-
公开(公告)号：US20240017852A1
公开(公告)日：2024-01-18
申请号：US17987527
申请日：2022-11-15
申请人： Earth Observant Inc.
CPC分类号： B64G1/242 , B64G1/413 , B64G1/52 , F03H1/0075 , G02B23/02
摘要： A satellite having a longitudinally elongated body and being capable of operating in the thermosphere. The satellite can be powered by an electric rocket engine, and includes a remote sensing system configured to obtain images of Earth. An elongated axis about which the elongated body extends can be generally aligned with a forward direction of the satellite, with a viewing angle from the satellite oriented transverse to the elongated axis. A center of mass of the satellite can be forward of a center of drag to produce positive natural stability. The remote sensing system, which can be part of a payload, can include a movable mirror and one or more movable optical elements. A first mirror can be pivoted, and/or other optical elements, including the payload, can be rotated about the axis of the elongated body. Counter-acting masses can be used to null motion of the movable components.
-
2.发明授权公开(公告)号：US11815074B1
公开(公告)日：2023-11-14
申请号：US16912946
申请日：2020-06-26
CPC分类号： F03H1/0075 , F03H1/0012 , F03H1/0018 , B64G1/405
摘要： Scalable power processing units (PPUs) for Hall-effect thrusters (HETs) and terrestrial systems are disclosed. A technique for current estimation may be employed on each output of parallel isolated discharge supply modules (DSMs) to force proper current/load sharing between the DSMs. A flyback power supply may be used that performs the dual functions of a cathode keeper plasma ignitor and sustainer. The flyback power supply may be tuned for a high no-load direct current (DC) output voltage to achieve cathode keeper ignition rather than requiring a separate ignitor supply, which reduces circuit complexity. To address requirements for higher voltage DC ignition than are achievable with a flyback power supply alone, a supplemental DC ignitor may be placed in parallel with the flyback power supply of some embodiments. Such simplified PPU architectures may provide a high efficiency, low part count, scalable architecture suitable for more compact and lower cost system designs.
-
公开(公告)号：US20230150697A1
公开(公告)日：2023-05-18
申请号：US17918303
申请日：2020-10-09
CPC分类号： B64G1/401 , B64G1/402 , F02K9/62 , F03H1/0075 , B64G1/405
摘要： A thrust generator is provided for producing thrust to move a spacecraft. The thrust generator includes a housing having a first end and an opposing second end. The first end is associated with a mount for coupling to the spacecraft. The housing further defines a central axis extending through the first end and the second end. The second end defines an annular propulsion outlet. At least one nozzle is positioned proximate the second end. The thrust generator is selectively operable in a first mode in which the thrust generator uses propellant to electrostatically generate thrust via the annular propulsion outlet, and a second mode in which the thrust generator uses propellant to gas-dynamically generate thrust via the at least one nozzle.
-
公开(公告)号：US09897079B2
公开(公告)日：2018-02-20
申请号：US15387658
申请日：2016-12-22
申请人： Burak Karadag
发明人： Burak Karadag
CPC分类号： F03H1/0075 , B64G1/405 , F03H1/0012 , F03H1/0062 , F03H1/0068 , H01J27/143 , H01J27/146
摘要： The invention is a Hall thruster that does not have any discharge channel, and magnetic pole piece. The Hall thruster utilizes permanent magnets to produce magnetic field with strong radial component in front of an annular anode, and expands propellant directly into vacuum through the anode acting also as a gas distributor. The invention reduces mass and complexity of conventional Hall thrusters, and offers a radical solution to discharge channel and magnetic pole piece erosion problem.
-
5.发明授权公开(公告)号：US09494143B1
公开(公告)日：2016-11-15
申请号：US14152125
申请日：2014-01-10
发明人： Michael J. Patterson
CPC分类号： F03H1/0037 , B64G1/405 , F03H1/0043 , F03H1/0075 , H01J27/024
摘要： Ion optics for use in a conventional or annular or other shaped ion thruster are disclosed including a plurality of planar, spaced apart ion optic electrode pairs sized to include a diameter smaller than the diameter of thruster exhaust and retained in, on or otherwise associated with a frame across the thruster exhaust. An electrical connection may be provided for establishing electrical connectivity among a set of first upstream electrodes and an electrical connection may be provided for establishing electrical connectivity among the second downstream electrodes.
摘要翻译： 公开了用于常规或环形或其他形状离子推进器的离子光学器件，其包括多个平面间隔开的离子光电极对，其尺寸被设计成包括直径小于推进器排气的直径并且保持在其中或与其相关联 框架横跨推进器排气。 可以提供电连接以在一组第一上游电极之间建立电连接，并且可以提供用于在第二下游电极之间建立电连接性的电连接。
-
公开(公告)号：US09476413B2
公开(公告)日：2016-10-25
申请号：US14343951
申请日：2012-08-03
CPC分类号： F03H1/0037 , B64G1/007 , B64G1/242 , B64G1/405 , B64G1/428 , F03H1/0012 , F03H1/0018 , F03H1/0075
摘要： An electric propulsion system includes a first stationary plasma thruster including a single first cathode, a first anode, and a first gas manifold, and a second stationary plasma thruster including a single second cathode, a second anode, and a second gas manifold. The system further includes an electrical connection device common to the first and second cathodes, first and second gas flow rate control devices with a common fluid flow device for feeding gas, and a selective control device for activating at any given instant only one of the first and second cathodes in co-operation with one or the other of the first and second anodes.
