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Matches 151 - 200 out of 1,303

Document Document Title
WO/2011/088335A1
An electric propulsion machine includes an ion thruster having an annular discharge chamber housing an anode having a large surface area. The ion thruster includes flat annular ion optics with a small span to gap ratio. Optionally, a sec...  
WO/2011/055403A1
An electromagnetic device for accelerating electrically neutral molecules of a substance is characterized by the fact of comprising: - a Treating Tube (14) in non-conducting material, into which the substance to be treated is introduced;...  
WO/2011/041882A1
A centrifugal engine features a round enclosure centered on an axis and having an outer wall closing the interior around the axis between a base and a cover. An inner surface of the outer wall slopes outwardly away from the axis where th...  
WO/2011/037597A1
An annular combustion (22) chamber and a transient plasma system (42) in communication with the annular combustion chamber (22) to sustain a spinning detonation wave. This system (42) is also called as "nanosecond pulsed plasma" system a...  
WO/2011/033238A1
The invention relates to a Hall-effect plasma thruster including: an annular discharge channel around a main axis, having an open downstream end defined between an inner wall and an outer wall; at least one cathode; a magnetic circuit fo...  
WO/2011/035167A1
Disclosed is a novel compound used as a fuel for thermonuclear fusion reactions for power generation applications. The compound is 11Boron Deuteride, which is an analogue of Boron Hydride. Also disclosed is a method of production of this...  
WO/2011/008126A3
The invention relates to engines that generate a support point from gravitational fields and is intended to produce a silent, invisible, environmentally neutral reactive thrust irrespective of the mode of transport and medium of travel.  
WO/2010/033994A3
According to the present invention, a blade with lift-to-drag ratio greater than one can generate a lift force greater than the drag force on the blade when a fluid flows across the blade. The blade can be positioned within an enclosed e...  
WO/2011/008126A2
The invention relates to engines that generate a support point from gravitational fields and is intended to produce a silent, invisible, environmentally neutral reactive thrust irrespective of the mode of transport and medium of travel.  
WO/2010/133802A1
The invention relates to a Hall effect plasma thruster including a main annular ionization and acceleration channel (120) having an open downstream end (129), at least one cathode, an annular anode that is concentric with the main annula...  
WO/2010/072995A3
An electric propulsion system comprising a plasma chamber having first and second apertures for producing ion beams. Respective first and second coils are arranged about the chamber to produce an electromagnetic field in regions adjacent...  
WO/2010/036291A4
A satellite propulsion system has both a chemical monopropellant thruster providing high thrust for rapid maneuvering and an electrospray thruster providing high specific impulse. Both thrusters operate off of a single ionic liquid prope...  
WO/2009/137583A3
An ionic liquid ion source can include a microfabricated body including a base and a tip. The microfabricated body can be formed of a porous metal compatible (e.g., does not react or result in electrochemical decaying or corrosion) with ...  
WO/2010/081465A2
The invention relates to a molding compound-enclosed power semiconductor element, wherein a power semiconductor is surrounded with metal contacts guided to the outside of a molded module in enveloping syringes by being encased with therm...  
WO/2010/055541A4
An electromagnetic device for accelerating electrically neutral molecules of a substance is characterized by the fact of comprising: a Treating Tube (14) in non-conducting material, into which the substance to treat is introduced; static...  
WO/2010/072995A2
An electric propulsion system comprising a plasma chamber having first and second apertures for producing ion beams. Respective first and second coils are arranged about the chamber to produce an electromagnetic field in regions adjacent...  
WO/2010/060887A1
The invention relates to a plasma thruster involving the extraction of a stream of positive ions, characterized in that it comprises: - a single ionisation stage; - means of injecting ionisable gas for said ionisation stage, said means c...  
WO/2010/057463A1
The invention relates to an ion drive (1) for a spacecraft, comprising a high frequency generator (4) for generating an alternating electromagnetic field for the ionization of a propellant and an acceleration system (7) for the charge ca...  
WO/2010/036291A3
A satellite propulsion system has both a chemical monopropellant thruster providing high thrust for rapid maneuvering and an electrospray thruster providing high specific impulse. Both thrusters operate off of a single ionic liquid prope...  
WO/2010/055541A1
An electromagnetic device for accelerating electrically neutral molecules of a substance is characterized by the fact of comprising: a Treating Tube (14) in non-conducting material, into which the substance to treat is introduced; static...  
WO/2010/055540A1
A static electromagnetic device for accelerating electrically neutral molecules utilizing their dipolar electric moment is characterized by the fact of comprising comprise: a treating tube in non-conducting material, internally empty or ...  
WO/2010/011706A3
A nano-particle field extraction system comprising a grid having a plurality of electrodes each defining an electrical field, wherein the grid has a plurality of vias extending therethrough. The system further comprises a reservoir havin...  
WO/2010/011706A2
A nano-particle field extraction system comprising a grid having a plurality of electrodes each defining an electrical field, wherein the grid has a plurality of vias extending therethrough. The system further comprises a reservoir havin...  
WO/2010/001422A1
The emitter for ion propulsion comprises: - two mutually coupled semi-emitters (3, 5), made of optical material, each of which presents a respective sharpened end; the two ends (3D, 5D) form a tip in correspondence of which there is a re...  
