公开(公告)号：US3110154A

公开(公告)日：1963-11-12

申请号：US8739461

申请日：1961-02-06

申请人： UNITED AIRCRAFT CORP

发明人： EDELBAUM THEODORE N ,  PINSLEY EDWARD A

IPC分类号： F03H1/00

CPC分类号： F03H1/0037 ,  Y10S376/906

公开(公告)号：US20240309858A1

公开(公告)日：2024-09-19

申请号：US18585369

申请日：2024-02-23

申请人： Orbital Arc Corporation

发明人： Jonathan Huffman

IPC分类号： B64G1/40 ,  F03H1/00

CPC分类号： F03H1/0037 ,  F03H1/0025 ,  B64G1/413

摘要： A propulsion device for vehicles, such as a spacecraft operating within a vacuum configured to ionize a fuel gas. Specifically, a soft ionization system pulls electrons from passing gas molecules directly into conductors and introduces ionized gas molecules into a static accelerating field. The ionized gas is utilized at a point of creation such that a chamber, housing, or channel to contain the ionized gas is not required.

公开(公告)号：US20240068454A1

公开(公告)日：2024-02-29

申请号：US18229516

申请日：2023-08-02

申请人： The Research Foundation for the State University of New York

发明人： Adrian Ieta ,  Marius Chirita-Mihaila

IPC分类号： F03H1/00 ,  B64D27/24

CPC分类号： F03H1/0037 ,  B64D27/24

摘要： An ionic wind propulsion system with a toroidal counter electrode that allows in-atmosphere propulsion in negative polarity. There are pin emitters extended on the trailing edge of a propeller placed above the toroidal counter-electrode that provides axial thrust with a corona discharge upon an electric current being applied. Axial thrust occurs due to the linear acceleration of ions between electrodes and the induced rotary motion of the propeller which captures the energy and momentum of ions accelerated in the propeller's rotational plane. An array of propellers and toroidal counter electrodes can be used to power aircraft, such as drones.

公开(公告)号：US20230382569A1

公开(公告)日：2023-11-30

申请号：US18027661

申请日：2021-09-23

申请人： Undefined Technologies Corp.

发明人： Tomas A. Pribanic

IPC分类号： B64U10/20 ,  B64U60/50 ,  B64U20/20 ,  B64U50/18 ,  H05K7/20 ,  F03H1/00

CPC分类号： B64U10/20 ,  B64U60/50 ,  B64U20/20 ,  B64U50/18 ,  H05K7/20145 ,  F03H1/0037 ,  B64U2101/30

摘要： Low noise vertical take-off and landing (VTOL) unmanned air vehicle. A vertical take-off and landing unmanned vehicle which generates low levels of noise includes an ion thruster providing a thrust in a vertical direction, and a thrust vectoring system providing thrust in at least one of a forward, aft, left, and right direction, when the unmanned vehicle is in flight

公开(公告)号：US20180106243A1

公开(公告)日：2018-04-19

申请号：US15573248

申请日：2016-05-12

申请人： AIRBUS DEFENCE AND SPACE LIMITED ,  University of Surrey

发明人： Aaron Knoll ,  Paolo Bianco

IPC分类号： F03H1/00 ,  H02K44/10 ,  H02K44/16

CPC分类号： F03H1/0012 ,  F03H1/0037 ,  F03H1/0075 ,  F03H1/0081 ,  H02K44/08 ,  H02K44/085 ,  H02K44/10 ,  H02K44/16 ,  H02N3/00

摘要： A method of producing a charge separation in a plasma having a low particle density which comprises a plurality of electrons and a plurality of positive ions. The method includes generating a magnetic field and passing the plasma having a low particle density along a first axis through the magnetic field. The magnetic field is generated having a component which is perpendicular to the first axis and is configured so as to deflect the plurality of electrons from the first axis and allow the plurality of positive ions to travel substantially undeflected along the first axis. Also provided is a magnetohydrodynamic generator and a low earth orbit thruster making use of the charge separation mechanism.

公开(公告)号：US20180051679A1

公开(公告)日：2018-02-22

申请号：US15552198

申请日：2016-02-19

申请人： COMMONWEALTH OF AUSTRALIA AS REPRESENTED BY DEFEN- CE SCIENCE AND TECHNOLOGY GROUP OF THE DEPARTMENT ,  THE UNIVERSITY OF SYDNEY THE UNIVERSITY OF SYDNEY

发明人： Joseph Khachan ,  Lachlan John Emblen Blackhall ,  Xioafeng Wu ,  Iain Cartwright ,  Weitang Li ,  Shyam Mehta ,  B. Upul Heyshan Mendis

IPC分类号： F03H1/00 ,  B64G1/40 ,  H05H1/48 ,  H05H1/50

CPC分类号： F03H1/0025 ,  B64G1/405 ,  F03H1/0037 ,  H05H1/48 ,  H05H1/50

摘要： A thruster comprising: a chamber to contain a fluid; a plurality of nozzles to exhaust neutral particles derived from the fluid in the chamber, wherein each nozzle has a converging section and the converging section includes a first electrode; a second electrode located distal to the first electrode to provide a voltage differential between the first and second electrodes sufficient to create plasma ions from the fluid and the voltage differential accelerates the plasma ions on a flow path through the converging section, and wherein at least one or more of the accelerated plasma ions are neutralised to form the neutral particles by charge exchange with other neutral particles, or by recombination with electrons, on the flow path.

