公开(公告)号：US20240043142A1

公开(公告)日：2024-02-08

申请号：US18489551

申请日：2023-10-18

申请人： Nano-Product Engineering, LLC

发明人： Vladimir Gorokhovsky

IPC分类号： B64G1/40 ,  F03H1/00 ,  H05H1/50

CPC分类号： B64G1/413 ,  F03H1/0037 ,  H05H1/50 ,  F03H1/0043

摘要： An apparatus generates energetic particles and generates a plasma of a vaporized solid material and gaseous precursors for the application of coatings to surfaces of a substrate by way of condensation of plasma and for electric propulsion applications.

公开(公告)号：US11754058B2

公开(公告)日：2023-09-12

申请号：US17605568

申请日：2020-09-30

申请人： NATIONAL UNIVERSITY OF DEFENSE TECHNOLOGY

发明人： Jianjun Wu ,  Yu Zhang ,  Biqi Wu ,  Yuqiang Cheng ,  Jian Li ,  Sheng Tan ,  Yang Ou ,  Peng Zheng ,  Yuanzheng Zhao ,  Haoyi Wang

IPC分类号： F03H1/00

CPC分类号： F03H1/0006 ,  F03H1/0037 ,  F03H1/0081

摘要： An intelligent control gas suction-type electric propulsion system applicable to multi-flow regimes: an ultra-low orbit rare gas is used as a working medium for attitude orbit control and resistance compensation propulsion, the gas is collected and inputted into an intelligent feedback pressurization system by means of a parabolic gas intake duct, intelligent feedback and pressurization are performed on the gas working medium by a molecular pump and a gas pump and the medium is stored in a working fluid storage tank so as to supply a hybrid thruster system that consists of seven sets of electric thrusters to generate thrust, which may achieve multiple thrust modes, and achieve the purpose of attitude orbit control and resistance compensation.

公开(公告)号：US09854660B2

公开(公告)日：2017-12-26

申请号：US14410488

申请日：2013-06-18

申请人： THE UNIVERSITY OF SURREY ,  ASTRIUM LIMITED

发明人： Aaron Kombai Knoll

IPC分类号： H05H5/02 ,  F03H1/00 ,  H01J27/14 ,  H01J27/20

CPC分类号： H05H5/02 ,  F03H1/0037 ,  F03H1/0068 ,  H01J27/146 ,  H01J27/205

摘要： 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.

公开(公告)号：US09670913B2

公开(公告)日：2017-06-06

申请号：US14577260

申请日：2014-12-19

申请人： The Boeing Company

发明人： Vyacheslav Khozikov ,  Shengyi Liu

IPC分类号： F03H1/00 ,  B64C39/02 ,  H05H1/24 ,  H05H1/54 ,  B64D27/24 ,  B64C23/00

CPC分类号： F03H1/0081 ,  B64C23/005 ,  B64C39/02 ,  B64C39/028 ,  B64D27/24 ,  F03H1/0012 ,  F03H1/0037 ,  H05H1/2406 ,  H05H1/54 ,  H05H2001/2412 ,  H05H2001/2431 ,  H05H2001/2462

摘要： A plasma propulsion nozzle incorporates a cylinder having an inlet and an outlet. A plurality of substantially cylindrical planarly disbanded electrodes with sandwiched dielectric spacers is cascaded in an array to be concentrically expanding from the inlet through an interior chamber to the outlet for a nozzle. A voltage source applies aperiodic signal with rapidly reversing polarity to the electrodes with differential phase applied to adjacent electrodes in the array creating and expelling plasma clusters at each dielectric spacer inducing flow from the nozzle outlet to produce thrust.

公开(公告)号：US09657725B2

公开(公告)日：2017-05-23

申请号：US14628254

申请日：2015-02-22

申请人： Gil Berl

发明人： Gil Berl

IPC分类号： F03H1/00

CPC分类号： F03H1/0081 ,  F03H1/0037 ,  F03H1/0043 ,  F03H1/0056

摘要： An ion thruster, comprising: a discharge chamber for accelerating ions towards one direction; an inflow opening for intake of a propellant into the discharge chamber; a discharge cathode, shaped in a form of a propeller, for releasing electrons in the discharge chamber, thereby ionizing the propellant in the discharge chamber, wherein the discharge cathode is rotatable around an axis, thereby propelling inward to the discharge chamber the propellant thereof; an outflow opening for exhausting the ions from the discharge chamber; and an accelerator electrode, shaped in a form of a propeller, for accelerating the ions towards the one direction of the outflow opening, wherein the accelerator electrode is rotatable around an axis, thereby propelling outward from the discharge chamber the ions and neutral atoms thereof; wherein the ion thruster comprises electromagnetic coils for generating a magnetic field inside the discharge chamber.

公开(公告)号：US09650159B2

公开(公告)日：2017-05-16

申请号：US14913975

申请日：2014-08-29

申请人： THALES

发明人： Alexandre Kaltenbach

IPC分类号： B64G1/00 ,  B64G1/24 ,  B64G1/40 ,  F03H1/00

CPC分类号： B64G1/007 ,  B64G1/242 ,  B64G1/40 ,  B64G1/405 ,  B64G2001/245 ,  F03H1/0037

摘要： An electric propulsion device for a satellite equipped with at least four active thrusters exerting a parallel thrust upon a transfer, the device comprises means for detecting a thruster failure and means for reorienting the thrusters, and comprises means for computing a reorientation angle of the thrusters remaining active upon a failure of a thruster, the value of the angle being computed to reorient at least two of the remaining thrusters in order to cancel the total torque about the center of mass of the satellite.

