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JP2015072909A |
To provide a plasma source that ionizes gas and heats plasma using an RF antenna, an applied magnetic field, plasma and a coaxial gas confinement tube, and specifically to provide a technique relating to improvements to antennas, magnet ...
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JP2015509262A |
The present invention relates to a small plasma thruster, and is an inside and near an exit promotion fuel gas, [of an injection means] The above-mentioned injection means is based on magnetism, and it has [lighting plasma by micro hollo...
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JP5685255B2 |
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JP2013222578A5 |
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JP5677843B2 |
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JP5671673B2 |
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JP2015502480A |
The present invention is set to a final stage of a Hall effect thruster and a magnetic circuit which has an inside pole (18) and an outside pole (15) which meets especially, An inside pole (18) is related with a field of a movable Hall e...
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JP2014240655A |
To provide a system for a floating base for airship having a floating system attached to an object having a structure for flight.There are provided magnetic members and powder permendur. These products most efficiently generate strong ma...
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JP2014234816A |
To provide a lift generation device which is available out of the atmosphere, does not waste huge energy and eliminates considerable noise.Around a rotor 6, a partition plate 12 is disposed radially, and a liquid is injected by applying ...
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JP2014530144A |
An adapter (3) which collaborates with at least one system which is related with a promotion bay (1) which had planned to be conveyed temporarily at least, and was temporarily carried in a bay (1) at least with a space launch rocket (2) ...
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JP2014529036A |
The 1st stood [still] type plasma thruster (111A) in which an electric propulsion system has the 1st negative pole (140A), the 1st anode (125A), and the 1st gas manifold, It has the 2nd negative pole (140B), the 2nd anode (125B), and the...
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JP5615565B2 |
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JP2014194220A |
To provide a thruster having a good ejection speed and versatility, being easily to be produced and lightweight as well as resistant to failures.A thruster 1 has a main chamber 6 defined within a tube 2. The tube has a longitudinal axis ...
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JP2014173534A |
To provide a microwave power source starting power-up circuit capable of increasing a microwave output at the time of starting a small-sized low power consumption ion engine, ionizing or plasma forming through a positive ignition, decrea...
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JP5582603B2 |
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JP2014519573A |
A hole thruster is at least 1 tank (101) for high pressure gas, A pressure regulation machine (103), a gas flow control device (105), and an ionization course, It has the negative pole (40A, 40B) arranged near the output mouth from an io...
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JP2014519148A |
A long and slender substantially nonconducing pipe which has the 2nd end that is the 1st end and an exhaust port for receiving supply of injection gas, It is the 1st, 2nd, and 3rd electrodes with which the perimeter of a pipe is surround...
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JP2014141108A |
To provide an orbit plane control method for a satellite, capable of achieving orbit control substantially equivalent to control by such a satellite as having a thruster with a high thrust force level, while reducing the size and weight ...
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JP2014141886A |
To provide a method and a system to supply gas for ion engine plasma ignition capable of reliably igniting a propellant and generating plasma thereof even for a compact ion engine.A method to supply gas for ion engine plasma ignition per...
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JP5561901B2 |
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JP5558376B2 |
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JP2014514482A |
It is related with a control system for controlling operation of a plurality of micro thrusters arranged at a plurality of parallel level lines and perpendicular sequences. A plurality of 1st power source lines that this control system w...
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JP2014111439A |
To provide a method and an apparatus for performing propulsion operations using electric propulsion systems.An apparatus 100 comprises: a frame; a power supply unit 104 coupled to the frame; and a payload 106 coupled to the frame and rec...
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JP2014101881A |
To provide a gridded ion propulsion system comprising two power controllers, four ion thrusters, and two switch assemblies.One switch assembly RSA A is connected to the two power controllers XPC1, XPC2 and to two thrusters 1, 2 of the fo...
