公开(公告)号：US12049878B2

公开(公告)日：2024-07-30

申请号：US17896651

申请日：2022-08-26

Applicant: The Trustees of Princeton University

Inventor： Jacob Simmonds ,  Yevgeny Raitses

IPC: F03H1/00

CPC classification number: F03H1/0068

Abstract: Disclosed is a miniaturized plasma propulsion device with minimized surface area of the thruster walls exposed to the plasma and, as a result, reduced plasma-surface interactions including a set of segmented electrodes to facilitate the following improvements compared to relevant existing technologies: 1) control of the plasma flow including focusing of the plasma plume 2) increase of the thrust 2) reduction of inefficiencies associated with the electron cross field current, and 3) mitigation of low frequency oscillations. The electrodes affect all these actions when a DC or modulated voltage is applied to one or all of them with the same or different amplitudes, with the same or different frequencies or phases which are all optimized to realize the best performance through changes in the acceleration and/or ionization regions. In addition, the applied voltage to the main electrodes may also be modulated.

公开(公告)号：US11905937B2

公开(公告)日：2024-02-20

申请号：US18029382

申请日：2021-11-15

Applicant: SHANGHAI INSTITUTE OF SPACE PROPULSION

Inventor： Zhen Zhao ,  Jiabing Cheng ,  Xiaolu Kang ,  Yanan Wang ,  Leichao Tian ,  Zhiyuan Zhang ,  Qingqing Jia ,  Caixia Qiao ,  Guanrong Hang

IPC: F03H1/00

CPC classification number: F03H1/0068 ,  F03H1/0006

Abstract: A magnetic pole structure for a Hall thruster is provided. The magnetic pole structure includes: multiple wide-envelope outer magnetic pole components, a magnetic bridge, a pagoda-shaped inner magnetic pole component, a top plate, and a bottom plate, where the multiple wide-envelope outer magnetic pole components are arranged on an outer edge of the Hall thruster, symmetrical about the pagoda-shaped inner magnetic pole component, and enclose a semi-open structure; the magnetic bridge is located between each of the wide-envelope outer magnetic pole components and the pagoda-shaped inner magnetic pole component; the bottom plate is attached to a bottom part of each of the wide-envelope outer magnetic pole components and a bottom part of the pagoda-shaped inner magnetic pole component; and the top plate is attached to an upper part of each of the wide-envelope outer magnetic pole components.

公开(公告)号：US20230358216A1

公开(公告)日：2023-11-09

申请号：US18029382

申请日：2021-11-15

Applicant: SHANGHAI INSTITUTE OF SPACE PROPULSION

Inventor： Zhen ZHAO ,  Jiabing CHENG ,  Xiaolu KANG ,  Yanan WANG ,  Leichao TIAN ,  Zhiyuan ZHANG ,  Qingqing JIA ,  Caixia QIAO ,  Guanrong HANG

IPC: F03H1/00

CPC classification number: F03H1/0068 ,  F03H1/0006

Abstract: A magnetic pole structure for a Hall thruster is provided. The magnetic pole structure includes: multiple wide-envelope outer magnetic pole components, a magnetic bridge, a pagoda-shaped inner magnetic pole component, a top plate, and a bottom plate, where the multiple wide-envelope outer magnetic pole components are arranged on an outer edge of the Hall thruster, symmetrical about the pagoda-shaped inner magnetic pole component, and enclose a semi-open structure; the magnetic bridge is located between each of the wide-envelope outer magnetic pole components and the pagoda-shaped inner magnetic pole component; the bottom plate is attached to a bottom part of each of the wide-envelope outer magnetic pole components and a bottom part of the pagoda-shaped inner magnetic pole component; and the top plate is attached to an upper part of each of the wide-envelope outer magnetic pole components.

