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WO/2024/077710A1 |
The present invention provides an iodine storage tank and electric propulsion. The iodine storage tank comprises a storage tank upper cover assembly, a storage tank lower shell assembly, and a solid iodine working medium. The storage tan...
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WO/2024/062202A1 |
A method of testing a gridded-ion thruster (2) is performed on board a spacecraft (100) while the spacecraft is in thrust in extraterrestrial space. The test method is a perveance-type test which makes it possible to update a thrust oper...
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WO/2024/023409A1 |
The invention relates to a power supply assembly (1) for a plasma thruster (2) of a spacecraft (100) for controlling a keeper current (Ikeeper) supplied to a keeper electrode (22) of the plasma thruster. The power supply assembly takes i...
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WO/2024/003483A1 |
The invention relates to improving the propulsion of a HET, RIT or GIT engine during solar eclipses and comprises, before the solar eclipse: deactivating the thrust and then disconnecting the bus supplied with power by the solar panel (T...
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WO/2023/244208A1 |
A microwave plasma thrust system (MTPS) is provided with a heavy expanding gas mixture of carbon dioxide and GED as the microwave absorbing gas mixture. The thrust system is used to generate kinetic energy to propel objects such as space...
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WO/2023/244857A1 |
A thruster includes a mass source, an ejection outlet, and a channel forming an ejection path from the mass source to the ejection outlet. Multiple annular current paths form loops such that current flow along the loops is transverse to ...
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WO/2023/244860A1 |
An electrospray thruster includes an emitter including an array of tips, each tip of the array of tips being configured to emit ionic liquid, and an extractor electrode spaced from the emitter and comprising a conductive film, the conduc...
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WO/2023/222155A1 |
The invention relates to a microwave-cyclotron-resonance plasma thruster comprising a permanent-magnet stack, a coaxial electrode array, an anode and a cathode, wherein: the permanent-magnet stack comprises at least one permanent magnet,...
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WO/2023/222626A1 |
The present invention provides a simple and reliable way of producing ions. According to the invention, the ions produced can be mixed and/or neutralized simply and without a large number of additional parts and apparatuses. The device (...
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WO/2023/217449A1 |
The present invention relates to an ion source (1), in particular an ion thruster for propelling a spacecraft, comprising a reservoir (2) for a propellant (3) that has a solid state and can be liquefied into a liquid state, a heater (4) ...
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WO/2023/215664A1 |
Described herein is a power processing unit (PPU) for use with a Hall Effect Thruster (HET) and a Propellant Management Assembly (PMA) of a spacecraft. The PPU comprises an anode and ignitor supply subsystem that provides anode and ignit...
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WO/2023/152005A2 |
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WO/2023/130168A1 |
The present invention relates to a novel form of air, land, underwater or space propulsion, achieved through the use of appropriate electromagnetic interactions. By using a toroidal coil (1) with an internal magnetic core (2), forces can...
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WO/2023/131826A1 |
Photon drive and photon turbine When light reflects from a mirror it transfers sometimes more and sometimes less momentum to the mirror when mirror has dielectric in front compared to mirror in vacuum. Bouncing focused light between two ...
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WO/2023/130166A1 |
The present invention relates to a novel form of air, land, subsea or space propulsion, achieved through the use of appropriate electromagnetic interactions. Through the use of coils (1) with an inner core (2) and a support part (3) that...
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WO/2023/127028A1 |
This propulsion device comprises a first conducting wire and a second conducting wire that are spaced apart and fixed, and a power source that outputs alternating current. The propulsion device is configured such that the alternating cur...
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WO/2023/126201A1 |
The invention relates to a propulsion system (100) for a spacecraft. The system comprises an electrical propulsion engine (101) comprising an anode (103) and a cathode (104), a chemical propulsion engine (102), a pressurant gas system co...
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WO/2023/122673A1 |
The present disclosure relates to a system and method that produces thrust without a propellant or any physically moving parts. The disclosed method produces thrust by accelerating electrons between a multilayer capacitive stack and taki...
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WO/2023/112039A1 |
Methods and systems are providing for generating relativistic motion of one or more nano particles. The methods include imposing a wave packet on the one or more nano particles by an electromagnetic field, the electromagnetic field inclu...
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WO/2023/111482A1 |
The present invention relates to the use of depleted uranium hexafluoride UF6 as propellant in an electric thruster.
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WO/2023/091492A1 |
A satellite having a cooling system to remove heat from an electric rocket engine using a working fluid. The cooling system can include a pump that circulates working fluid along a cooling loop between the rocket engine and a radiator. T...
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WO/2023/091123A1 |
A novel gas propulsion device comprises one or more high-frequency linear actuators (such as a voice coil linear actuator or a piezoelectric linear actuator) attached to one or more gas propulsion elements having a concave internal surfa...
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WO/2023/079341A1 |
This invention discloses an ultra-strong propulsion system, operating by the implementation of magnetic pressure of a rectangular-shape coil on its wires and support. In the normal cases, the pressure on the wires of electromagnetic coil...
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WO/2023/073431A1 |
A vehicle for obtains linear momentum without throwing the mass from the vehicle in the space, comprising of a power source 13; a rigid base 1; a motor 3A and a motor 3B fitted in the rigid base1; a shaft 4A for the motor 3A, and a shaft...
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WO/2023/057934A1 |
Methods and systems for electric propulsion are provided. An example method includes providing a magnetic shield using an accelerating channel made of a soft magnetic material; generating, by a magnetic system, a radial magnetic field in...