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JP5510830B2 |
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JP2014511966A |
[Subject] A system and a method of electromagnetism promotion. [Means for Solution] An electromagnetism thrust system is an axis asymmetrical resonance cavity including the inside surface of conductivity, a resonance cavity is suitable f...
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JP2014080938A |
To realize generally space structures (such as space elevators and the like) in which special spaceships and their types of (connected/permanent air flow circulation type) power units solely not requiring (any disposable expensive) rocke...
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JP5478633B2 |
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JP5449166B2 |
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JP5439393B2 |
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JP5425081B2 |
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JP5417643B2 |
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JP2014005762A |
To provide a power supply device capable of stably controlling discharge vibration even when a stable control region of an ion accelerator is shifted with time.A power supply device 100 controls an ion accelerator 10 which includes an an...
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JP2014005799A |
To provide an ion beam generator capable of making and neutralizing plasma by using only one electron source disposed outside of a discharge chamber.The ion beam generator capable of being operated only by one electron source is provided...
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JP5391490B2 |
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JP5376449B2 |
To provide a hollow cathode for a spacecraft, facilitating starting (ignition) of discharge. Members have distal ends opposed to a keeper electrode plate 6. The distal ends have a nanocarbon fine projection group structure, a fine projec...
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JP5357879B2 |
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...
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JP2013222578A |
To provide a power supply device capable of stably controlling discharge oscillation even when a stable control region of an ion accelerator changes with lapse of time.A power supply device controls an ion accelerator comprising an anode...
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JP2013213471A |
To move ahead by means of internal force only without need of depending on its surrounding environment.When a weighted object 2 having weight is pulled in a direction B so that the weighted object 2 approaches a rotating body center 5, t...
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JP2013536356A |
An electric thruster includes at least one electric engine, a feed system for the engine including a high-pressure tank of ionizable gas, a low-pressure buffer tank connected to the high-pressure tank by a valve, and a system of pipes fo...
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JP5295423B2 |
In a Hall thruster 10, an acceleration channel 12 ionizes propellant flowing into an annular discharge space 11 to generate ions, and accelerates and discharges the generated ions. A distributor 37 supplies propellant from a plurality of...
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JP2013174204A |
To provide a pulse type propelling machine unit capable of operating while maintaining a high propelling efficiency for a long period of time.A pulse type propelling machine unit has an electric discharge chamber formed from an upstream ...
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JP2013531755A |
An electric discharge channel (50) in which the present invention has the lower stream side open end part (52), A cathode (100) arranged to the exterior of an electric discharge channel (50), It is related with a Hall effect motor (1) pr...
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JP2013137024A |
To provide a space thruster with which energy transfer becomes more efficient.A thruster 1 has a main chamber 6 defined within a tube 2. The tube has a longitudinal axis which defines an axis of thrust. An injector 8 injects ionizable ga...
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JPWO2011108060A |
By hole thruster 10, acceleration channel 12 makes the promotion agent which flows in annular electric discharge space 11 ionize, and it accelerates the ion which generated and generated ion and it emits it. Distributor 37 passes anode 1...
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JPWO2011108060A1 |
By hole thruster 10, acceleration channel 12 makes the promotion agent which flows in annular electric discharge space 11 ionize, and it accelerates the ion which generated and generated ion and it emits it. Distributor 37 passes anode 1...
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JP2013087764A |
To provide a propelling device which is operated only by electricity and magnetic force without requiring propellent, atmosphere, and seawater.Two electrodes for electric discharge are arranged on a surface of the propelling device which...
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JP2013505529A |
An annular discharge channel provided with an opening downstream end which the present invention is a Hall effect plasma thruster, is located in a circumference of a principal-axis line, and is constituted between an inner wall and an ou...
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JP2013504008A |
The solid state device can give direct quantity of motion via a micro element of thermoelectricity. A high surface field is used in order to reinforce the efficiency of heat movement. The device concerned operates in heat insulation mode...
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JP5119514B2 |
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