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公开(公告)号：WO2022159166A1
公开(公告)日：2022-07-28
申请号：PCT/US2021/060055
申请日：2021-11-19
发明人： LOZANO, Paulo, C. , WARDLE, Brian, L. , KREJCI, David , ZHOU, Yue
摘要： Polymeric electro spray emitters and related methods are generally described. In some embodiments, an emitter may be made from an ionic electro active polymer. The composition of the electro spray emitters described herein may enable the transport of ions and/or liquid ion sources, such as an ionic liquid or room temperature molten salt, through the bulk of the polymeric emitter. In some embodiments, the described emitters may be fabricated using a mixture of an ionic electroactive polymer, a solvent, and a liquid ion source to at least partially mitigate swelling effects of the polymer emitter that may otherwise occur when the one or more emitters are exposed to the liquid ion source during operation.
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公开(公告)号：WO2022086667A2
公开(公告)日：2022-04-28
申请号：PCT/US2021/051636
申请日：2021-09-23
发明人： PRIBANIC, Tomas A.
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.
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公开(公告)号：WO2022051513A1
公开(公告)日：2022-03-10
申请号：PCT/US2021/048889
申请日：2021-09-02
申请人： MOMENTUS INC.
发明人： KOKORICH, Mikhail
摘要： A spacecraft propulsion system comprises an attitude adjustment thruster system with multiple thrusters (488a-d) receiving heated propellant via a shared thermal capacitance block (275). The thermal capacitance block (275) receives energy from a solar concentrator (320) and stores the heat.
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公开(公告)号：WO2021233909A1
公开(公告)日：2021-11-25
申请号：PCT/EP2021/063128
申请日：2021-05-18
发明人： RTIMI, Youness , MESSINE, Frédéric
摘要： L'invention concerne un Circuit magnétique de création d'un champ magnétique dans un canal annulaire principal (1) d'ionisation et d'accélération de propulseur plasmique à effet Hall, présentant une extrémité supérieure ouverte d'émission d'ions et une extrémité inférieure fermée, comprenant : - des aimants externes comprenant un aimant (5) externe inférieur annulaire, et un aimant (6) externe supérieur annulaire disposé au-dessus de l'aimant (5) externe inférieur; - des aimants internes comprenant un aimant (7) interne inférieur, de forme cylindrique ayant une partie inférieure de diamètre inférieur au diamètre d'une partie supérieure, disposé en-dessous de l'aimant (6) externe supérieur, et un aimant (8) interne supérieur annulaire disposé au-dessus de l'aimant (7) interne inférieur; - les aimants externes (5, 6) ayant un même pôle (N, S) sur leur face supérieure respective et un même pôle opposé (S, N) sur leur face inférieure; - les aimants internes (7, 8) ayant une orientation de leurs pôles inverse de celle des aimants externes (5, 6); et - les aimants externes (5, 6) et les aimants internes (7, 8) étant disposés au-dessus de l'extrémité inférieure fermée du canal annulaire (1).
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公开(公告)号：WO2021081427A1
公开(公告)日：2021-04-29
申请号：PCT/US2020/057194
申请日：2020-10-23
摘要： Provided herein are various leptonic power sources, leptonic control systems, and leptonic-powered engines. In one example, an apparatus includes a housing having apertures through which material can enter and exit, and an anode coupled to the housing upstream from a cathode. A leptonic source emits beam electrons into the housing to ionize the material into a plasma according to a selectable ionization degree and deposit charge onto the cathode to establish an electric field in the plasma. A magnetic field source produces a magnetic field in the plasma at selectable angle to the flow of the plasma to at least partially entrain plasma electrons. Ions of the plasma are accelerated downstream in the housing by the electric field and impart momentum to a portion of the material to produce a thrust proportional to the selectable ionization degree of the plasma and a selectable intensity of the electric field.
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公开(公告)号：WO2021046044A1
公开(公告)日：2021-03-11
申请号：PCT/US2020/048924
申请日：2020-09-01
申请人： PHASE FOUR, INC.
发明人： TSAI, David , THOMPSON, Derek , SIDDIQUI, M. Umair
摘要： The invention provides an electrothermal RF plasma production system and thruster design, and associated components, that may use water vapor or other condensable propellants. The plasma production system and thruster design may be used in terrestrial and/or on-orbit applications.
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公开(公告)号：WO2020254425A1
公开(公告)日：2020-12-24
申请号：PCT/EP2020/066793
申请日：2020-06-17
申请人： THRUSTME
摘要： The invention concerns a radio-frequency plasma generating system comprising a radio-frequency generator (1) and a plasma source, the radio- frequency generator (1) being inductively or capacitively coupled to the plasma source through a resonant electric circuit (4), the radio-frequency generator (1) being adapted to receive direct current power from a direct current power supply (5) and for generating radio-frequency power at a frequency f, the radio-frequency power comprising a reactive radio-frequency power oscillating in the resonant electric circuit (4) and an active radio-frequency power absorbed by the plasma. According to the invention, the radio-frequency plasma generating system comprises means for measuring an efficiency of conversion E of direct- current power to active radio-frequency power absorbed by the plasma and means for adjusting the frequency f as a function of the measured efficiency of conversion E so as to maintain the efficiency of conversion E in a predetermined range within a RF plasma operational range.
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公开(公告)号：WO2020139188A1
公开(公告)日：2020-07-02
申请号：PCT/SE2019/051341
申请日：2019-12-23
申请人： HELMERSON, Ulf , BRENNING, Nils
发明人： HELMERSON, Ulf
摘要： An ion thruster (1, 1a) and a method for providing trust is disclosed. The ion thruster (1, 1a) comprises a first electrode (3, 3a), magnetic field generating device (2, 2a) providing a magnetic trap zone (MT) at the first electrode, and a second electrode (4). The ion thruster further comprises a power supply device (6) configured to provide a potential difference between the first electrode and the second electrode, and a plasma generating device (9, 12, 13) configured to create a plasma sufficient to ionise at least a portion of a propellant. The ion thruster further comprises a control device (10) configured to control the power supply device so that the first electrode is at a positive potential with respect to the second electrode. This increases the potential of a volume of the plasma adjacent to the target, which in turn accelerates ions in a direction away from the target. Thereby, thrust is provided. The disclosure further relates to a computer program and a computer readable medium, as well as a spacecraft comprising the ion thruster.
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公开(公告)号：WO2020049528A1
公开(公告)日：2020-03-12
申请号：PCT/IB2019/057548
申请日：2019-09-06
发明人： OQAB, Haroon B. , DIETRICH, George
摘要： An example engine for producing thrust includes: a fuel supply to supply a fuel; a chamber fluidly coupled to the fuel supply to receive the fuel; an induction heating assembly operatively coupled to the chamber to inductively energize the fuel in the chamber; and an exhaust nozzle coupled to the chamber to receive energized fuel from the chamber to produce thrust.
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公开(公告)号：WO2020049090A1
公开(公告)日：2020-03-12
申请号：PCT/EP2019/073679
申请日：2019-09-05
摘要： The present invention relates to a propulsion system for a spacecraft comprising at least one chemical propulsion engine, at least one electrical propulsion engine; and, a propellant feed system comprising: a propellant supply system including at least one tank to store a common propellant; wherein the propellant supply system is configured to deliver a controlled flow of the common propellant to both the chemical propulsion engine and the electrical propulsion engine. The present invention also relates to the use of a common propellant in a spacecraft and a method of providing a common propellant to an electrical and a chemical propulsion engine.
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