US3071705A - Electrostatic propulsion means - Google Patents

Electrostatic propulsion means Download PDF

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US3071705A
US3071705A US76566158A US3071705A US 3071705 A US3071705 A US 3071705A US 76566158 A US76566158 A US 76566158A US 3071705 A US3071705 A US 3071705A
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means
toroid
ionizing
electrostatic
force
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William J Coleman
Santo Daniel F De
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Grumman Corp
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Grumman Corp
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    • FMECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F03MACHINES OR ENGINES FOR LIQUIDS; WIND, SPRING WEIGHT AND MISCELLANEOUS MOTORS; PRODUCING MECHANICAL POWER; OR A REACTIVE PROPULSIVE THRUST, NOT OTHERWISE PROVIDED FOR
    • F03HPRODUCING A REACTIVE PROPULSIVE THRUST, NOT OTHERWISE PROVIDED FOR
    • F03H1/00Using plasma to produce a reactive propulsive thrust

Description

3 1 F; v 3. 8 S 12213 3 0T1.9?05

Jan. 1, 1963 w. J. COLEMAN ETAL 3,07

ELECTROSTATIC PROPULSION MEANS Filed O ct. 6. 1958 2 Sheets-Sheet 1 Lines of electrostatic force INVENTORS. w AM .co AN 0 EL es 0 ATTORNEY Jan. 1, 1963 w. J. COLEMAN ETAL 3,071,705

' ELECTROSTATIC PROPULSION MEANS Filed Oct. 6. 1958 2 Sheets-Sheet 2 J age O-- Source FIG. 4

h :3 V0743 FIG. 2

Source IN V EN TORS.

WILLIAM J.COLEMAN DANIEL F. DESANTO ATTORNEY United States Patent 3,071,705 ELECTROSTATIC PROPULSION MEANS William J. Coleman, Port Jelferson, and Daniel F, De

'Santo, Huntington Station, N.Y., assignors to Grum- -n1an Aircraft Engineering Corporation, Eethpagc,

N.Y., a corporation of New York Filed Oct. 6, 1958, Ser. No. 765,661

12 Claims. (Cl. 313-63) This invention relates to electrostatic propulsion means, and more particularly to means for propelling air and other fluids by electrostatic forces acting upon such fluids and for propelling devices through air and other fluids by such forces.

It is well known that if an electrically-charged conducting surface has a relatively sharp point, a large part of the charge will concentrate in the neighborhood of the point, thus producing a high electrostatic stress in the air surrounding the point. Free electrons present in this region of air will be accelerated so strongly by the elsctrostatic force that by collision with neutral gas molecules they will strip or knock loose other electrons from those molecules. Thus, electron-positive ion pairs will be created and the cumulative collision process known as corona will result. Further, if the pointed conductor is positively charged, the positive ions present in the corona discharge will move away from the point because of mutual electrostatic repulsion, while the negative electrons will be attracted to the conductor. Neutral molecules will be struck by the repelled positive ions and momentum will be transferred from the ions to the air mass in the vicinity of the point, thereby generating a flow of air. This flow of air, or socalled electric wind, will be in directions radially outward from the point of the positively charged conductor and therefore of little or no use as propulsion means. In order to provide a useful and efficient device, the flow of air must be concentrated in one direction.

Accordingly, it is the primary object of this invention to provide in the vicinity of the ionization point of a corona discharge device of other ionization means, an electrostatic field whose lines of force are concentrated along a desired flow axis originating at the ionization point whereby practically all of the ions produced, along with entrained neutral molecules, will flow in the desired direction. Further thereto, it is an object to provide in the vicinity of such ionization means, a conducting surface electrically energized and so shaped in cross-section as to produce an electrostatic field in the desired direction.

It is a further object to provide means downstream of the ionization point to further restrict the electrostatic field to a downstream direction. Further thereto, it is an object to provide a conducting surface or surfaces a variable distance downstream of the ionization point to establish an end point for the lines of force emanating from the electrically energized conducting surface and ionization point, thereby preventing the electrostatic field from diverging while allowing substantially unimpeded airflow.

