Class / Patent application number | Description | Number of patent applications / Date published |
060202000 | Ion motor | 65 |
20080223017 | HALL-TYPE ELECTRIC PROPULSION - The present invention provides a hall-type electric propulsion that exhibits both overheating protection and operational stability, thereby simultaneously solving the problem of waste heat, which worsens with micronization, and the problem of discharge current oscillation. First, the magnetic flux distribution in ionization/acceleration channel is formed to optimize ion velocity vector, whereupon a propellant flow passage (propellant conduit) is disposed in a magnetic pole of the propulsion, or more specifically in the vicinity of the acceleration channel, and then propellant is passed through the flow passage. Thus, the magnetic pole, which is overheated by the generated plasma, can be cooled, and at the same time the propellant can be heated. Furthermore, the heated propellant is choked immediately before being introduced into the ionization/acceleration channel by a throat region provided immediately before the ionization/acceleration channel, and as a result the sonic speed of neutral species (propellant) is increased. | 09-18-2008 |
20080271430 | Electronegative Plasma Motor - The subject of the invention is a plasma motor for the extraction of a positive ion flow. The plasma motor has a single ionization stage ( | 11-06-2008 |
20090000268 | THERMONUCLEAR PLASMA REACTOR FOR ROCKET THRUST AND ELECTRICAL GENERATION - A reactor system produces plasma rocket thrust using alpha-initiated atomic fuel pellets without the need for a critical mass of fissionable material. The fuel pellets include an outer layer reactive material to alpha particles to generate neutrons (e.g., porous lead or beryllium), an under-layer of fissionable material (e.g., thorium or enriched uranium), and an optional inner core of fusion material (e.g., heavy water ice, boron hydride). The pellets are injected one at a time into a charged reaction chamber containing a set of alpha beam channels, possibly doubling as ion accelerators, all directed toward a common point. Alpha particles converging on each successive pellet initiate an atomic reaction in the fissionable under-layer, via a neutron cascade from the pellet outer layer, producing plasma that is confined within the chamber. This may be enhanced by atomic fusion of the optional inner core. The resulting high-energy plasma creates electrostatic pressure on the chamber and is allowed to exit the chamber through a port. An ion accelerator at the exhaust port of the chamber accelerates outgoing plasma ions, possibly with added reaction mass, to generate the rocket thrust. An electric circuit that includes the charged chamber may collect the electrons in the plasma to help power the ion accelerator(s). | 01-01-2009 |
20090113872 | Electrospray source - An electrospray source useful for a variety of applications and including an emitter with a porous media flow distributor having a surface forming multiple Taylor cones. A casing about the porous media flow distributor controls the direction of a working fluid through the porous media. An extractor is at a potential different than the emitter for forming the Taylor cones. A guard electrode is disposed between the emitter and the extractor and is at or above the potential of the emitter for shaping the electric field formed between the emitter and the extractor. | 05-07-2009 |
20090120055 | METHOD AND APPARATUS FOR PROPELLING A VESSEL IN A ZERO GRAVITY ENVIRONMENT - The invention relates to a space vessel that includes the vessel, at least one propulsion unit mounted to the vessel, and a source of particles. The propulsion unit includes a hollow body having a first end and a second end. The first end includes a circuit and a speaker. The circuit includes an antenna and a diode and the speaker is configured to receive the signal from the circuit. The second end includes a flexible membrane. The invention also relates to the propulsion unit itself and methods of propelling space vessels using radio-frequency waves. | 05-14-2009 |
20090255231 | MULTIPLE PHASE POWER SUPPLY FOR ROCKET ENGINES - Conventional power supplies that actify the grids of electric rockets use an output capacitor to smooth the output DC voltage signal. Large capacitors tend to store a great amount of energy. Arcing acts to transfer this energy to create a well or pit on an accelerator grid of the electric rockets that may eventually cause repeating arcing or perforation on the accelerator grid. Various embodiments of the present invention eliminate or reduce the need to use an output capacitor. Additionally, various embodiments of the present invention use multiple phases of an input signal into the power supply to cause the output DC voltage signal to be substantially smooth. | 10-15-2009 |
20090288385 | CHARGED PARTICLE THRUST ENGINE - 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 provide means to take maximum advantage of each. We also describe several methods to reduce the energy associated with the generation of charged particles and to minimize the number of charged particles needed to further increase energy efficiency. In addition to the methods used to increase thrust and energy efficiency, we have also developed several methods of efficiently controlling the amount and direction of thrust. Finally, we show many uses of these charged particle jet engines and ways to control them. | 11-26-2009 |
