Login| Sign Up| Help| Contact|

Patent Searching and Data


Matches 1 - 50 out of 1,271

Document Document Title
WO/2019/048497A1
The present invention relates to an ion beam generator (10), including an emission electrode (12), an extraction electrode (14), and an electricity generator (16). The emission electrode comprises a substrate (20) and a plurality of nano...  
WO/2019/025174A1
The invention relates to a field emission propulsion system (1) for spacecraft, comprising: a control unit (4); a propulsion assembly (2) with a plurality of field emission propulsion units (23) that comprise an ion source with a plurali...  
WO/2019/020330A1
An electric thruster comprises a propellant delivery system, wherein the propellant delivery system comprises: a pipe for carrying propellant; a valve which is adapted to adjust a volume or mass flow of the propellant in the pipe; and an...  
WO/2019/021234A1
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...  
WO/2019/005242A1
According to certain aspects, an electric-propulsion thruster is used as part of a base or platform which also includes a power converter, having a plurality of inductors and other electrical components, and a printed circuit board (PCB)...  
WO/2018/210929A1
Device (52) for regulating the rate of flow of propellant fluid for an electric thruster, of the thermo-capillary device type comprising at least one capillary duct that is electrically conductive and capable of regulating the rate of fl...  
WO/2018/196888A1
The invention relates to an electromagnetic toroidal impeller in the field of physics applied to electromagnetism. The invention comprises a cylindrical arrangement of superconducting antennas (9) which are separated by a dielectric (8) ...  
WO/2018/182475A1
The present invention provides a compressed air artificial wind system including compressed air storage device, compressed air discharge device, artificial wind system base and controller; also a firefighting equipment including an extin...  
WO/2018/147925A1
A satellite system operates at altitudes between 100 and 350 km relying on vehicles including a self-sustaining ion engine to counteract atmospheric drag to maintain near-constant orbit dynamics. The system operates at altitudes that are...  
WO/2018/144348A1
A miniature Hall current plasma source apparatus having magnetic shielding of the walls from ionized plasma, an integrated discharge channel and gas distributor, an instant-start hollow cathode mounted internally to or on the surface of ...  
WO/2018/138458A1
The invention relates to a system for generating a plasma jet of metal ions. This system comprises: a tube (10) made of electrically insulating material containing a metal (20) that is solid at room temperature; an anode (30) making cont...  
WO/2018/112184A1
An ion beam generator includes a discharge chamber with a backplate and tubular sidewalk A source of propellant, for example, Xenon gas is provided to the discharge chamber. First and second annular magnets are disposed on or near the ba...  
WO/2018/108905A1
The invention relates to a method and to a device for position control of a spacecraft (1). In the method, a force is exerted on the spacecraft (1) by emitting at least one directed beam (7) of electromagnetic radiation having sufficient...  
WO/2018/096236A1
Device and method for regulating a flow rate of gas intended to supply a propulsion apparatus for a spacecraft comprising xenon tank (2), a circuit comprising a withdrawing pipe (3) having an upstream end connected to the tank (2) and a ...  
WO/2018/095505A1
The invention relates to the ways of propulsion of a space or aerial vehicle. Disclosed are the basic design of the gravity propulsion device based on the gravity induction principle and six its subdesigns. The basic design realizes a ra...  
WO/2018/094504A1
A system and a method for laser-driven propulsion, comprising transferring momentum to a projectile through a low-density material at laser fluences below plasma ablation threshold, the method comprising providing a metal layer having a ...  
WO/2018/091962A4
This invention is an improvement and completion of my granted USPTO patent (US 8272283 B2) to enhance fuel efficiency by utilizing a number of reaction engines running along a looped track which the said looped track is comprised of two ...  
WO/2018/091962A3
This invention is an improvement and completion of my granted USPTO patent (US 8272283 B2) to enhance fuel efficiency by utilizing a number of reaction engines running along a looped track which the said looped track is comprised of two ...  
WO/2018/069642A1
The invention relates to an ion thruster that can be used to generate and confine a plasma discharge in an external confinement area created by an external magnetic field B .  
WO/2018/055612A1
A propulsion system attached to a space vehicle for propelling the space vehicle in an essentially gravity free environment, comprises: a) a first section of tubing; b) a second section of tubing having a cross-sectional area significant...  
WO/2018/048501A9
An arcjet thruster system for a spacecraft is provided. The arcjet thruster system may include a power supply that includes a radio-frequency start power supply and a continuous direct-current power supply, each selectively coupled to el...  
WO/2018/048501A1
An arcjet thruster system for a spacecraft is provided. The arcjet thruster system may include a power supply that includes a radio-frequency start power supply and a continuous direct-current power supply, each selectively coupled to el...  
WO/2018/031934A1
A method and means to produce a force for propulsion comprises a source of free electrons and a means to produce pseudoelectrons; whereas, a gravitating body such as the Earth provides a repulsive fifth force on the pseudoelectrons. Pseu...  
WO/2018/026786A1
Various examples related to a deployable gridded ion thruster are described. A deployable gridded ion thruster can include: a thruster body including an ion generating unit; and an expandable discharge chamber configured to expand from a...  
WO/2018/007545A1
The invention relates to an electric power supply system (1) for a Hall effect electric thruster, said Hall effect electric thruster comprising an anode (50), a cathode (51), a heating device (53) for the cathode and an igniter (52). The...  
WO/2018/007542A1
The invention relates to a process for controlling a Hall effect electric thruster (1), said Hall effect electric thruster comprising a discharge channel (2), an anode (40), a cathode (50), a system (10) for injecting propulsion gas into...  
WO/2018/005707A1
Functional components of spacecraft structures can be subject to detrimental impacts by energetic particles produced from an electric propulsion system. A graphene coating applied to a functional component can maintain electrical conduct...  
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...  
WO/2017/160375A3
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...  
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...  
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...  
WO/2017/146797A1
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...  
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...  
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) ...  
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...  
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...  
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...  
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...  
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...  
WO/2017/085746A4
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...  
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...  
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...  
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...  
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...  
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...  
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...  
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,...  
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...  
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 ...  
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...  

Matches 1 - 50 out of 1,271