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WO/2017/146797A9 |
A thruster for a micro-satellite is disclosed. The thruster includes a cathode composed of a propellant material and an anode composed of ablative material. The thruster includes a housing having a proximate end and an opposite distal en...
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WO/2017/216802A1 |
A vacuum arc thruster device having a cathode rod disposed within a concentric insulator tube, and an anode electrode located at the distal edge of the insulator tube, separated from the cathode rod by the insulator tube. A controlled fe...
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WO/2017/160375A2 |
A thruster operable in a chemical mode or in an electrospray mode using the same liquid monopropellant for operation in both modes is described having a multiplicity of a microthrusters made of a catalytic material having a bore therethr...
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WO/2017/151029A1 |
The present invention provides a system of using compressed air as force source, comprising: compressed air jet engines, which use high/ultra-high pressure compressed air as a jet working medium, a compressed air production/supply device...
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WO/2017/134432A1 |
A propulsion device (1) for use in an aerospace or other vehicle (2) comprising: a first laser beam (11); a second laser beam (12); and a field material (13) which is a source of a first electric field, wherein the first laser beam (11) ...
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WO/2017/119501A1 |
The plasma acceleration device comprises: a cathode (11) supplying electrons to a plasma acceleration region; an anode (12); a power source (13) applying a voltage between the cathode and the anode; a supply port (14) disposed more towar...
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WO/2017/116257A1 |
A hydrodynamic device presented in different variants, having in common an unsupported force which is generated by means of a flow pressing on the walls of a device. Specifically, changing the design of a regular hydrodynamic transmissio...
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WO/2017/115023A1 |
The system (1) for generating a plasma beam comprises at least one device (3) for generating a magnetic barrier consisting of a first magnetic pole (5) and a second magnetic pole (6), at least one extraction and acceleration grid (4) and...
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WO/2017/093906A1 |
Propulsion apparatus (10) for space vehicles, comprising a solid state oxygen-rich source layer (11), means (12) for extracting oxygen from said solid state oxygen-rich source layer (11), means (16, 14, 17) for accelerating corresponding...
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WO/2017/089699A1 |
The present invention relates to a method for ionising argon, as well as, in particular, to a propulsion method and a surface treatment method implementing the method of the invention. The present invention also relates to a device for i...
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WO/2017/085746A1 |
The present invention relates to a Microwave Electrothermal Thruster(MET) adapted for in-space electrothermal propulsion comprising a tunable frequency Microwave Electrothermal Thruster propulsion module enabling primary propulsion and a...
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WO/2017/071739A1 |
The invention relates to a plasma accelerator that produces and controls a plasma stream exhaust, in particular for space propulsion. The ions are produced inside the discharge chamber by working gas collisional ionization by electrons f...
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WO/2017/072434A1 |
The invention concerns a device for producing an amorphous carbon layer by electron cyclotron resonance plasma, the device comprising: - a plasma chamber (3); - means for conveying a gas (4), - a magnetic mirror (15), - a waveguide (5) e...
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WO/2017/069728A1 |
A propulsion system includes at least one group of electric thrusters that are spatially distributed in a multi-axis system. A controller is in communication with each of the electric thrusters. The controller is configured to differenti...
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WO/2017/046115A1 |
The invention aims to produce a consumption of several kilograms of cathode, or even more, as part of a vacuum arc propulsion (VAT). To do this, the invention drives the cathode in a helical movement optimised so as to allow the consumpt...
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WO/2017/045020A1 |
Disclosed herein is a propulsion system comprising: a solid conductive or semiconductive cathode (130); an anode (110) having a potential difference relative to said cathode (130), said potential difference creating an electric field bet...
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WO/2017/037062A1 |
The invention relates to an ion thruster (100), comprising: a chamber (10); a reservoir (20), comprising a solid propellent (PS), housed in the chamber (10) and including a conductive jacket (21) equipped with an orifice (22); means (30,...
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WO/2017/023383A1 |
In one aspect and one example, a liquid fueled pulsed plasma thruster includes an ionic liquid propellant and electrodes disposed to at least partially cause electrolytic decomposition of the ionic liquid propellant. The ionic liquid pro...
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WO/2017/006056A1 |
The invention relates to a Hall-effect thruster (10), configured to be arranged inside or outside a spacecraft. The thruster has a concentrator (36) for collecting particles (P). The shape of this concentrator is defined by a continuous ...
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WO/2017/003318A1 |
The invention relates to mechanical engineering. The rotary engine comprises a casing, in a groove of which a bladed rotor is mounted on a shaft, wherein the above-mentioned casing has at least one input opening formed along a tangent to...
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WO/2016/180955A2 |
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 ...
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WO/2016/181360A1 |
The invention relates to a vacuum arc thruster (10). The vacuum arc thruster (10) includes an anode arrangement (12), a cathode (14), an insulator (16) which is located between the anode arrangement (12) and the cathode (14), and a contr...
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WO/2016/178701A1 |
Methods and apparatuses for augmenting thrusts using ionized gases. A gas is partially ionized, which then ionizes a second, neutral gas. A magnetic field creates a Townsend cascade in the ionized gases, greatly increasing the amount of ...
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WO/2016/162676A1 |
A superconducting microwave radiation thruster used to accelerate a spacecraft or an airborne vehicle. The thruster includes a flat superconducting surface for the major end plate and a specially shaped, non-superconducting minor end pla...
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WO/2016/164004A1 |
Methods and apparatus of adding propellant to a thruster assembly are described. A first end of a beaker is disposed in an opening of the tank, where the beaker contains propellant and the first end of the beaker includes a breakaway bot...