It is a still further object to provide downstream of the ionization point, electrostatic field or fields having lines of force substantially parallel and in the downstream direction to confine the airflow in the desired downstream direction.

Other objects of the invention, as Well as the advantages thereof will become apparent from the following description when read in conjunction with the accompanying drawings in which:

FIG. 1 is a cross-sectional view schematically illustrating one embodiment of the invention;

FIG. 2 is a cross-sectional view schematically illustrating another embodiment of the invention;

3,071,705 Patented Jan. 1, 1963 FIG. 3 is a perspective view of still another embodiment; and

FIG. 4 is a cross-sectional view of the device of FIG. 3 provided with additional means for preventing the electrostatic field from diverging.

As shown in FIG. 1, the device of the present invention comprises an ionization head 10 threadedly mounted for longitudinal adjustment upon one end of a C-shaped bracket or connector 11, which in turn is fixedly attached to a toroid 12 whose axis coincides with that of the head 10. A suitable high voltage D.C. source 13 has one terminal connected to the toroid 12 and another terminal connected to ground.

It is characteristic of electrostatic lines of force that they concentrate in those places on the surface of a conductor where the radius of curvature is the least; that they are normal to the surface from which they emanate; and that such lines of force do not cross one another, but when influenced by such lines emanating from another body, will cause one another to bend and thereby change direction. With this in mind, it will be noted that the crosssection of the toroid 12 is such that the lines of force emanating therefrom upon the application of a positive charge from the voltage source 13 would be concentrated in the direction of the arrow A. However, because such lines of force and those emanating from the ionization head 10 will not cross one another, the lines of force emanating from the toroid are bent outwardly while the lines of force emanating from the ionization head 10 are bent inwardly or compressed to thereby take a desired downstream direction as shown by the arrows on'the ends thereof. Since the positive ions in the vicinity of the positively charged ionization head 10 are-repelled from the head and travel along the lines of force, and since momentum will be transferred from the ions to the air mass, a flow of air is generated in the direction of the flow arrow. The air, as it moves to the right, is replenished by an inflow of air through the toroid, thereby ensuring continuous operation of the device.

As previously indicated, the head 10 is mounted for longitudinal adjustment. Thus the head may be positioned with respect to the toroid 12 to vary the resulting airflow and to permit the optimum placement thereof to obtain the greatest airflow possible under different operating conditions.

As shown in FIG. 2, means for ionizing the air comprise a heating element 14 positioned on the axis of the toroid 12 and supplied with an electric current from a source 15. The high voltage D.C. source 13 is connected to the toroid 12, which in turn is connected by means of a conductor 16 to the negative side of the source 15. The operation of the device shown in FIG. 2 is similar to that of the FIG. 1 device and further explanation is therefore deemed unnecessary.

Referring now to FIG. 3, there is shown a device which utilizes an ionization head 10 and toroid 12 similar to those shown in FIG. 1, and provided with means downstream thereof to establish an end point for the lines of force emanating from the ionization head and the toroid. Such means comprise a streamline-shaped metal target 17 connected to and supporting a metal ring 18. As shown, the positive terminal of the high voltage source 13 is connected to the toroid 12, while the negative terminal thereof is connected to the target 17. The target 17 and ring 18 connected thereto thereby become sources of electrons which neutralize all of the ions striking the surfaces of the target and ring. Since substantially all of the ions repelled by the head 10 will strike either the target 17 or the ring 18, a closed circuit is thereby established which permits operation of the device with no appreciable net accumulation of charge.

The ionization head 10 is mounted upon the connector 11 for longitudinal adjustment as in FIG. 1, and is provided with a plurality of needle points 19 which are symmetrically spaced in rows around the head and which are given a positive charge from the source 13 so as to secure positive ion flow. The longitudinal adjustment of the ionization head permits the optimum placement of the head with respect to the toroid, as indicated hereinabove with reference to FIG. 1, while additional control means may comprise provision for varying the distance between the toroid and the downstream metal ring and target.