20090308049 | ELECTRIC PROPULSION SYSTEM - An electric propulsion system including a plasma chamber having a first output aperture having first acceleration and screen grids, and a second output aperture having second acceleration and screen grids. The screen grids are maintained at a constant positive potential. In use, ions are expelled from the two apertures in anti-parallel directions. By independently controlling the potentials of the acceleration grids to adjust the rates of ion extraction from the output apertures, small resultant thrusts at the μN level may be obtained and the resultant thrust maybe continuously reduced to zero. By closing off apertures of one of the screen grids, thrust at the mN may be obtained with sub-μN accuracy. The system therefore provides functionality previously achievable only with plural types of electric propulsion system, providing weight and complexity savings for satellites or space-probes comprising such systems. | 12-17-2009 |
20100018184 | NANO-PARTICLE FIELD EXTRACTION THRUSTER - 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 having a generally dry mixture disposed therein, a plurality of particles suspended in the generally dry mixture, a biasing member applying a biasing force to the generally dry mixture in the reservoir, and a sieve electrode system in electrical communication with the grid. The sieve electrode system has a plurality of through-holes extending from the reservoir to the grid, such that the sieve electrode system cooperates with the biasing member to extract at least one particle from the generally dry mixture and into the grid whereby the electrical fields charge and accelerate the particle in the vias. | 01-28-2010 |
20100018185 | EMITTER FOR IONIC THRUSTER - The invention relates to a field effect emitter for a field emission thruster or colloid thrusters, that comprises first and second revolution parts ( | 01-28-2010 |
20100089027 | MAGNETIC GAS ENGINE AND METHOD OF EXTRACTING WORK - The present subject matter overcomes the deficiencies in the prior art by introducing or generating charged particles in an air stream and manipulating the air stream with magnetic fields operating on the charged particles. Embodiments of the present subject mater compress the air stream by accelerating charged particles with a moving magnetic field, where the magnetic field has a velocity perpendicular to its flux lines. The increased velocity of the charged particles increases the statistical mean particle velocity and thereby increases the pressure in the air stream. The compressed air stream is then heated and expanded through a second magnetic field. The expansion of the air stream substantially increases the velocity of the air stream and the charged particles therein. The interaction of the high velocity charged particles and the magnetic field imparts a force perpendicular to the flux lines, this force powers the movement of the magnetic field and can also be extracted in the form of mechanical work. | 04-15-2010 |
20100107596 | LOW-POWER HALL THRUSTER - A low power hall thruster is provided that is effective for micro-spacecrafts and nano-spacecrafts as well as mini-spacecrafts. The hall thruster comprises a co-axial acceleration channel capable of being applied with predominantly-radial magnetic field and a co-axial anode within a cavity capable of being applied with substantially longitudinal magnetic field. A cathode-compensator is placed beyond the acceleration channel and magnetic system is provided capable of generating the radial magnetic field within the co-axial acceleration channel and the longitudinal magnetic field within the co-axial anode. An electrically isolated gas distributor is also provided. | 05-06-2010 |
20100146931 | METHOD AND APPARATUS FOR IMPROVING EFFICIENCY OF A HALL EFFECT THRUSTER - A method of designing a plasma thruster with improved thrust efficiency. The method includes providing a thruster body having a discharge chamber with a first opening having an axis centrally located relative thereto; a cathode having a second opening at a first end thereof, the cathode being disposed at a radial position, relative to the axis, outside of the first opening; and an outer pole piece including a magnetic plate, the outer pole piece being adjacent to the first plane and extending radially outward, relative to the axis. At least one electromagnet is disposed adjacent to, and in magnetic communication with, the outer pole piece, a magnetic field being formed adjacent to the thruster body and the outer pole piece and having a separatrix surface therein. The magnetic field is altered such that the separatrix surface is moved radially outward relative to the axis toward the second opening. | 06-17-2010 |
20100192538 | Capacitive Stator - A standard 4-pole electric motor stator with capacitive plates in-line with the magnetic poles, but electrically 90° out of phase, produces two Lorentz force geometries 90° out of phase with each other (i.e., vertical, horizontal). An alternating source electrically rotates this pair of Lorentz geometries producing a propagating electromagnetic wave at the source frequency within the vacant internal cavity. Any charged particle within the cavity and along its axis will be accelerated or decelerated from an initial velocity via the Lorentz force. The rotating geometry provides for the coupling of the Lorentz force through a current loop and diamagnetism, providing acceleration and deceleration of non-charged particles. The force coupling is dependent upon the material's electromagnetic properties, the frequencies generated by the capacitive stator, and the velocity of the particles within the capacitive stator's influence. | 08-05-2010 |