摘要翻译： 电推进系统包括第一固定等离子体推进器，其包括单个第一阴极，第一阳极和第一气体歧管，以及包括单个第二阴极，第二阳极和第二气体歧管的第二固定等离子体推进器。 该系统还包括与第一和第二阴极共用的电连接装置，具有用于供给气体的公共流体流动装置的第一和第二气体流量控制装置，以及用于在任何给定时刻激活第一和第二阴极中的一个的选择性控制装置 第二阴极与第一和第二阳极中的一个或另一个相配合。
-
公开(公告)号：US09453502B2
公开(公告)日：2016-09-27
申请号：US13768788
申请日：2013-02-15
CPC分类号： F03H1/0075 , B64G1/40 , B64G1/405 , F03H1/00 , F03H1/0012 , F03H1/0037 , F03H1/0062 , F03H1/0068 , F03H1/0081
摘要： A Hall thruster apparatus having walls constructed from a conductive material, such as graphite, and having magnetic shielding of the walls from the ionized plasma has been demonstrated to operate with nearly the same efficiency as a conventional non-magnetically shielded design using insulators as wall components. The new design is believed to provide the potential of higher power and uniform operation over the operating life of a thruster device.
摘要翻译： 已经证明具有由诸如石墨的导电材料构成的壁并且具有壁与电离等离子体的磁屏蔽的霍尔推进器设备以与使用绝缘体作为壁部件的常规非磁屏蔽设计几乎相同的效率来运行 。 相信这种新设计可以在推进器装置的使用寿命内提供更高功率和统一的操作的潜力。
-
公开(公告)号：US09145216B2
公开(公告)日：2015-09-29
申请号：US13223041
申请日：2011-08-31
CPC分类号： B64G1/402 , B64G1/404 , F02K9/72 , F02K9/94 , F03H1/00 , F03H1/0006 , F03H1/0012 , F03H1/0043 , F03H1/005 , F03H1/0062 , F03H1/0068 , F03H1/0075
摘要： A spacecraft propulsion system has at least one chemical thruster, at least one electric thruster, a propellant supply arrangement that stores a propellant and a propellant conditioning arrangement configured to convert propellant into chemical species in a thermodynamic phase that can be readily ionized. The propellant is commonly supplied from the propellant storage device to each of the chemical thruster and the electric thruster. The chemical thruster has a gas generator and a high thrust accelerator; the electric thruster has a plasma generator and a high specific impulse accelerator. The propellant supply arrangement is configured to control flow of the propellant from the propellant supply arrangement to the gas generator and the propellant conditioning arrangement, and a first flow path connects propellant supply arrangement with the gas generator, and a second flow path connects propellant supply arrangement with the plasma generator.
摘要翻译： 航天器推进系统具有至少一个化学推进器，至少一个电推进器，推进剂供应装置，其存储推进剂和推进剂调节装置，所述推进剂调节装置构造成将推进剂转化为能容易地电离的热力学相中的化学物质。 推进剂通常从推进剂储存装置提供给每个化学推进器和电推进器。 化学推进器具有气体发生器和高推力加速器; 电推进器具有等离子体发生器和高比冲速加速器。 推进剂供应装置被配置为控制推进剂从推进剂供应装置到气体发生器和推进剂调节装置的流动，并且第一流动路径将推进剂供应装置与气体发生器连接，第二流动路径连接推进剂供应装置 与等离子发生器。
-
9.发明授权Autonomous method and system for minimizing the magnitude of plasma discharge current oscillations in a hall effect plasma device 有权用于最小化霍尔效应等离子体装置中的等离子体放电电流振荡的幅度的自动方法和系统公开(公告)号：US08907578B2
公开(公告)日：2014-12-09
申请号：US13621342
申请日：2012-09-17
申请人： Vladimir Hruby , Nathaniel Demmons , Eric Ehrbar , Bruce Pote , Nathan Rosenblad
发明人： Vladimir Hruby , Nathaniel Demmons , Eric Ehrbar , Bruce Pote , Nathan Rosenblad
CPC分类号： H05H1/00 , F03H1/0075 , H05H1/54
摘要： An autonomous method for minimizing the magnitude of plasma discharge current oscillations in a Hall effect plasma device includes iteratively measuring plasma discharge current oscillations of the plasma device and iteratively adjusting the magnet current delivered to the plasma device in response to measured plasma discharge current oscillations to reduce the magnitude of the plasma discharge current oscillations.
摘要翻译： 用于最小化霍尔效应等离子体装置中的等离子体放电电流振荡的幅度的自主方法包括迭代地测量等离子体装置的等离子体放电电流振荡，并且响应于测量的等离子体放电电流振荡迭代地调整输送到等离子体装置的磁体电流以减少 等离子体放电电流振荡的幅度。
-
公开(公告)号：US20140290210A1
公开(公告)日：2014-10-02
申请号：US14360099
申请日：2012-11-19
申请人： SNECMA
IPC分类号： F03H1/00
CPC分类号： F03H1/0006 , B64G1/405 , F03H1/0062 , F03H1/0068 , F03H1/0075
摘要： A steerable-thrust Hall effect thruster in which a final stage of a magnetic circuit includes an inner pole and a facing outer pole, the inner pole being offset axially downstream relative to the outer pole, so that a magnetic field is inclined relative to a transverse plane of the thruster.
摘要翻译： 一种可转向推力霍尔效应推进器，其中磁路的最后一级包括内极和相对的外极，内极相对于外极轴向下游偏移，使得磁场相对于横向 推进器的平面。
-
-
-
-
-
-
-
-
-
搜索结果
129 条记录 (耗时 0.022 秒)