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WO/2023/059413A1 |
Electroaerodynamic devices and their methods of operation are disclosed. In one embodiment, ions are formed by dielectric barrier discharge using a time-varying voltage differential applied between a first electrode and a second electrod...
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WO/2023/053207A1 |
A spacecraft-borne propulsion device (1000) is characterized by a configurational form which is provided with: a propellant storing mechanism provided with a propellant storage container (10) for storing propellant in a vapor-liquid equi...
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WO/2023/056046A1 |
Exemplary air breathing plasma jet engine and method of operation that can be used in electrically powered aircraft and spacecraft as a hybrid between a turbo jet engine and a ramjet or supersonic sonic ramjet (SCRAMJET) engine. The air ...
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WO/2023/038611A1 |
The invention relates to space technology and can be used in electric jet engines, as well as in vacuum-plasma apparatus. Proposed is a stationary ion/plasma engine comprising a magnetically conductive housing having mounted therein a di...
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WO/2023/037138A1 |
An electrodeless plasma thruster with close ring-shaped gas discharge chamber (1,10) can include a gas discharge chamber (1,10) close ring shaped in fluid communication with a propellant storage system (10,70). An antenna (3,30) can be p...
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WO/2023/028623A2 |
A vacuum arc thruster (VAT) and method of feeding a VAT is disclosed. The VAT comprises an anode, a cathode and a feeding mechanism including an actuator in data communication with a computing unit. The actuator is configured to move the...
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WO/2023/025846A1 |
The present invention relates to a power conversion system for electrically-powered thrusters located on and/or inside a satellite.
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WO/2023/027679A1 |
Proposed is a stationary ion/plasma engine comprising: a discharge chamber having an annular ionization and acceleration channel and a bottom with an inner seating surface for an anode, said chamber being made of an electrically insulati...
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WO/2023/012834A1 |
Plasma propulsion engine works like an ion source to create ion beam and extract from engine. Invention works at the air with atmosphere pressure by 5 step. System can produce power between 27-51 horsepower with zero pollution. Engine ju...
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WO/2023/275579A1 |
A first aspect of the present invention is related to a method for manufacturing an emitter for electrospray generators. The method comprising the steps of providing a substrate, presenting a plate and at least one protrusion, and then n...
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WO/2022/264177A1 |
Electromagnetic propulsion system for spacecraft movement without the emission of reaction mass, characterised in that it comprises two arms (10) which share one of their vertices at a point called feedpoint (14); said feedpoint (14) bei...
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WO/2022/243543A1 |
A thermal management system (5) for a magnetoplasmadynamic thruster (10) for a space craft is disclosed. The thermal management system (5) is located between at least one superconducting magnet (120) and a plasma discharge unit (15 and c...
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WO/2019/021234A9 |
A space propulsion system (1), having reduced sizes, is designed specifically for the application on miniaturised satellites, but it can be scaled easily based upon a wide range of sizes of the target vehicle, and it comprises: a combust...
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WO/2022/240706A1 |
A plasma engine includes a plasma source that generates ions from molecular gas species received at a gas input where at least some of the ions generated are atomic species ions. An ion extractor is configured to extract ions from the pl...
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WO/2022/208507A1 |
The invention of fuelless space propulsion systems will be a new revolution in the field of space explorations. The system is an electric engine that can propel itself in space using solar energy and without using any fuel that dissipate...
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WO/2022/125264A9 |
A method includes producing an electric propulsion (EP) rocket engine. The method selects a core discharge chamber. A discharge cathode assembly (DCA) is selected along with a DCA common interface (CI). The DCA CI is connected to the cor...
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WO/2022/201050A1 |
A photonic motor is disclosed that comprises: - at least one optical radiation input; - a first arrangement of optical waveguides, comprising at least one first optical resonator lying in a first region of space to form a static part of ...
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WO/2022/189964A1 |
There is disclosed a vehicle (100) and a method for propelling the vehicle comprising a propulsion arrangement (102). The propulsion arrangement (102) includes a chamber arrangement (104) that is configured to store antimatter therein by...
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WO/2022/183920A1 |
An electromagnetic fluid vortex power device, comprising a main air inlet channel (1), an auxiliary air inlet channel (4) and vortex holes (5). The auxiliary air inlet channel is distributed on the two sides of the main air inlet channel...
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WO/2022/159166A1 |
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...
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WO/2022/142776A1 |
A magnetic pole structure for a Hall thruster. The magnetic pole structure comprises wide-envelope type outer magnetic pole components (1), a magnetic bridge (2), a pagoda-shaped inner magnetic pole component (3), an upper plate (4) and ...
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WO/2022/139942A1 |
Bi-modal propulsion systems and related methods are generally described. In some embodiments, a bi-modal propulsion system may employ a single propellant for both chemical thruster(s), operating at elevated pressures, and electrical thru...
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WO/2022/120499A1 |
An apparatus for ionizing and accelerating a fluid comprises at least a pair of spaced-apart electrodes arranged coaxially and each comprising a planar, electrically conductive body locating a plurality of apertures arranged to substanti...
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WO/2022/104408A1 |
A plasma reactor is provided together with a method for generating kinetic energy to propel a craft. The reactor includes an inlet for plasma; a reactor core having an interior chamber and an exterior chamber, the interior chamber being ...
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WO/2022/096506A1 |
A propulsion unit (10) for a spacecraft is described. The propulsion unit (10) comprises a centrally arranged cathode (20), a concentric anode (30), an injection point (60) for injecting a propellant (50) between the central cathode (20)...
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