In the arrangement shown in FIG. 4, a series of metal rings 20-22, each charged to a DC. potential, are positioned between the toroid 12 and the downstream ring 18. As shown, the rings 20-22 are connected through resistors 23-26 to each other and to the toroid 12 and the ring 18. The resistors are preferably so selected to provide a linear potential gradient between the toroid 12 and the grounded ring 18 whereby a constant strength electrostatic field between the toroid 12 and the ring 18 is obtained. The advantage in so selecting the resistors and thus obtaining such electrostatic field is that the repelled ions will fall through equal potential increments between collisions with molecules, regardless of their downstream position, and each ion will therefore gain equal increments of kinetis energy between collisions. Thus, the energy transfer from the ions to neutral molecules will be evenly spread over the entire volume between the ionization point and the ring 18 and target 17. A further and possibly greater advantage is that a constant strength electrostatic field consists of parallel electrostatic lines of force in the downstream direction, thereby providing further means for maintaining the ion flow in the desired downstream direction.

From the foregoing, it will be apparent that the invention provides highly effective apparatus for propelling fluid mediums such as air. By the ionization of molecules and the concentrating of electrostatic lines of force along and in the direction of a desired flow axis, the ions so produced are caused to move in the desired direction. Momentum is transferred from the moving ions to the fluid mass, thus creating the desired fluid flow.

Although shown and described in what is believed to be the most practical and preferred embodiments, it is apparent that departures therefrom will suggest themselves to those skilled in the art and may be made without departing from the spirit and scope of the invention. We therefore do not wish to restrict ourselves to the particular forms of construction illustrated and described, but desire to avail ourselves of all modifications that may fall within the scope of the appended claims.

Having thus described our invention, what we claim is:

1. An electrostatic propulsion device comprising means for ionizing a fluid, an electrically energized conducting surface positioned relative to said ionizing means and adapted to produce an electrostatic field whose lines of force concentrate along an axis subtsantially passing through said ionizing means, those lines of force emanating from said ionizing means, a plurality of conducting surfaces spaced from each other and downstream from said electrically energized conducting surface, a connector between said electrically energized conducting surface and that conducting surface of said plurality of conducting surfaces nearest thereto, connectors between adjacent conducting surfaces of said plurality of conducting surfaces, and a connection to ground from that conducting surface of said plurality of conducting surfaces most remote from said electrically energized conducting surface, said connectors including means to provide a linear potential gradient between said electrically energized conducting surface and said grounded conducting surface.

2. A device as set forth in claim 1 wherein said electrically energized conducting surface is a toroid having its axis coincident with that of said ionizing means.

3. A device as set forth in claim 1 wherein said plurality of conducting surfaces comprise metal rings whose axes are coincident with that of said ionizing means.

4. An electrostatic propulsion device comprising means for ionizing a fluid in the vicinity of a point, a toroid up stream of said point and surrounding said means and having its axis coincident with that of said means, means for electrically energizing said toroid, said toroid being adapted to produce upon energization an electrostatic field whose lines of force concentrate about said axis and in the downstream direction thereof, those lines of force emanating from said ionizing means, a plurality of metal rings spaced from each other and downstream from said toroid and having their axes coincident with the axis of said toroid, a connector between said toroid and the ring nearest thereto, connectors between adjacent rings, and a connection to ground from that ring most remote from said toroid, said connectors including means to provide a linear potential gradient between said toroid and said grounded ring.

5. A device as set forth in claim 4 and including a grounded conducting surface positioned on the axis of and in the plane of the ring most remote from said toroid.

6. An electrostatic propulsion device comprising means for ionizing a fluid in the vicinity of a point, and conducting surface upstream of said point, a source of electric potential connected to said conducting surface, said'conducting surface being adapted to produce an electrostatic field whose lines of force concentrate along an axis substantially passing through said ionizing means those lines of force emanating from said ionizing means, target means spaced downstream from said conducting surface to establish an end point for said electrostatic lines of force, and means connecting said target means to the negative side of said source of electric potential.