20100199632 | SOLUTE ION COULOMB FORCE ACCELARATION AND ELECTRIC FIELD MONOPOLE PASSIVE VOLTAGE SOURCE - At least one electrode assembly is configured to enable like charged ions to convert potential energy of the like charged ions into kinetic energy based on the Coulomb forces therebetween via linear alignment thereof, or enable a first portion of like charged ions to convert potential energy of the first portion of like charged ions to kinetic energy based on interaction with the Coulomb forces of a second portion of like charged ions, or enable a first portion of like charged ions to convert potential energy of a second portion of like charged ions to kinetic energy based on similar interaction. Various electrode assemblies are described and corresponding methods of converting potential energy of like charged ions to kinetic energy. The like charged ions are configured to form a passive electric field voltage source that may have one or more electric field monopoles to enable motion of a mobile assembly. | 08-12-2010 |
20100212284 | ION THRUSTER GRIDS AND METHODS FOR MAKING - An ion thruster includes an accelerator grid proximate to an ionization chamber for drawing and accelerating ions from the chamber. The accelerator grid include a core and an overlying layer that is made of a material having a mass less than that of the propellant. | 08-26-2010 |
20100251690 | Current Controlled Field Emission Thruster - There is disclosed a field emission electric propulsion (FEEP) system including a FEEP thruster having at least one emitter and an extractor electrode, and a power supply. The power supply may provide an extractor voltage applied between the emitter and the extractor electrode. The power supply may be operable in a constant current mode in which the extractor voltage is controlled to set an ion current flowing from the emitter at a target current level. | 10-07-2010 |
20100251691 | FIFTH-FORCE APPARATUS AND METHOD FOR PROPULSION - A method and means to produce a force for propulsion comprises a source of electrons and a means to produce hyperbolic electrons; whereas, a gravitating body such as the Earth provides a repulsive fifth force on the hyperbolic electrons. Hyperbolic electrons are produced by elastically scattering the electrons of an electron beam from atoms or molecules at specific energies. The emerging beam of hyperbolic electrons experiences a fifth force away from the Earth, and the beam moves upward (away from the Earth). To use this invention for propulsion, the repulsive fifth force on the hyperbolic-electron beam is transferred to a negatively charged plate. The Coulombic repulsion between the beam of hyperbolic electrons and the negatively charged plate causes the plate (and anything connected to the plate) to lift. The craft may additionally gain angular momentum from the fifth force along an axis defined by the gravitational force, and the craft may be tilted to move the vector away from the axis such that a component of acceleration tangential to the surface of a gravitating body is achieved via conservation of the angular momentum. | 10-07-2010 |
20100263349 | HIGH VOLTAGE MULTIPLE PHASE POWER SUPPLY - To explore deeper expanses of space, rocket ships need rockets that can last twice as long as conventional rockets. Modern rockets use the electric field to attract and accelerate charged particles out and away from the combustion chamber. Space qualified components to increase the electric field are difficult to obtain. Various embodiments of the present subject matter use multiple phases of an input signal into the power supply to cause the output DC voltage signal to be substantially smooth. These smoother signals reduce the voltage requirements of the output diodes and capacitors thereby making them easier to obtain. | 10-21-2010 |
20100269483 | ION PROPULSION EMITTER AND METHOD FOR THE PRODUCTION THEREOF - The emitter for ion propulsion comprises: —two mutually coupled semi-emitters ( | 10-28-2010 |
20100300064 | Lateral Flow High Voltage Propellant Isolator - A high voltage propellant isolator includes at least two different types of isolator rings or segments, in alternating lateral arrangement, that direct the flow of propellant, such as xenon gas, in a tortuous path through the isolator. | 12-02-2010 |
20100313543 | Lateral Flow High Voltage Propellant Isolator - A high voltage propellant isolator includes at least two different types of isolator rings or segments, in alternating lateral arrangement, that direct the flow of propellant, such as xenon gas, in a tortuous path through the isolator. | 12-16-2010 |
20100326042 | Efficient RF Electromagnetic Propulsion System With Communications Capability - An electronic propulsion engine that creates a propulsive force or thrust using electromagnetic forces or electrostatic forces, with an effect that is similar to the thrust of a jet or rocket engine. Forces are generated using electromagnets or capacitor plates that are separated by dielectric spacer cores and are operated with two modulated currents. The two modulated currents are synchronized, but with a relative phase such that the forces on the two magnets or capacitor plates are not balanced. Included are techniques to reduce circuit impedance and control electric-magnetic field dispersion, such as tuned LCR circuits, dielectric core materials between the magnets or capacitor plates, and RF superconductors result in high propulsion efficiencies. The system operates at RF frequencies and can also be used as a communication device. | 12-30-2010 |
