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WO/2005/033498A1 |
The inventive aerospace laser jet engine comprises an optical unit (2) for receiving a repetitively pulsed laser radiation, matching the aperture of a laser beam with the size of said optical unit and for forming a flat radiation front, ...
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WO/2005/033544A2 |
A force generator for an active vibration control (AVC) system provides a mass located upon an inner circular member which is movable within an outer circular member to simultaneously complete one revolution about its axis as it orbits w...
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WO/2005/028310A2 |
A thruster has a chamber (6) defined within a tube (2). The tube has a longitudinal axis which defines an axis (4) of thrust; an injector (8) injects ionizable gas within the tube, at one end of the chamber. A magnetic field generator wi...
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WO/2005/029927A2 |
A pulsed plasma accelerator comprises two electrodes (1) arranged between dielectric bars (2) made from an ablating material, a discharge channel with an open end part whose walls are defined by the surfaces of electrodes (1) and dielect...
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WO/2005/027142A1 |
The invention relates to a method and a device for generating Alfvén waves, in which ionizable material is provided that penetrates a magnetic field. In order to create such a method or a device in which material can be conveyed based o...
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WO/2005/010360A2 |
A modular ion source design relies on relatively short modular anode layer source (ALS) components, which can be coupled together to form a longer ALS (200). For long ion sources, these shorter modular components allow easier manufacturi...
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WO/2005/008066A1 |
In accordance with one embodiment of the present invention, the ion-beam apparatus takes the form of an end-Hall ion source in which the detachable anode module incorporates the outer pole piece and includes an enclosure around the anode...
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WO/2005/003557A1 |
A hybrid electric-laser propulsion (HELP) thruster. A propellant has self-regenerative surface morphology. A laser ablates the propellant to create an ionized exhaust plasma that is non-interfering with a trajectory path of expelled ions...
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WO/2005/002965A1 |
A mobile object being a vehicle of any type includes a plurality of force generators and a plurality of engines. Each force generator (42) is a propulsion mechanism that converts directly a rotational energy of an engine (44) into a self...
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WO/2004/109085A1 |
A thruster (10) for providing thrust for spacecraft positioning, which has a propellant reservoir (12) for storing propellant, a reaction chamber (20) for discharging a vapor for providing thrust, a pump module (14) comprising one or mor...
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WO/2004/107824A2 |
The invention can be used for space engineering in the form of stationary ion engines and for vacuum-plasma technologies. The inventive method for producing propulsive power in an ion engine by generating an oriented accelerated ion beam...
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WO/2004/095473A1 |
A target (30) placed in a vacuum chamber (60) is irradiated with laser beam (L1) that is outputted from a laser beam source (10) while being condensed through a condensation optical system (20). Consequently, high-speed particles (P), e....
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WO/2004/079188A2 |
The invention relates to a structure and a method for a drive device pertaining to a space missile comprising at least one ion accelerator arrangement, whereby a neutralising ion source is consciously rendered superfluous and an ion flow...
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WO/2004/064459A2 |
The invention relates to an ion accelerator arrangement which uses a combination of a magnetic field having a cusp structure and a cross-section of an ionisation chamber that is extended in one direction transversally in relation to the ...
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WO/2004/064461A1 |
Disclosed is an ion accelerator arrangement with a special magnetic field structure in which the magnetic field alternately extends in a mostly longitudinal and transversal direction. The ionization chamber for said ion accelerator arran...
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WO/2004/057643A2 |
The invention relates to a liquid-metal ion source comprising an electro-conductive housing (2) which is preferably made of metal and provided with a hollow space (4) for liquid or fusable metal (3), preferably indium, or a metal alloy. ...
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WO/2004/036011A2 |
This invention relates to actuators having biologically-based components, and methods of making and using the same. The actuator of the invention has a movable member that moves substantially linearly as a result of a biomolecular intera...
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WO/2004/032314A1 |
Apparatus and method for propelling a body by means of the repulsion of two magnetic fields. A fixed electromagnet (1) is attached to a base (5) through a connection column (11). A moveable magnet (2, 19, 18, 16) is forced to the end of ...
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WO/2004/027261A1 |
A propulsion motor for rockets and spaceships comprises two cylindrical rings (17) linked by means of a bar (18) forming the motor external structure (17,18) and an exhaust (13,14,15) linked to a third cylindrical ring (17A) and to a rea...
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WO/2004/025118A2 |
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 ...
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WO/2004/011802A1 |
A method of propelling an object, wherein the object includes a thrust post (6) fixed to the object to be propelled, and a mass (2), and a connecting assembly (4) that freely rotates about the thrust post (6) and which is connected to th...
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WO/2004/007957A2 |
The invention concerns a plasma thruster having a magnetic circuit (40) consisting of a downstream base plate (4) wherefrom project arms (41, 42) characterized in that at least one of the arms (41', 42') comprises a permanent magnet (54,...
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WO/2003/098041A2 |
An air/atmosphere breathing electrically powered Hall effect thruster including a thruster duct having an inlet, an exit, and a discharge zone between the inlet and the exit for receiving air from the inlet into the discharge zone, an el...
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WO/2003/093673A2 |
The large-scale green power (51), water (64) and /or conditioned air (73) can be produced at any climate and loads, using wind, heat and vapor of free air (4, 14, 24) in a compact structured vortex tower (74) giving direct long ac genera...
