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Patent Searching and Data


Matches 1 - 50 out of 1,287

Document Document Title
WO/2019/136535A1
The present device for redirecting and lending momentum to streams of a fluid under pressure is positioned at the outlet of an external power device that generates propulsive thrust, such as a pump, a turbine, a propeller, or functional ...  
WO/2019/125405A1
A Hall thruster includes an annular discharge region and an annular cathode concentric to the annular discharge region.  
WO/2019/113617A1
The present invention relates to an ion thruster (1) for propulsion of spacecrafts, comprising: a reservoir (2) for a propellant (3), an emitter (4) for emitting ions (3+) of the propellant (3), the emitter (4) having one or more project...  
WO/2019/116361A1
A heaterless hollow cathode provides electron emission current in an electric space propulsion system. A mechanical, thermal, and electromagnetic design of the cathode apparatus is presented, and a method of operation for rapid ignition ...  
WO/2019/116371A1
Disclosed is a closed drift, narrow channel Hall thruster configured to operate at powers < 30 W. The thruster includes a thruster body and a neutralizing cathode. The thruster body includes a magnetic circuit including a magnetic source...  
WO/2019/113223A1
A low-power Hall thruster gains significantly improved efficiency by a combination of features, including a single piece, h-shaped magnetic screen which enables a more efficient internal volume utilization as well as optimal magnetic shi...  
WO/2019/078752A1
Proposed is a hydrodynamic perpetual motion machine which generates a non-support force as a liquid or gas moves in a cavity or channel thereof, wherein a special device is installed, the design of which depends on the purpose of said hy...  
WO/2019/075051A1
A thruster has a first stage and a second stage. The first stage is a plasma source that outputs a plasma. The second stage is an accelerator. In one embodiment, the second stage is a plasma accelerator that accelerates the plasma. In an...  
WO/2019/025174A8
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/2019/074785A1
The invention provides an electrothermal RF plasma production system and thruster design, and associated components, that may be used in terrestrial applications and/or miniaturized to the mass, volume, and power budget of Cube Satellite...  
WO/2019/067451A1
This disclosure is generally directed to controlling energy distribution to a load, especially when anomalous events are detected. Benefits of the present disclosure include minimizing the length of a discharge event, mitigating the effe...  
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...  

Matches 1 - 50 out of 1,287