20110005191 | COLD CATHODES AND ION THRUSTERS AND METHODS OF MAKING AND USING SAME - 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 cathode includes an emitter formed from a plurality of vertically aligned carbon nanotubes. An ion thruster can include the improved cathode. | 01-13-2011 |
20110067380 | ELECTRIC THRUSTER FOR A SPACECRAFT - The invention relates to an electric thruster for a spacecraft. According to the invention, the thruster (II) comprises a jet generating portion (G | 03-24-2011 |
20110154803 | ELECTRODYNAMIC METHOD - An electrodynamic method includes providing an electrodynamic structure with a periphery, providing power, collecting electrons, and emitting electrons. The emitting electrons and the collecting electrons utilizes at least 20% of the periphery of the electrodynamic structure. The method includes conducting current to provide at least one of electrodynamic propulsion and power generation. | 06-30-2011 |
20110232260 | Ion impulse turbine - A turbine power plant which produces power from a plasma and high voltage electricity. A plurality of powerful electric fields are in operation within the turbine. One set of electrodes produce electric fields that charge the plasma to a very high degree of ionization, and forces the plasma to be pressed against a plurality of normally positively charged electrodes making up what is termed the power field. Suddenly, the plurality of electrodes making up the polarization fields are de-energized, and simultaneously, the plurality of electrodes making up the power fields are energized, and repels the plasma at an extremely high velocity into a plurality of turbine blades. As they strike the turbine blades, huge amounts of kinetic energy is transferred to a turbine shaft. | 09-29-2011 |
20110232261 | ELECTRONEGATIVE PLASMA THRUSTER WITH OPTIMIZED INJECTION - A plasma thruster includes extraction of a stream of positive ions. The plasma thruster includes a single ionization stage; means for injecting ionizable gas for said ionization stage, said means comprising at least first means for injecting a first gas and second means for injecting an electronegative second gas; means for creating an RF electric field so as to cause the gases to ionize in the ionization stage, said means creating a first zone called the hot zone, in the ionization stage; the first gas being distributed in the hot first zone, the second gas being distributed in a second zone less hot than said first zone; first means for extracting a stream of negative ions and second means for extracting a stream of positive ions, these being both connected to the ionization stage; and the extraction of a stream of positive ions and the extraction of a stream of negative ions, ensuring that the thruster is electrically neutral. | 09-29-2011 |
20110258981 | MICRO-CATHODE THRUSTER AND A METHOD OF INCREASING THRUST OUTPUT FOR A MICRO-CATHODE THRUSTER - A magnetically enhanced micro-cathode thruster assembly for providing long-lasting thrust is provided. The micro-cathode thruster assembly includes a tubular housing, a tubular cathode, an insulator, an anode and a magnetic field. The tubular housing includes an open distal end. The tubular cathode is housed within the housing and includes a distal end positioned proximate the open distal end of the housing. The insulator is in contact with the cathode forming an external cathode-insulator interface. The anode is housed within the housing, proximate the open distal end of the housing. The magnetic field is positioned at or about the external cathode-insulator interface and has magnetic field lines with an incidence angle of about 0 to about 90 degrees and preferably about 4 to about 30 degrees relative to the external cathode-insulator interface. | 10-27-2011 |
20110277444 | Ion Drive for a Spacecraft - An ion drive for a spacecraft, including a high-frequency generator for generating an alternating electromagnetic field for the ionization of a propellant and an acceleration system for the charge carriers, is provided. The ion drive includes a voltage source with which the high voltages that are necessary for the acceleration system can be derived from the currents and/or voltages generated by the high-frequency generator for generating the alternating electromagnetic field. | 11-17-2011 |
20110277445 | ELECTRIC PROPULSION - 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 to the apertures, and are driven differentially by a radio frequency (RF) drive module. By driving the coils differentially, the electric field in the region of the two apertures can be differentially controlled, and a variation of output thrusts at the two apertures is possible. In this way a net thrust can be produced, which net thrust is varied by controlling the drive to the two coils. | 11-17-2011 |
20120031070 | APPARATUS, SYSTEMS AND METHODS FOR ESTABLISHING PLASMA AND USING PLASMA IN A ROTATING MAGNETIC FIELD - Systems and methods establish plasma in a rotating magnetic field. An exemplary embodiment is a plasma thruster that establishes a first transverse magnetic field with respect to a system axis of a plasma propulsion system; establishes a second transverse magnetic field oriented orthogonally to the first transverse magnetic field, wherein the second transverse magnetic field is out of phase with the first transverse magnetic field; and establishes a magnetic field aligned with the system axis using a plurality of magnet elements oriented along the system axis. A plasma containment portion defines an interior region, wherein an interior region of a plasma containment portion accommodates a plasma that is established by a rotating magnetic field component that is cooperatively established by the first transverse magnetic field and the second transverse magnetic field, and wherein the plasma is accelerated out of the plasma containment portion by magnetic forces to generate a propulsion force. | 02-09-2012 |