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WO/2003/082674A1 |
The invention relates to a method of assembling a spacecraft (1), comprising a carrier rocket (2) and at least a first payload (3), such as a satellite or the like, wherein the first payload is placed on the carrier rocket employing an a...
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WO/2003/081965A1 |
The invention relates to gas-discharge high-vacuum devices. Said invention makes it possible to increase the efficiency of electron beam extraction and the gas and energy efficiency. The inventive plasma electron-emitting source comprise...
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WO/2003/050415A1 |
The invention relates to devices producing a reactive force for moving aircraft. The inventive device is embodied in the form of a MHD generator which comprises a toroidal body (1) made of a non-magnetic material whose hermetical cavity ...
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WO/2003/039215A1 |
The invention relates to a multistage plasma accelerator system that comprises at least one intermediate electrode between the plasma chamber between electrodes that include each other. An especially good efficiency can be achieved by wa...
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WO/2003/031931A2 |
An apparatus (18) for forming a stable electrospray of a volatile liquid in a low pressure region (8) includes multi-component capillary jets (34, 35); a plurality of electrodes or grids (20, 23) including at least one emitter electrode ...
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WO/2003/012294A2 |
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WO/2003/007311A1 |
Propellant modules for Micro Pulsed Plasma Thrusters, and techniques for bundling propellant modules (30) and for using a two-stage (36,36') discharge process to increase MicroPPT propellant (18) throughput, and decrease the output volta...
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WO/2003/000550A1 |
The invention relates to various advantageous embodiments of a plasma-accelerator configuration, especially for the configuration and design of electron sources used for ionizing the working gas and/or neutralizing the discharged plasma ...
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WO/2003/001219A2 |
A field ionizing element formed of a membrane (99) that houses electrodes located closer to one another than the mean free path of the gas being ionized. The membrane includes a supporting section (106) and non-supporting section (130).
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WO/2002/101235A2 |
A linear gridless ion thruster (LGIT) is provided to serve as an ion source for spacecraft propulsion or plasma processing. The LGIT is composed of two stages: (1) an ionization stage composed of a hollow cathode, anode, and cusp magneti...
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WO/2002/095225A1 |
The inventive method for producing propulsion in a vacuum consists in redistributing the quantum density of a vacuum field environment inside a working medium in a direction which is opposite with respect to a tractive force vector by de...
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WO/2002/093987A2 |
A closed loop exit aperture is formed in a magnetically permeable end wall (2) of an enclosure (1) of a closed electron drift ion source. Parts of this end wall separated by the exit aperture serve as pole pieces (7 and 8) of the magneti...
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WO/2002/086317A1 |
The invention relates to the use of the collision of matter and antimatter as a means of propulsion in a spacecraft, to the control system for said engine and to a block diagram of the connections for same, in which all of the functions ...
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WO/2002/073218A2 |
A plurality of asymmetrical capacitors (10) that develop power in a propulsion system are disclosed. In one embodiment, the capacitor (10) is constructed so as to have an elongated rearward conductive element (22) to provide a relatively...
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WO/2002/070894A1 |
The frequencies and phases of the currents flowing through conductors (1, 2) arranged in predetermined positions are controlled so as to be predetermined values, and the distance L between the conductors is a predetermined value. With re...
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WO/2002/069364A2 |
In one embodiment of a compact closed-drift ion source, an ionizable gas is introduced into a annular discharge region. An anode is at one end of this region and an electron-emitting cathode is near the opposite and open end. A magnetic ...
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WO/2002/054836A1 |
The invention relates to plasma engineering and can be used for developing plasma closed electron drift accelerators (engines) for space conditions and can be used in other technical branches. The inventive plasma accelerator comprises a...
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WO/2002/046611A1 |
A device for generating linear thrust, the device comprising: a drive element; and a field generator to produce an asymmetric distribution of time-varying electric and magnetic fields around the drive element such that an overall Poyntin...
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WO/2002/037521A2 |
A high current density, low voltage ion source includes a vacuum chamber. A plasma source induces generation of a plasma within the chamber, or injects a plasma directly into the chamber. A magnetic and electric field cooperate to guide ...
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WO/2002/035092A1 |
The invention relates to plasma technology and can be used for developing electric propulsion engines, in particular the engines based on plasma accelerators having a closed electron drift and ion accelerators. The inventive engine compr...
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WO/2002/012722A1 |
This invention called airwheel, concerns of a flying disk shaped flying/space vehicle with the use of a new technic of thrust through the rolling of a wheel. If we exercise a force from a fixed point on the edge of a turning wheel (fixed...
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WO/2002/006120A1 |
A method and apparatus which includes a displacement engine which is capable of moving itself and a payload from one location to another without the expulsion of reaction mass or without applying reaction forces to the external environme...
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WO/2001/094781A1 |
The invention relates to a component for a turbine for generating a directional force. In said turbine, a fluid traverses a sequence of n stages through a pressure differential between the inlet and outlet of the component. Said stages a...
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WO/2001/093293A1 |
A plasma ion source comprises a cathode chamber (1) with a gas input unit (2). A hollow cathode (3) forming an anode chamber (4) is connected with the cathode chamber (1) via the outlet made in the wall of the latter. The ion source stru...
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WO/2001/071185A2 |
The invention relates to a plasma acceleration arrangement comprising a toroidal plasma chamber. According to the invention, a novel structure of the magnetic and/or electric fields is provided. Said structure makes, especially multistep...
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WO/2001/067840A2 |
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