each switch assembly comprises a respective movable body and a respective multiplicity of switches which change state in unison when the movable body changes position. For example, the movable body may be a rotatable hollow shaft driven by a stepper motor.
摘要翻译： 包括两个功率控制器，四个离子推进器和两个开关组件的网格离子推进系统。 一个开关组件连接到两个功率控制器和四个离子推进器中的两个。 另一个开关组件连接到两个电源控制器和另外两个离子推进器。 每个开关组件具有第一和第二开关状态，其可以被选择以使得功率控制器能够向四个离子推进器中的任何一个供电。 每个开关组件包括相应的可移动体和相应的多个开关，其在可移动体改变位置时一致地改变状态。 例如，可动体可以是由步进电动机驱动的可旋转中空轴。
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3.发明授权公开(公告)号：US09123850B2
公开(公告)日：2015-09-01
申请号：US12621877
申请日：2009-11-19
申请人： Edward H. Allen , Andrew G. York
发明人： Edward H. Allen , Andrew G. York
IPC分类号： H01S3/0937 , H01S3/095 , H01S3/0953 , B64G1/40 , F03H1/00 , H01L31/054
CPC分类号： H01L31/0547 , B64G1/405 , F03H1/00 , F03H1/0018 , F03H1/0081 , H01S3/0937 , H01S3/095 , H01S3/0953 , Y02E10/46 , Y02E10/52
摘要： An electric generator is disclosed that includes a duct configured to direct hyperthermal air molecules toward a source of exothermic fuel, a fuel dispenser configured to dispense fuel into a flow of the hyperthermal air molecules to cause a hyperthermic chemical reaction between the fuel and the hyperthermal air molecules that produces highly internally excited air molecules. The excited molecules amplify a seed current. Power harvesting cells are configured to capture and convert the amplified current to electricity.
摘要翻译： 公开了一种发电机，其包括被构造成将超热空气分子引向放热燃料源的管道，配置成将燃料分配到超热空气分子的流中以在燃料和超热空气之间引起高温化学反应的燃料分配器 产生高度内部激发的空气分子的分子。 激发的分子放大种子电流。 功率收集单元被配置为捕获并将放大的电流转换成电。
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公开(公告)号：US20110277444A1
公开(公告)日：2011-11-17
申请号：US13129943
申请日：2009-11-11
申请人： Hans Leiter , Johann Mueller , Horst Neumann , Frank Scholze
发明人： Hans Leiter , Johann Mueller , Horst Neumann , Frank Scholze
IPC分类号： F03H1/00
CPC分类号： H05H1/54 , B64G1/405 , B64G1/42 , B64G1/428 , F03H1/0018 , F03H1/0037 , H01J27/16
摘要： An ion drive for a spacecraft, including a high-frequency generator for generating an alternating electromagnetic field for the ionization of a propellant and an acceleration system for the charge carriers, is provided. The ion drive includes a voltage source with which the high voltages that are necessary for the acceleration system can be derived from the currents and/or voltages generated by the high-frequency generator for generating the alternating electromagnetic field.
摘要翻译： 提供了一种用于航天器的离子驱动器，包括用于产生用于推进剂电离的交变电磁场的高频发生器和用于电荷载体的加速系统。 离子驱动器包括电压源，通过该电压源可以从用于产生交变电磁场的高频发生器产生的电流和/或电压导出加速系统所需的高电压。
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公开(公告)号：US20100263349A1
公开(公告)日：2010-10-21
申请号：US12578404
申请日：2009-10-13
IPC分类号： F03H1/00
CPC分类号： F03H1/0018
摘要： To explore deeper expanses of space, rocket ships need rockets that can last twice as long as conventional rockets. Modern rockets use the electric field to attract and accelerate charged particles out and away from the combustion chamber. Space qualified components to increase the electric field are difficult to obtain. Various embodiments of the present subject matter use multiple phases of an input signal into the power supply to cause the output DC voltage signal to be substantially smooth. These smoother signals reduce the voltage requirements of the output diodes and capacitors thereby making them easier to obtain.
摘要翻译： 为了探索更广阔的空间，火箭船需要的火箭可以持续两倍于常规火箭。 现代火箭使用电场吸引和加速带电粒子离开燃烧室。 空间合格的部件增加电场难以获得。 本主题的各种实施例将输入信号的多个相位用于电源，以使输出直流电压信号基本上平滑。 这些更平滑的信号降低了输出二极管和电容器的电压要求，从而使它们更容易获得。
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公开(公告)号：US20090255231A1
公开(公告)日：2009-10-15
申请号：US11123374
申请日：2005-05-06
IPC分类号： F03H1/00
CPC分类号： F03H1/0037 , F03H1/0018
摘要： Conventional power supplies that actify the grids of electric rockets use an output capacitor to smooth the output DC voltage signal. Large capacitors tend to store a great amount of energy. Arcing acts to transfer this energy to create a well or pit on an accelerator grid of the electric rockets that may eventually cause repeating arcing or perforation on the accelerator grid. Various embodiments of the present invention eliminate or reduce the need to use an output capacitor. Additionally, various embodiments of the present invention use multiple phases of an input signal into the power supply to cause the output DC voltage signal to be substantially smooth.