公开(公告)号：US20180266403A1

公开(公告)日：2018-09-20

申请号：US15912673

申请日：2018-03-06

Applicant: Airbus Defence and Space GmbH

Inventor： Franz Georg HEY ,  Ulrich JOHANN ,  Guenter KORNFELD

IPC: F03H1/00 ,  B64G1/40

CPC classification number: F03H1/0068 ,  B64G1/405

Abstract: A cusped-field thruster for a space system, wherein the cusped-field thruster comprises: at least two substantially annular permanent magnets arranged in an antipolar manner, wherein a magnetic pole piece is formed between the permanent magnets, and an anode, which comprises a permanent-magnetic material. The cusped-field thruster is configured such that a cusp is formed in a region adjacent to the anode of the cusped-field thruster.

公开(公告)号：US20150373826A1

公开(公告)日：2015-12-24

申请号：US14410488

申请日：2013-06-18

Applicant: THE UNIVERSITY OF SURREY ,  ASTRIUM LIMITED

Inventor： Aaron Kombai KNOLL

IPC: H05H5/02 ,  F03H1/00 ,  H01J27/20

CPC classification number: H05H5/02 ,  F03H1/0037 ,  F03H1/0068 ,  H01J27/146 ,  H01J27/205

Abstract: An ion accelerator includes: an inner magnet having a channel extending through it in an axial direction; an outer magnet extending around the inner magnet, the magnets having like polarities so as to produce a magnetic field having two locations of zero magnetic field strength. The locations are spaced apart in the axial direction; and an anode and a cathode are arranged to generate an electrical potential difference between the locations.

Abstract translation: 离子加速器包括：具有沿轴向延伸穿过其的通道的内部磁体; 围绕内磁体延伸的外磁体，磁体具有相同的极性，从而产生具有零磁场强度的两个位置的磁场。 这些位置沿轴向间隔开; 并且布置阳极和阴极以在位置之间产生电位差。

公开(公告)号：US20140090357A1

公开(公告)日：2014-04-03

申请号：US14123175

申请日：2012-05-23

Applicant: Stephan Joseph Zurbach ,  Frederic Marchandise ,  Michael Oberg

Inventor： Stephan Joseph Zurbach ,  Frederic Marchandise ,  Michael Oberg

IPC: F03H1/00

CPC classification number: F03H1/0018 ,  F03H1/0062 ,  F03H1/0068 ,  F03H1/0075 ,  F03H1/0087

Abstract: A Hall effect thruster includes at least one tank of gas under high pressure, a pressure regulator module, a gas flow rate control device, an ionization channel, a cathode placed in a vicinity of an outlet from the ionization channel, an anode associated with the ionization channel, an electrical power supply unit, an electric filter, coils for creating a magnetic field around the ionization channel, and an additional electrical power supply unit for applying a pulsating voltage between the anode and the cathode.

Abstract translation: 霍尔效应推进器包括至少一个高压气体罐，压力调节器模块，气体流速控制装置，离子化通道，放置在离电离通道出口附近的阴极，与 电离通道，电源单元，电动过滤器，用于在电离通道周围产生磁场的线圈，以及用于在阳极和阴极之间施加脉动电压的附加电源单元。

公开(公告)号：US20120311992A1

公开(公告)日：2012-12-13

申请号：US13579640

申请日：2010-03-01

Applicant: Toshiyuki Ozaki ,  Kimiya Komurasaki

Inventor： Toshiyuki Ozaki ,  Kimiya Komurasaki

IPC: F03H1/00 ,  H05H1/00

CPC classification number: H05H1/54 ,  B64G1/405 ,  F03H1/0012 ,  F03H1/0037 ,  F03H1/0062 ,  F03H1/0068 ,  F03H1/0075

Abstract: In a Hall thruster 10, an acceleration channel 12 ionizes propellant flowing into an annular discharge space 11 to generate ions, and accelerates and discharges the generated ions. A distributor 37 supplies propellant from a plurality of holes 13 arranged azimuthally, via an anode 14 penetrating to the discharge space 11 of the acceleration channel 12, to the discharge space 11 of the acceleration channel 12, an amount of the propellant varying according to positions of the plurality of holes 13, thereby generating a plurality of regions, between adjacent ones of which the mass flow rate of the propellant is different, azimuthally in the discharge space 11 of the acceleration channel 12. During that time, the distributor 37 adjusts, with respect to the mass flow rate of the propellant in the discharge space 11 of the acceleration channel 12, a differential within a range of 5 to 15% between the mass flow rate of the propellant in a region with a large mass flow rate of the propellant and the mass flow rate of the propellant in a region with a small mass flow rate of the propellant. Thus, the width of a operation parameter region with reduced discharge current oscillation of the Hall thruster 10 is expanded.