20120110977 | SYSTEM AND METHOD OF PHOTOIONIZATION OF FULLERENE AND DERIVATIVE CLUSTERS FOR HIGH THRUST-DENSITY ION THRUSTERS - The present invention is for a system and a method of VUV photoionization of fullerene and derivative clusters followed by their thermal effusion for a practical energy-efficient and economically-viable high thrust density ion thruster. By taking advantage of the state-of-the-art high intensity VUV photon sources, present invention is able to provide much softer ionization with minimal internal energy deposition than the ionization in the electron impact or charge exchange type ionization in plasma environment used in conventional ion thrusters. Because the invention eliminates the need of additional gas for forming discharge plasma, it permits simpler and lighter structures than the conventional fullerene thrusters with significantly enhanced propellant-usage efficiencies, thrust to power ratios, and thrust to weight ratios. Because the present invention employs softer VUV photoionization, it permits the usage of heavier and more complex fullerene derivatives, nanotubes, and nanotube derivatives than fullerene clusters for fuels without significantly fragmenting them. | 05-10-2012 |
20120117938 | HALL EFFECT PLASMA THRUSTER - The Hall effect plasma thruster comprises a main annular channel ( | 05-17-2012 |
20120137652 | Electromagnetic Thrust System - A method for developing thrust from current flow is disclosed. In a first embodiment, a plurality of loops ( | 06-07-2012 |
20120144796 | MICROFLUIDIC ELECTROSPRAY THRUSTER - An electrospray thruster and methods of manufacturing such thrusters are provided. The micro-electrospray thruster increases the thrust density of conventional electrospray thrusters by miniaturizing the individual components of the thruster thereby allowing for the increase in the number and density of the charged particle emitters. | 06-14-2012 |
20120311992 | HALL THRUSTER, COSMONAUTIC VEHICLE, AND PROPULSION METHOD - In a Hall thruster | 12-13-2012 |
20130067883 | SPACECRAFT THRUSTER - A thruster ( | 03-21-2013 |
20130125526 | HALL-EFFECT MOTOR IN WHICH THE TEMPERATURE OF THE CATHODE-HEATING DEVICE IS CONTROLLED - A Hall effect thruster including: a discharge channel with an open downstream end; a cathode situated outside the discharge channel; an injector system configured to inject atoms of gas into the discharge channel, the injector system situated at an upstream end of the discharge channel and also forming a cathode; a heater device configured to heat the cathode; a measurement mechanism measuring temperature of the heater device, and a regulator circuit regulating the temperature such that the heater device heats so long as its temperature is less than a threshold temperature from which the thruster is capable of starting, and ceases to heat shortly after the threshold temperature has been reached. | 05-23-2013 |
20140033677 | EXTERNALLY POWERED VEHICLE PROPULSION SYSTEM - A vehicle propulsion system comprises a propellant source, a microwave energy source; an ionizer, a heater, and a propellant accelerator. The ionizer is configured for receiving propellant and for also receiving microwave energy from the microwave energy source so as to produce ionized propellant. The heater comprises a heater shell that defines a plasma heating cavity and is configured for receiving the ionized propellant from the ionizer. The heater shell is configured to transmit microwave energy received from the microwave energy source to the ionized propellant in the plasma heating cavity and to thereby facilitate absorption of microwave energy by the ionized propellant to produce heated ionized propellant. The propellant accelerator is configured for receiving the heated ionized propellant from the heater, accelerating the heated ionized propellant to produce accelerated propellant, and expelling the accelerated propellant in a desired direction to impose a reaction force (i.e., thrust) upon the vehicle. | 02-06-2014 |
20140053531 | METALLIC WALL HALL THRUSTERS - A Hall thruster apparatus having walls constructed from a conductive material, such as graphite, and having magnetic shielding of the walls from the ionized plasma has been demonstrated to operate with nearly the same efficiency as a conventional non-magnetically shielded design using insulators as wall components. The new design is believed to provide the potential of higher power and uniform operation over the operating life of a thruster device. | 02-27-2014 |
20140090357 | HALL-EFFECT THRUSTER - A Hall effect thruster includes at least one tank of gas under high pressure, a pressure regulator module, a gas flow rate control device, an ionization channel, a cathode placed in a vicinity of an outlet from the ionization channel, an anode associated with the ionization channel, an electrical power supply unit, an electric filter, coils for creating a magnetic field around the ionization channel, and an additional electrical power supply unit for applying a pulsating voltage between the anode and the cathode. | 04-03-2014 |