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WO/2016/151609A1 |
Described is an air plasma propulsion system comprising: a plant (100) with an air turbine (A) designed to receive a supply of air (A) from an outside environment, and a plasma propulsion unit (200) designed to increase a speed of the ai...
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WO/2016/151251A1 |
The invention relates to the field of regulation of fluid flow rates, and in particular to a flow-rate-regulating device (109) comprising: an upstream chamber (206); a downstream chamber (207); a plurality of electrically conductive capi...
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WO/2016/147032A1 |
Abstract: An ultra-high rpm rotatory turbine system for propulsion in the vacuum of space. The system attains ultra high angular velocities and uses sparse gas molecules, electrons, photons as well as radiation as ejectory material to pr...
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WO/2016/149082A1 |
A Hall thruster includes an annular discharge channel, a cathode, an exclusive outer magnetic core disposed asymmetric to the annular discharge channel, and an outer magnetic pole between the cathode and the annular discharge channel. Th...
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WO/2016/138068A1 |
According to some embodiments, a system for widening and densifying a scrape-off layer (SOL) in a field reversed configuration (FRC) fusion reactor is disclosed. The system includes a gas box at one end of the reactor including a gas inl...
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WO/2016/131111A1 |
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 elec...
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WO/2016/120570A1 |
The invention relates to a Hall effect thruster (10) arranged inside a wall (22) and comprising a magnetic circuit (30) and an electrical circuit (60) including an anode (62), a first cathode (64), and an electrical voltage source (68). ...
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WO/2016/060271A9 |
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WO/2016/016563A1 |
The invention relates to the field of spacecraft propulsion, and more specifically to electrically powered spacecraft propulsion. A spacecraft propulsion system (100) according to the invention includes at least one electrostatic thruste...
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WO/2016/004044A1 |
Thrusting systems and vehicles are disclosed. One thrusting system includes a signal generator (104) and a waveguide (102). The signal generator is configured to generate an electromagnetic wave. The waveguide is coupled to the signal ge...
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WO/2015/177942A1 |
Electrodeless plasma is supplied to a space (S) between a cathode (22) and an anode (23) to lower the electrical resistivity in the space, and the electrodeless plasma is accelerated by Lorentz force induced by an axial magnetic field co...
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WO/2015/177938A1 |
A plasma supplied from a supply path (1) is caused to accelerate due to a Hall electric field (E) produced by an interaction between electrons (e-) released from a cathode (3), a radial magnetic field (Bd), and an electric field (Ex).
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WO/2015/177438A1 |
An engine (10) for a spacecraft comprising a chemical thruster comprising a nozzle (30) for ejecting combustion gas, and a Hall-effect thruster. The engine is arranged such that the nozzle acts as an ejection channel for particles ejecte...
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WO/2015/176170A1 |
An implosion reactor tube is provided, including: a receptacle body having a tube shape open at a first end; a cylinder positioned within the receptacle body; a mixing chamber at a second end of the receptacle body; the mixing chamber de...
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WO/2015/174366A1 |
Provided is a vapor jet system that is capable of continuously jetting vapor for a long duration of time while suppressing the occurrence of cavitation. By using a vapor jet system that is equipped with liquid storage parts for separatel...
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WO/2015/166787A1 |
Provided is a plasma generation device equipped with a measuring device and capable of stably and appropriately controlling the state of plasma, and also provided is a plasma propeller using the plasma generation device. A plasma generat...
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WO/2015/159944A1 |
A vapor jet system which includes: a container which accommodates a sublimable solid and is equipped with a vapor discharge port for discharging vapor generated by sublimation of the sublimable solid; a member which is equipped with an o...
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WO/2015/159208A1 |
The invention relates to a device (100) for forming a quasi-neutral ion-electron beam, comprising: a chamber (20); a set of means (31, 30, 40, 58) for forming an ion-electron plasma in the chamber (20); a means (50) for extracting and ac...
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WO/2015/155004A1 |
The invention relates to an ion drive for a spacecraft, in particular for a satellite, comprising a reservoir with fuel; an ionization chamber connected to the reservoir; a generator for producing an electrostatic, magnetostatic and/or e...
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WO/2015/132534A1 |
The invention relates to a Hall-effect plasma thruster (10) comprising: - an annular discharge channel (121) around a principal axis (A) with an open downstream end, having an ionisation zone (128) between an internal wall (116) and an e...
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WO/2015/105431A1 |
A hydrodynamic device is presented in various variants having in common the production of reactionless force by means of a flow pressing against the walls of the device. In particular, changing the design of a regular hydrodynamic transm...
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WO/2015/086982A1 |
A system for regulating the flow of a propellant fluid for an electric thruster of a space vehicle, comprising a propellant fluid reservoir and a flow regulator mounted at the outlet of said reservoir, the flow regulator comprising a hea...
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WO/2015/082739A1 |
The invention relates to a system, without moving parts or electrodes, for obtaining thrust vectoring capability in space plasma thrusters with a substantially axial magnetic field or without an applied magnetic field, as well as to the ...
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WO/2015/065518A1 |
System (300, 400) and methods (500) for testing a reaction thruster (100) in a vacuum environment. The methods comprise: disposing the reaction thruster in a vacuum chamber which is at least partially connected to earth ground; removing ...
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WO/2015/057105A2 |
The invention relates to the field of aerospace engineering, and more particularly to engine design, and concerns methods for generating thrust in engines. It is proposed that from 2 to 100, preferably from 5 to 10, heating chambers with...
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