| Document |
Document Title |
|
JP2012219681A |
To provide a space ships exhibiting better propulsion efficiency without requiring rocket fuel and a space structure or the like to which power unit thereof or the like are integrally applied.The system prepares two systems (A system and...
|
|
JP5041526B2 |
|
|
JP2012149617A |
To provide a power supply device which prevents discharge vibration of a Hall thruster and achieves high efficient operation thereof while always stably and properly maintaining characteristics of the Hall thruster for a long period of t...
|
|
JP2012149618A |
To provide a power supply device which reduces influences of a residual magnetic field of an electromagnet as much as possible and always stably ignites and starts the Hall thruster.The power supply device includes: coil power supplies 6...
|
|
JP2012137082A |
To provide a propulsion force generating device for generating floatation force of dead weight or more in a stationary object, without using a combustion system and air resistance.A revolving shaft and a rotating plate 1 are set in the o...
|
|
JP4977459B2 |
|
|
JP4969019B2 |
|
|
JP2012113967A |
To provide a charge neutralization apparatus capable of remarkably improving efficiency by suppressing divergence of ion beams in an ion beam source device.The ion beam source device extracts ions from a plasma source in a plasma source ...
|
|
JP4925132B2 |
|
|
JP4917801B2 |
|
|
JP2012508840A |
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 inc...
|
|
JP2012072754A |
To provide an aerospace engine substantially emitting no exhaust gas and generating noise only at a substantially silent level, without requiring a runway because of its vertical lift capability.When a main rotor having a plurality of el...
|
|
JP4902926B2 |
|
|
JP2011529612A |
A neutral particle generator is disclosed that includes a container which holds a material in at least a partial plasma state, for example a Deuterium plasma. In one form, a first cathode is positioned within the container and produces a...
|
|
JP4831681B2 |
|
|
JP2011238385A |
To provide an extensively controllable surface plasma actuator consisting of surface plasma-induced flow which can be controlled, in direction and velocity, by controlling an applied voltage.Used as an actuator is an induced flow which i...
|
|
JP4816004B2 |
|
|
JP4816170B2 |
|
|
JP4816179B2 |
|
|
JP2011220318A |
To solve a problem wherein a propelling principal and a propelling device available in space, atmosphere, and underwater and attaining propelling force by means of electricity and magnetic force are scarcely existed until now.Electrodes ...
|
|
JP2011208567A |
To provide a moving body that utilizes a movement method for pushing at right angle a center of gravity of a rotating body to move it by an action and reaction at right angle, since the method exists.A movement becomes practicable regard...
|
|
JP2011202650A |
To provide technology (referred to as "atmospheric pressure propulsion") using the wave nature of air molecules for collapsing the isotropy of atmospheric pressure to produce propulsive force, while reducing the effects of weakening the ...
|
|
JP4741245B2 |
|
|
JP2011144699A |
To obtain an electric power supply device inhibiting the occurrence of a discharge vibration phenomenon and stably operating a Hall thruster working as an ion accelerator even when the distribution of a magnetic flux density in a channel...
|
|
JP2011522357A |
A plasma generator having a housing surrounding an ionization chamber, at least one working-fluid supply line leading into the ionization chamber, the ionization chamber having at least one outlet opening, at least one electric coil arra...
|
|
JP4734274B2 |
|
|
JP2011521163A |
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...
|
|
JP4729947B2 |
|
|
JP4729577B2 |
|
|
JP4723576B2 |
|
|
JP4697460B2 |
|
|
JP2011085121A |
To provide a propulsion unit capable of obtaining the propulsive force by canceling the reaction using the centrifugal force since the action and the reaction are generated when obtaining the propulsive force by a propeller, and the reac...
|
|
JP2011074887A |
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 project...
|
|
JP4669219B2 |
|
|
JP2011058398A |
To provide a super-conductive magnet device for space which can cool a superconducting coil to a sufficient temperature region not higher than superconducting transition temperature and can easily secure long term service life, and a pro...
|
|
JP4650136B2 |
|
|
JP4650258B2 |
|
|
JP2011043159A |
To provide a machine which floats and proceeds using a centrifugal force obtained by rotating a weight having a mass by a plurality of rotating bodies.To an end of a rotating body A is attached with a rotating body B. To an end of the ro...
|
|
JP4630439B2 |
|
|
JP4616126B2 |
|
|
JP2010539373A |
The invention relates to an ion accelerator arrangement comprising an electrostatic acceleration field between a cathode to which a frame potential is applied and an anode to which a high-voltage potential is applied. The ion accelerator...
|
|
JP2010539374A |
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 ...
|
|
JP2010539377A |
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...
|
|
JP2010539376A |
An arrangement with radiation cooling of the anode, which avoids the need for complex additional cooling measures, is proposed for an electrostatic ion accelerator arrangement in which the thermal power loss which is not negligible occur...
|
|
JP2010539375A |
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...
|
|
JP2010275929A |
To provide a laser propulsion system achieving high specific thrust rocket engine without limit in combustion chamber temperature, pressure, and space charge density, achieving variability of thrust and specific thrust, and enabling free...
|
|
JP4593919B2 |
|
|
JP4549854B2 |
|
|
JP2010174894A |
To provide a high-output sealed electronic drift thruster for minimizing the mass of a winding by forming a uniform radial magnetic field in a main channel.The sealed electronic drift thruster includes a magnetic circuit for producing a ...
|
|
JP2010164041A |
To provide an ion rocket which can fly in the atmosphere although a conventional ion rocket has been used in a vacuum. The atmosphere flying ion rocket is allowed to be used in the atmosphere by ionizing air with high voltage. Besides, i...
|