公开(公告)号：US09784251B2

公开(公告)日：2017-10-10

申请号：US14001890

申请日：2012-03-01

申请人： Andrew D. Zonenberg ,  Jason D. Sanchez ,  Piotr A. Garbuz

发明人： Andrew D. Zonenberg ,  Jason D. Sanchez ,  Piotr A. Garbuz

IPC分类号： F03H1/00 ,  F02K3/08 ,  F02K9/46 ,  F02K9/62 ,  F02K9/80 ,  F03H99/00

CPC分类号： F03H1/0037 ,  F02K3/08 ,  F02K9/46 ,  F02K9/62 ,  F02K9/80 ,  F03H1/0018 ,  F03H99/00 ,  F05D2240/40 ,  F05D2270/09 ,  F05D2270/62

摘要： A control system for controlling the operation of a plurality of micro thrusters arranged in a plurality of parallel horizontal rows and a plurality of parallel vertical columns, the control system requires a power source, a first plurality of power lines connected to the power source and coupled to at least one micro thruster of the plurality of micro thrusters in a horizontal row of the plurality of parallel horizontal rows, a second plurality of power lines connected to the power source and coupled to at least one micro thruster of the plurality of micro thrusters in a vertical column of the plurality of parallel vertical columns, and a control unit coupled to the power source to control activation of the first plurality of power lines and activation of the second plurality of power lines.

公开(公告)号：US20160333865A1

公开(公告)日：2016-11-17

申请号：US15093937

申请日：2016-04-08

申请人： Busek Co., Inc.

发明人： Nathaniel Demmons ,  Vladimir J. Hruby ,  Douglas Spence

IPC分类号： F03H1/00

CPC分类号： F03H1/0037 ,  B05B5/001 ,  B05B5/0255 ,  C09K3/30

摘要： An electrospray thruster and method includes an emitter, an extractor, and a propellant storage vessel. A porous propellant delivery pathway from the vessel to the emitter wicks liquid propellant to the emitter. An ionic liquid in the vessel has a chemical composition rending the ionic liquid solid at room temperature to prevent water absorption. In the liquid state, the ionic liquid exhibits favorable electrospray characteristics. A heater associated with the vessel is configured to heat the ionic liquid to above its melting point when thrust is required for delivery to the emitter via the porous propellant delivery pathway.

摘要翻译： 电喷雾推进器和方法包括发射器，提取器和推进剂储存容器。 从容器到发射器的多孔推进剂输送路径将液体推进剂吸入发射器。 容器中的离子液体具有在室温下使离子液体固体化学化学组成以防止吸水。 在液体状态下，离子液体表现出良好的电喷雾特性。 与容器相关联的加热器构造成当需要推动通过多孔推进剂输送路径输送到发射器时，将离子液体加热到其熔点以上。

公开(公告)号：US20160207640A1

公开(公告)日：2016-07-21

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 ,  B64G1/40

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.

摘要翻译： 一种用于卫星的电推进装置，其配备有至少四个主动推进器，在传送时施加平行推力，所述装置包括用于检测推进器故障的装置和用于重新定向推进器的装置，并且包括用于计算剩余推进器的重新定向角的装置 在推进器故障时起作用，该角度的值被计算以重新定向至少两个剩余的推进器，以便消除围绕卫星质心的总转矩。

公开(公告)号：US09297368B1

公开(公告)日：2016-03-29

申请号：US13713907

申请日：2012-12-13

申请人： The United States of America, as represented by the Administrator of the National Aeronautics and Space Administration

发明人： Michael J Patterson

IPC分类号： B64G1/40 ,  F03H1/00 ,  H01J27/02

CPC分类号： F03H1/0037 ,  B64G1/405 ,  F03H1/0043 ,  F03H1/0075 ,  H01J27/024

摘要： An electric propulsion machine includes an ion thruster having a discharge chamber housing a large surface area anode. The ion thruster includes flat annular ion optics with a small span to gap ratio. Optionally, at least a second thruster may be disposed radially offset from the ion thruster.

摘要翻译： 电动推进机包括具有容纳大表面积阳极的排出室的离子推进器。 离子推进器包括平坦的环形离子光学器件，其跨距与间隙比小。 可选地，至少第二推进器可以设置在离离子推进器的径向偏移处。