公开(公告)号：US20170064806A1

公开(公告)日：2017-03-02

申请号：US15307482

申请日：2015-04-10

申请人： MITSUBISHI HEAVY INDUSTRIES, LTD.

发明人： Tatsufumi AOI ,  Kengo YAMAGUCHI ,  Ryuichi MATSUDA ,  Akio IKEDA ,  Hirofumi SHIMIZU ,  Takuya YAMAZAKI ,  Tatsuya KIMURA

IPC分类号： H05H1/46 ,  G01R29/24 ,  G01N21/71 ,  F03H1/00 ,  H05H1/54

CPC分类号： H05H1/46 ,  F03H1/0037 ,  F03H1/0081 ,  G01N21/718 ,  G01R29/24 ,  H05H1/0037 ,  H05H1/54 ,  H05H2001/4645

摘要： Provided are a plasma generation apparatus including a measurement device and capable of controlling conditions of plasma properly and stably, and a plasma thruster using the plasma generation apparatus. A plasma generation apparatus including a measurement device of the present invention includes a discharge vessel, a light-emitting monitor, a probe measuring instrument, a control device, and an optical axis driving unit. The discharge vessel ionizes gas which is introduced to an inside thereof so as to generate plasma. The light-emitting monitor measures electron density of the plasma by emission spectra of the plasma. The probe measuring instrument measures the electron density of the plasma by a probe disposed in the discharge vessel.

摘要翻译： 提供了一种包括测量装置并能够适当且稳定地控制等离子体的等离子体产生装置以及使用等离子体产生装置的等离子体推进器。 包括本发明的测量装置的等离子体产生装置包括放电容器，发光监视器，探针测量仪器，控制装置和光轴驱动单元。 放电容器将引入其内部的气体电离以产生等离子体。 发光监视器通过等离子体的发射光谱测量等离子体的电子密度。 探头测量仪器通过设置在放电容器中的探针来测量等离子体的电子密度。

公开(公告)号：US20160333866A1

公开(公告)日：2016-11-17

申请号：US15218682

申请日：2016-07-25

申请人： CALIFORNIA INSTITUTE OF TECHNOLOGY

发明人： Dan Michael GOEBEL ,  Richard Robert HOFER ,  Ioannis G. MIKELLIDES

IPC分类号： F03H1/00 ,  B64G1/40

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 nonmagnetically 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： 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装置已经被证明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：US09410539B2

公开(公告)日：2016-08-09

申请号：US13577657

申请日：2011-02-08

申请人： Giulio Manzoni

发明人： Giulio Manzoni

IPC分类号： B64G1/40 ,  F03H1/00 ,  H05H1/50 ,  H05H1/54

CPC分类号： F03H1/0037 ,  B64G1/40 ,  B64G1/405 ,  B64G1/406 ,  F03H1/00 ,  F03H1/0043 ,  F03H1/0056 ,  F03H1/0081 ,  F03H1/0087 ,  F03H1/0093 ,  H05H1/50 ,  H05H1/54

摘要： A micro-nozzle thruster comprising a micro-nozzle having an inlet at a first end perpendicularly aligned gas supply channel at a first end, and a thruster outlet at a second opposed end; said inlet in fluid communication with a gas supply channel, said gas supply channel perpendicularly aligned with a longitudinal axis of the micro-nozzle; a cathode within the gas supply channel and an anode external to the gas supply channel and proximate to the inlet, so as to create a plasma flow from said gas.

摘要翻译： 一种微喷嘴推进器，包括微喷嘴，所述微喷嘴在第一端处具有在第一端垂直对齐的气体供应通道的入口和在第二相对端处的推进器出口; 所述入口与气体供应通道流体连通，所述气体供应通道与微喷嘴的纵向轴线垂直对准; 气体供应通道内的阴极和气体供应通道外部并靠近入口的阳极，从而产生来自所述气体的等离子体流。

公开(公告)号：US09003767B2

公开(公告)日：2015-04-14

申请号：US13816408

申请日：2011-07-27

申请人： Frederic Marchandise ,  Michael Oberg ,  Gerard Passagot

发明人： Frederic Marchandise ,  Michael Oberg ,  Gerard Passagot

IPC分类号： F03H1/00 ,  B64G1/40

CPC分类号： F03H1/0012 ,  B64G1/405 ,  F03H1/0018 ,  F03H1/0037

摘要： An electric thruster includes at least one electric engine, a feed system for the engine including a high-pressure tank of ionizable gas, a low-pressure buffer tank connected to the high-pressure tank by a valve, and a system of pipes for conveying the gas from the low-pressure buffer tank to an anode and to a cathode of the engine. The low-pressure buffer tank is in open connection with the engine. The thruster detects that a magnitude of the discharge current between the anode and the cathode is less than a threshold value and switches off the discharge voltage as a result of the detection. The thruster can be for use in a satellite.

摘要翻译： 电推进器包括至少一个电动发动机，用于发动机的进料系统，其包括可电离气体的高压罐，通过阀连接到高压罐的低压缓冲罐，以及用于输送的管道系统 从低压缓冲罐到发动机的阳极和阴极的气体。 低压缓冲罐与发动机处于开放连接状态。 推进器检测到阳极和阴极之间的放电电流的大小小于阈值，并且由于检测而关闭放电电压。 推进器可用于卫星。