Abstract translation: 在霍尔推进器10中，加速通道12将流入环形放电空间11的推进剂电离以产生离子，并加速和排出所产生的离子。 分配器37经由穿过加速通道12的放电空间11的阳极14方位排列的多个孔13向加速通道12的放电空间11供给推进剂，推进剂的量根据位置而变化 ，从而在加速通道12的放电空间11中在方位角之间产生多个区域，其中相邻的区域之间的推进剂的质量流量不同。在此期间，分配器37调整， 相对于加速通道12的放电空间11中的推进剂的质量流量，在推进剂的质量流量与质量流量的大的质量流量之间的差为5〜15％ 推进剂和推进剂在推进剂质量流量较小的区域中的质量流量。 因此，扩大了霍尔推进器10的放电电流振荡减小的动作参数区域的宽度。

公开(公告)号：US4548033A

公开(公告)日：1985-10-22

申请号：US608354

申请日：1984-05-09

Applicant: Gordon L. Cann

Inventor： Gordon L. Cann

IPC: F03H1/00 ,  H05B7/18 ,  H05H1/34 ,  H05H1/40 ,  H05B7/00

CPC classification number: B64G1/406 ,  F03H1/0068 ,  H05B7/185 ,  H05H1/40 ,  H05H2001/3484

Abstract: This invention relates to a thruster apparatus applicable to the environment of a space vehicle or satellite and operable for positioning such vehicle or satellite in the proper orbital location. The device utilizes a unique configuration of passageways to convey the propellant to a location adjacent an electrical arc forming device. The propellant, heated thereby, then travels out a nozzle section of the thruster to thereby produce thrust. If desired, an external heater may be provided to preheat the thruster to thereby contribute to greater efficiency in the use of propellant. Further, if desired, the thruster may include an accelerator extension.

公开(公告)号：US12044220B2

公开(公告)日：2024-07-23

申请号：US17802468

申请日：2021-02-22

Applicant: The George Washington University

Inventor： Michael Keidar ,  Denis Zolotukhin ,  Siva Ram Prasad Bandaru

IPC: F03H1/00 ,  B64G1/40

CPC classification number: F03H1/0081 ,  B64G1/411 ,  B64G1/413 ,  B64G1/415 ,  F03H1/0068

Abstract: A satellite propulsion system and methods of operating the same include a first ionization stage and a second acceleration stage. The first ionization stage has a plasma source configured to produce an arc discharge and emit a preliminary plasma. The plasma source includes an external magnetic field configured to magnetize the arc discharge. The second acceleration stage has an accelerator positioned in series with the plasma source. The accelerator is configured to accelerate the preliminary plasma out through the accelerator, thereby creating an accelerated plasma flow. The application of an activation threshold voltage to the accelerator results in a surge in system performance parameters.

公开(公告)号：US20230279845A1

公开(公告)日：2023-09-07

申请号：US18117977

申请日：2023-03-06

Applicant: ORBION SPACE TECHNOLOGY, INC.

Inventor： Jason D. Sommerville

IPC: F03H1/00 ,  H01J27/14

CPC classification number: F03H1/0075 ,  F03H1/0068 ,  F03H1/0081 ,  H01J27/146

Abstract: A Hall-effect thruster assembly includes a plurality of magnetic sources for creating a magnetic circuit. The plurality of magnetic sources are positioned between a first end and a second, opposite end of the Hall-effect thruster. The plurality of magnetic sources define a longitudinal axis extending through the first end and the second end. The first end is configured as a discharge end. A mount assembly is coupled to the second end. The mount assembly is configured to secure the plurality of magnetic sources to a spacecraft. A magnetic element is supported by the mount assembly. The magnetic element is positioned relative to the plurality of magnetic sources by the mount assembly.