20140109549 | THRUSTER GRID CLEAR CIRCUITS AND METHODS TO CLEAR THRUSTER GRIDS - Thruster grid clear circuits and methods to clear thruster grids are disclosed. An example apparatus includes a low voltage grid clear circuit to apply first energy to a grid at a first voltage, and a high voltage grid clear circuit to detect a failure of the applied energy to clear a short circuit condition of the grid and to apply second energy to the grid at a second voltage higher than the first voltage. | 04-24-2014 |
20140137537 | Rotary Switch Assembly for Ion Propulsion System - A gridded ion propulsion system comprising two power controllers, four ion thrusters, and two switch assemblies. One switch assembly is connected to the two power controllers and to two of the four ion thrusters. The other switch assembly is connected to the two power controllers and to the other two ion thrusters. Each switch assembly has first and second switching states which can be selected to enable either power controller to supply power to any one of the four ion thrusters. Each switch assembly comprises a respective movable body and a respective multiplicity of switches which change state in unison when the movable body changes position. For example, the movable body may be a rotatable hollow shaft driven by a stepper motor. | 05-22-2014 |
20140202131 | PLASMA MICRO-THRUSTER - A plasma micro-thruster, including: an elongate and substantially non-conductive tube having a first end to receive a supply of propellant gas, and an open second end to act as an exhaust; first, second, and third electrodes extending circumferentially around the tube and being mutually spaced along a longitudinal axis of the tube, the third electrode being longitudinally interposed between the first and second electrodes; wherein the tube and the first, second and third electrodes are configured to generate a plasma from propellant gas flowing though the tube from the first end of the tube when the third electrode receives radio frequency power and the first and second electrodes are electrically grounded relative to the third electrode, such that the expansion of the plasma from the open end of the tube generates a corresponding thrust. | 07-24-2014 |
20140208713 | ELECTRIC PROPULSION SYSTEM WITH STATIONARY PLASMA THRUSTERS - An electric propulsion system includes a first stationary plasma thruster including a single first cathode, a first anode, and a first gas manifold, and a second stationary plasma thruster including a single second cathode, a second anode, and a second gas manifold. The system further includes an electrical connection device common to the first and second cathodes, first and second gas flow rate control devices with a common fluid flow device for feeding gas, and a selective control device for activating at any given instant only one of the first and second cathodes in co-operation with one or the other of the first and second anodes. | 07-31-2014 |
20140260179 | System, Method and Apparatus for Lean Combustion with Plasma from an Electrical Arc - The present invention provides a plasma arc torch that can be used for lean combustion. The plasma arc torch includes a cylindrical vessel, an electrode housing connected to the first end of the cylindrical vessel such that a first electrode is (a) aligned with a longitudinal axis of the cylindrical vessel, and (b) extends into the cylindrical vessel, a linear actuator connected to the first electrode to adjust a position of the first electrode, a hollow electrode nozzle connected to the second end of the cylindrical vessel such that the center line of the hollow electrode nozzle is aligned with the longitudinal axis of the cylindrical vessel, and wherein the tangential inlet and the tangential outlet create a vortex within the cylindrical vessel, and the first electrode and the hollow electrode nozzle create a plasma that discharges through the hollow electrode nozzle. | 09-18-2014 |
20140290210 | HALL EFFECT THRUSTER - A steerable-thrust Hall effect thruster in which a final stage of a magnetic circuit includes an inner pole and a facing outer pole, the inner pole being offset axially downstream relative to the outer pole, so that a magnetic field is inclined relative to a transverse plane of the thruster. | 10-02-2014 |
20140305096 | HYBRID ELECTRIC PROPULSION FOR SPACECRAFT - A propulsion system for spacecraft is based on an electric engine that expels propellant to achieve thrust. The propellant is first ionized to generate a plasma. Plasma particles are selectively accelerated via a pulsed laser that accelerates predominantly the electrons in the plasma. The electrons are expelled first, forming a space charge that acts as a virtual cathode to accelerate the positive ions. Interactions between the laser beam and plasma electrons are predominantly through the ponderomotive force. | 10-16-2014 |
20140345251 | Efficient Electromagnetic Propulsion System With Communications Capability - An electronic propulsion engine that creates a propulsive force or thrust using electromagnetic forces or electrostatic forces, with an effect that is similar to the thrust of a jet or rocket engine. Forces are generated using electromagnets or capacitor plates that are separated by dielectric spacer cores and are operated with two modulated currents. The two modulated currents are synchronized, but with a relative phase such that the forces on the two magnets or capacitor plates are not balanced. Included are techniques to reduce circuit impedance and control electric-magnetic field dispersion, such as tuned LCR circuits, dielectric core materials between the magnets or capacitor plates, and RF superconductors result in high propulsion efficiencies. The system operates at RF frequencies and can also be used as a communication device. | 11-27-2014 |