摘要翻译： 激活电子火箭网格的传统电源使用输出电容器平滑输出直流电压信号。 大容量电容器倾向于储存大量的能量。 电弧作用是传递这种能量，以在电火箭的加速器网格上产生井或坑，这可能最终在加速器网格上引起重复的电弧或穿孔。 本发明的各种实施例消除或减少使用输出电容器的需要。 此外，本发明的各种实施例将输入信号的多个相位用于电源以使输出直流电压信号基本上平滑。
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公开(公告)号：US06541916B2
公开(公告)日：2003-04-01
申请号：US09774378
申请日：2001-01-30
申请人： Darwin K. Decker
发明人： Darwin K. Decker
IPC分类号： B64D3100
摘要： A satellite power distribution method for efficiently distributing power to satellite electric propulsion thrusters (24) is provided. The satellite includes spacecraft loads (20), an electric propulsion thruster (24), thruster auxiliary circuits (22), and a first power transformer (30). The first power transformer (30) has a primary winding (32) coupled to a first energy source (12) that supplies satellite power. A first secondary winding (36) of the first power transformer (30) is coupled to the spacecraft loads (20) for supplying primary power. The power distribution method includes the steps of first coupling a second secondary winding (34) to the first power transformer (30) for converting the satellite power to thruster discharge power which is rectified. The rectified discharge power is filtered to obtain power that is supplied to the electric propulsion thruster (24). Finally, satellite power is converted to auxiliary power for powering the thruster auxiliary circuits (22).
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公开(公告)号：US20020100841A1
公开(公告)日：2002-08-01
申请号：US09774378
申请日：2001-01-30
发明人： Darwin K. Decker
IPC分类号： B64G001/40 , B64G001/42
摘要： A satellite power distribution method for efficiently distributing power to satellite electric propulsion thrusters (24) is provided. The satellite includes spacecraft loads (20), an electric propulsion thruster (24), thruster auxiliary circuits (22), and a first power transformer (30). The first power transformer (30) has a primary winding (32) coupled to a first energy source (12) that supplies satellite power. A first secondary winding (36) of the first power transformer (30) is coupled to the spacecraft loads (20) for supplying primary power. The power distribution method includes the steps of first coupling a second secondary winding (34) to the first power transformer (30) for converting the satellite power to thruster discharge power which is rectified. The rectified discharge power is filtered to obtain power that is supplied to the electric propulsion thruster (24). Finally, satellite power is converted to auxiliary power for powering the thruster auxiliary circuits (22).
摘要翻译： 提供了一种用于向卫星电动推进器（24）有效分配电力的卫星配电方法。 卫星包括航天器负载（20），电推进推进器（24），推进器辅助回路（22）和第一电力变压器（30）。 第一电力变压器（30）具有耦合到提供卫星电力的第一能量源（12）的初级绕组（32）。 第一电力变压器（30）的第一次级绕组（36）联接到用于提供主电力的航天器负载（20）。 功率分配方法包括以下步骤：首先将第二次级绕组（34）耦合到第一电力变压器（30），以将卫星功率转换为被整流的推进器放电功率。 经整流的放电功率被滤波以获得供应给电推进推进器（24）的功率。 最后，将卫星功率转换成用于为推进器辅助回路（22）供电的辅助动力。
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公开(公告)号：US5359180A
公开(公告)日：1994-10-25
申请号：US956131
申请日：1992-10-02
CPC分类号： F03H1/0018 , G05F1/59 , H02J1/102 , H02J9/061 , H02J1/108 , Y10T307/653 , Y10T307/724
摘要： A power supply system for thrusters (e.g., arcjet thrusters) in a spacecraft system comprises lightweight, redundant power supplies that share the power distribution function to the thrusters. Each power supply comprises a plurality of parallel-connected power supply subunits of which the combined power output capability exceeds the required maximum power demand by at least one subunit capacity for each arcjet thruster in the system. Each power supply subunit comprises a lightweight, high-frequency, soft-switching power supply. For arcjet systems comprising arcjet thrusters that do not operate simultaneously, relays are employed to switch between thrusters.
摘要翻译： 在航天器系统中的用于推进器（例如，电弧喷射推进器）的供电系统包括与推进器共享功率分配功能的轻量级冗余电源。 每个电源包括多个并联连接的电源子单元，其中组合的功率输出能力超过系统中每个电弧喷射推进器的至少一个子单元容量所需的最大功率需求。 每个电源子单元包括轻便的高频软开关电源。 对于包括不同时操作的电弧喷射推进器的电弧喷射系统，采用继电器在推进器之间切换。
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公开(公告)号：US11939966B2
公开(公告)日：2024-03-26
申请号：US17117049
申请日：2020-12-09
发明人： Jeffrey Greason
CPC分类号： F03H1/0018 , B64G1/405 , F03H1/0081 , F03H1/0025
摘要： The present technology is directed to plasma systems and associated methods, including propulsion systems for flight vehicles. A representative system includes a plurality of coils. The coils include a first coil positioned along a force axis, a second coil positioned along the force axis and spaced apart from the first coil, and a third coil that is magnetically shielded. A controller is operatively coupled to the coils and is configured to (a) increase energy to the first coil to generate a magnetic field in a portion of the plasma adjacent to the first coil, (b) decrease energy to the first coil and increase energy to the second coil to translate the resulting superposed magnetic field through the plasma to a position adjacent the second coil, and (c) transfer energy from the second coil to the third coil and decrease energy to the second coil to reduce the magnetic field in the plasma.
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