WO/2009/150312A1
The invention relates to an electric thruster for a spacecraft. According to the invention, the thruster (II) comprises a jet generating portion (G1) and a jet accelerating portion (A2), pivotably connected (H1) such that the jet acceler...  
WO/2009/037203A3
The invention relates to an ion accelerator arrangement comprising an ionization chamber which is surrounded by a chamber wall and a magnetic arrangement that is disposed outside the chamber wall. Steps are taken to dissipate lost heat o...  
WO/2009/135471A1
The invention relates to a plasma generator comprising a housing (20) that surrounds an ionisation chamber (5); at least one working fluid supply line (30) leading into the ionisation chamber (5), said ionisation chamber (5) comprising a...  
WO/2009/137583A2
An ionic liquid ion source can include a microfabricated body including a base and a tip. The microfabricated body can be formed of a porous metal compatible (e.g., does not react or result in electrochemical decaying or corrosion) with ...  
WO/2009/131754A1
Described herein are improved ion thruster components and ion thrusters made from such components. Further described are methods of making and using the improved ion thruster components and ion thrusters made therefrom. An improved catho...  
WO/2006/011978A3
A propulsion device contains a working mass within an enclosed plenum, where the working mass is circulated through the plenum to produce a net force vector. The working mass is accelerated around a first bend or change in direction with...  
WO/2009/102227A2
The invention refers to raise theoretical some complex movements which generated well determined direction and sense accelerations, resulting an acceleration direction principle, and on the base of the principle it describes an accelerat...  
WO/2009/037197A3
The invention relates to a surface section that is exposed to an ion flow, in particular for a drive arrangement in a spacecraft, comprising an electrostatic ion accelerator arrangement. According to the invention, in order to reduce ero...  
WO/2007/035124A8
The invention relates to a plasma vehicle engine based on two high frequency ion sources which are arranged on a rotor in the form of a Segner wheel and are placed in a cage for removing waste gases. The inventive engine exhibits a high-...  
WO/2009/037196A1
The invention relates to a drive arrangement in a spacecraft, comprising several drive units (TW1,TW2,TW3), several individually controllable drive units that can be continuously applied to a common, constant voltage potential (HV), and ...  
WO/2009/037197A2
The invention relates to a surface section that is exposed to an ion flow, in particular for a drive arrangement in a spacecraft, comprising an electrostatic ion accelerator arrangement. According to the invention, in order to reduce ero...  
WO/2009/037203A2
The invention relates to an ion accelerator arrangement comprising an ionization chamber which is surrounded by a chamber wall and a magnetic arrangement that is disposed outside the chamber wall. Steps are taken to dissipate lost heat o...  
WO/2005/044664A3
The invention concerns a carrier (1) for transporting a payload into an orbit, whereby the carrier, during or after the release of the payload, is located in a transfer orbit or in the orbit of the payload. The carrier (1) comprises a me...  
WO/2009/028977A1
The invention relates to a hydrogen-gas engine which uses electrojet motion and is designed in the form of a ceramic or glass combustion chamber, to which a fuel with an oxidising agent and high-frequency electromagnetic energy for atomi...  
WO/2009/016264A1
The invention relates to a Hall-effect ion ejection device that comprises a longitudinal axis (00') substantially parallel to the ion ejection direction, and comprises at least: a main ionisation and acceleration annular channel (21), th...  
WO/2007/008234A4
Several methods of increasing the thrust and energy efficiency of charged particle jet engines operating in a gaseous or liquid medium have been developed. We identify the three main components of charged particle thrust generation and p...  
WO/2007/008234A3
Several methods of increasing the thrust and energy efficiency of charged particle jet engines operating in a gaseous or liquid medium have been developed. We identify the three main components of charged particle thrust generation and p...  
WO/2008/048249A3
A scalable flat-panel nano-particle MEMS/NEMS thruster includes a grid having a plurality of electrodes to establish electrical fields. A liquid is disposed in a liquid reservoir of the grid. The liquid is positioned within the electrica...  
WO2008089753A8  
WO/2008/113942A1
The invention relates to a field effect emitter for a field emission thruster or colloid thrusters, that comprises first and second revolution parts (110, 120) defining an inner tank (160) for supplying a conductive liquid metal or ionic...  
WO/2008/089753A2  
WO/2008/083636A1
The invention relates a flying device with at least one propulsion unit in an oval body shape, which that the propulsion unit consists of a closed chamber (1), with gas in this space with lower pressure than the air pressure, containing ...  
WO2008043867B1
The invention relates to an installation for obtaining mechanical energy from solar thermal energy, combining a conventional solar thermal installation connected to heat exchangers housed inside an externally-insulated vertical shell hav...  
WO/2008/031058A3
Spindt-type field-emission cathodes for use in electric propulsion (EP) systems having self- assembling nanostructures that can repeatedly regenerate damaged cathode emitter nanotips. A nanotip is created by applying a negative potential...  
WO/2008/071287A1
The invention relates to a plasma accelerator arrangement with electrostatic acceleration of ions by an electric field running through a plasma chamber essentially parallel to the beam direction with a plasma geometry of the cylindrical ...  
WO2008035061A8
A pulsed plasma thruster and method of operation are provided. The pulsed plasma thruster comprises solid propellant material. A main discharge source provides a pulsed discharge across the propellant material for ablating the propellant...  

Matches 151 - 200 out of 1,303