20150020502 | PLASMA THRUSTER AND METHOD FOR GENERATING A PLASMA PROPULSION THRUST - The invention, which relates to a miniaturisable plasma thruster, consists of: —igniting the plasma by microhollow cathode discharge close to the outlet and inside the means for injecting the propellant gas, said injection means being magnetic and comprising a tip at the downstream end thereof; —bringing the electrons of the magnetised plasma into gyromagnetic rotation, at the outlet end of said injection means; —sustaining the plasma by means of Electron Cyclotron Resonance (ECR), said injection means being metal and being used as an antenna for electromagnetic (EM) emission, the volume of ECR plasma at the outlet of said injection means being used as a resonant cavity of the EM wave; —accelerating the plasma in a magnetic nozzle by diamagnetic force, the ejected plasma being electrically neutral. | 01-22-2015 |
20150107219 | CHEMICAL-ELECTROMAGNETIC HYBRID PROPELLER WITH VARIABLE SPECIFIC IMPULSE - A chemical-electromagnetic hybrid propeller with variable specific impulse. Fuel gas ejected out from a spraying tube of the chemical propeller through chemical propulsion enters an ionization chamber through a first magnetic mirror tube for ionization. The fuel gas after ionization is heated up by radio-frequency ion cyclotron waves in an ion cyclotron wave heating chamber so as to improve the kinetic energy. Then a second magnetic mirror tube is used, so that ions in the fuel gas after the ionization are heated up many times in a reciprocating manner between the magnetic mirror tubes, and ejected to generate forward propulsion force. By means of the propeller, the propulsion force and the specific impulse are greatly increased. | 04-23-2015 |
20150128560 | MAGNETICALLY SHIELDED MINIATURE HALL THRUSTER - Magnetically shielded miniature Hall thrusters are disclosed that use a unique magnetic field topology that prevents the magnetic field lines from intersecting the discharge channel walls in the acceleration region of the thruster. Instead, the lines of force originating from both the inner and outer pole pieces curve around the downstream edges of the discharge channel and follow the channel walls towards the anode. This unique field topology results in low electron temperature at the discharge channel walls while eliminating strong electric field components that would otherwise lead to high erosion rates and power deposition from ion acceleration into the channel walls. | 05-14-2015 |
20150300329 | PROPELLANT GAS SUPPLY FOR AN IONIC PROPULSION UNIT - A field of feeding propellant gas to ion thrusters, and in particular a method of feeding an ion thruster with propellant gas coming from a pressurized tank via a feed circuit including an on/off valve and, in succession downstream from the on/off valve, a high pressure restrictor, a buffer tank, and at least one low pressure restrictor. The method includes the steps of calculating a pressure setpoint for the buffer tank as a function of a flow rate setpoint, calculating the difference between the pressure setpoint for the buffer tank and a pressure measured in the buffer tank, calculating a setpoint for the opening time of the on/off valve as a function of the difference and of a pressure inside the pressurized tank, and opening the on/off valve in compliance with the opening time setpoint. | 10-22-2015 |
20160010631 | GENERATING ELECTROSPRAY FROM A FERROFLUID | 01-14-2016 |
20160032907 | Magnetic Gas Engine and Method of Extracting Work - The present subject matter overcomes the deficiencies in the prior art by introducing or generating charged particles in an air stream and manipulating the air stream with magnetic fields operating on the charged particles. Embodiments of the present subject mater compress the air stream by accelerating charged particles with a moving magnetic field, where the magnetic field has a velocity perpendicular to its flux lines. The increased velocity of the charged particles increases the statistical mean particle velocity and thereby increases the pressure in the air stream. The compressed air stream is then heated and expanded through a second magnetic field. The expansion of the air stream substantially increases the velocity of the air stream and the charged particles therein. The interaction of the high velocity charged particles and the magnetic field imparts a force perpendicular to the flux lines, this force powers the movement of the magnetic field. | 02-04-2016 |
20160040658 | SELF CONTAINED ION POWERED AIRCRAFT - A self-contained ion powered aircraft assembly is provided. The aircraft assembly includes a collector assembly, an emitter assembly, and a control circuit operatively connected to at least the emitter and collector assemblies and comprising a power supply configured to provide voltage to the emitter and collector assemblies. The assembly is configured, such that, when the voltage is provided from an on board power supply, the aircraft provides sufficient thrust to lift each of the collector assembly, the emitter assembly, and the entire power supply against gravity. | 02-11-2016 |
20160083119 | Thrust Augmentation Systems - Methods and apparatuses for augmenting thrusts using ionized gases. A gas is partially ionized, which then ionizes a second, neutral gas. Vector addition can be used to increase the velocity of the first ionized gas with relatively high efficiency due to the gyroradii of the ionized particles. If the velocity is sufficiently high the critical ionization velocity of at least some of the elements in the second gas will be exceeded, greatly increasing A magnetic field creates a Townsend cascade in the ionized gases, greatly increasing the amount of ionized gases. The magnetic field can be created using permanent magnets or superconductors, thereby requiring little or no power to operate. To produce thrust the ionized gases are accelerated through a coil, which can have logarithmically increasing coil spacings. Electrical power can be generated by passing the accelerated ionized gas through generating coils and/or a turbine. In another embodiment, electromagnetic forces in the atmosphere can be used to propel a vehicle that has parallel superconducting coils circumferentially disposed about an axis of travel of the vehicle, the coils comprising one or more moveable segments which are reversibly disconnectable from other segments in said coil, thereby allowing the polarity of the coil to be reversed. The ionization engines described above can be used to further accelerate or decelerate the vehicle. | 03-24-2016 |
20160114908 | Electrically Powered Propulsion System for Use in a Spacecraft - An electrically powered propulsion system for a spacecraft includes a first center of gravity at a first time of operation and a second center of gravity at a second time of operation, where the second center of gravity is different from the first center of gravity. The electrically powered propulsion system includes a thruster realignment mechanism and at least two thrusters coupled to the thruster realignment mechanism. Each of the at least two thrusters has an individual thrust vector. The thruster realignment mechanism is adapted such that, in a first position, the individual thrust vectors of the at least two thrusters pass through the first center of gravity and that, in a second position, the individual thrust vectors of the at least two thrusters pass through the second center of gravity. The thruster realignment mechanism holds the first position in the event all of the at least two thrusters are without any failure. In addition, the thruster realignment mechanism realigns the thrusters to the second position in the event of at least one of (i) a failure of one of the at least two thrusters, and (ii) a predetermined time criterion is fulfilled. | 04-28-2016 |
20160115946 | APPARATUS, SYSTEMS AND METHODS FOR ESTABLISHING PLASMA AND USING PLASMA IN A ROTATING MAGNETIC FIELD - Systems and methods establish plasma in a rotating magnetic field. An exemplary embodiment is a plasma thruster that establishes a first transverse magnetic field with respect to a system axis of a plasma propulsion system; establishes a second transverse magnetic field oriented orthogonally to the first transverse magnetic field, wherein the second transverse magnetic field is out of phase with the first transverse magnetic field; and establishes a magnetic field aligned with the system axis using a plurality of magnet elements oriented along the system axis. A plasma containment portion defines an interior region, wherein an interior region of a plasma containment portion accommodates a plasma that is established by a rotating magnetic field component that is cooperatively established by the first transverse magnetic field and the second transverse magnetic field, and wherein the plasma is accelerated out of the plasma containment portion by magnetic forces to generate a propulsion force. | 04-28-2016 |
20160200458 | CONVERGING/DIVERGING MAGNETIC NOZZLE | 07-14-2016 |
20160377029 | HELICON YIELD PLASMA ELECTROMAGNETIC RAM-SCRAMJET DRIVE ROCKET ION VECTOR ENGINE - HYPERDRIVE receives continuous air breathing assistance from compressed atmospheric air through a high speed magnetically core driven turbine accelerator which resolves around a common flow path tunnel. The tunnel runs from the front to the back of the engine. It is assisted by a series of radial geometric ramjet engines that share the common flow path tunnel for hypersonic exhaust but has separate inlet air from a linear aerospike which governs mass flow of air, velocity of inlet air and pressure to the turbine and/or ramjets, as well as the positioning of the shock wave at the inlet to reduce aerodynamic drag. The ramjet is of hybrid engine design where it can also function as a scramjet, thus a ram-scramjet structure for combustion in a radial configuration about the engine (aft of an electrical compressor), where the common flow path tunnel also serves as a compression tunnel to compress air through a the constantly occurring series of compression shocks entering from and around the aerospike. | 12-29-2016 |
20160377064 | CONTROL SYSTEM FOR A PLURALITY OF ELECTRIC SATELLITE THRUSTERS AND ELECTRIC PROPULSION DEVICE COMPRISING SUCH A CONTROL SYSTEM - A control system comprises sources of supply, in terms of power and in terms of control signals, capable of equally piloting each of the electric thrusters and further comprises a switching device capable of linking any one of the sources of supply to any one of the electric thrusters. The switching device comprises a rotary main roller divided into a number of angular segments comprising input and output conductive tracks and pre-wired electrical networks linking the input conductive tracks to the output conductive tracks of each angular segment, the pre-wired electrical networks associated with the different angular segments all being different and dedicated to different configurations for the piloting of the electric thrusters by the sources of supply. | 12-29-2016 |
20180022475 | HALL EFFECT THRUSTER AND A SPACE VEHICLE INCLUDING SUCH A THRUSTER | 01-25-2018 |
20180023550 | IODINE PROPELLANT RF ION THRUSTER WITH RF CATHODE | 01-25-2018 |