7. An electrostatic propulsion device comprising means for ionizing a fiuid in the vicinity of a point, a toroid upstream of said point and surrounding said means and having its axis coincident with that of said means, a source of electric potential connected to said toroid, said toroid being adapted to produce upon energization an electrostatic tield whose lines of force concentrate about said axis and in the direction thereof those lines of force emanating from said ionizing means, target means spaced downstream from said toroid to establish an end point for said electrostatic lines of force, and means connecting said target means to the negative side of said source of electric potential.

8. An electrostatic propulsion device comprising means for ionizing a fluid in the vicinity of a point, a toroid upstream of said point and surrounding said means and having its axis coincident with that of said means, means for electrically energizing said toroid, said toroid producing upon energization an electrostatic field whose lines of force concentrate about said axis and in the direction thereof those lines of force emanating from said ionizing means, a plurality of metal rings spaced from each other and downstream from said toroid and having their axes coincident with the axis of said toroid, a connector between said toroid and the ring nearest thereto, connectors between adjacent rings, and means connecting that ring most remote from said toroid to the negative terminal of said electrical energizing means, said connectors including means to provide a potential gradient between said toroid and that ring connected to said negative terminal.

9. An electrostatic propulsion device comprising means for ionizing a fluid in the vicinity of a point, a toroid upstream of said point and surrounding said means and having its axis coinciding with that of said means, means for electrically energizing said toroid, said toroid being adapted to produce upon energization an electrostatic field whose lines of force concentrate about said axis and in the downstream direction thereof those lines of force emanating from said ionizing means, a plurality of metal rings spaced from each other and downstream from said toroid and having their axes coincident with that of said toroid, a connector between said toroid and the ring nearest thereto, and connectors between adjacent rings, said connectors including means to provide a linear potential gradient between said toroid and the ring most remote therefrom.

to. An electrostatic propulsion device comprising means for ionizing a fluid in the vicinity of a point, means positioned relative to said ionizing means for creating an electrostatic field whose lines of force concentrate about an axis those lines of force emanating from said ionizing means, a plurality of conducting surfaces spaced one from another and downstream from said ionizing means and said electrostatic field creating means, connectors between adjacent conducting surfaces, and means for electrically energizing said conducting surfaces, said connectors including means to provide a linear potential gradient between said conducting surfaces.

1 1. An electrostatic propulsion device comprising means for ionizing a fluid in the vicinity of a point, means positioned relative to said ionizing means for creating an electrostatic field whose lines of force concentrate about an axis those lines of force emanating from said ionizing means, a plurality of rings spaced from each other and downstream from said ionizing means and said electrostatic field creating means and having their axes coincident with that of said ionizing means, connectors between adjacent rings, and means for electrically energizing said 5 rings, said connectors including means to provide a'linear potential gradient between said rings when energized by said energizing means.

12. A device as set forth in claim 9 wherein the ring most remote from said toroid is connected to ground.

References Cited in the file of this patent UNITED STATES PATENTS 1,357,466 Moller Nov. 2, 1920 15 2,264,495 Wilner Dec. 2, 1941 2,460,175 Hergenrother Jan. 25, 1949 2,636,664 Hertzler April 28, 1953 2,658,009 Ransburg Nov. 3, 1953 2,765,975 Lindenblad Oct. 9, 1956 20 2,809,314 Herb Oct. 8, 1957.

FOREIGN PATENTS 262,829 Great Britain Feb. 16, 1928

Claims (1)

1. AN ELECTROSTATIC PROPULSION DEVICE COMPRISING MEANS FOR IONIZING A FLUID, AN ELECTRICALLY ENERGIZED CONDUCTING SURFACE POSITIONED RELATIVE TO SAID IONIZING MEANS AND ADAPTED TO PRODUCE AN ELECTROSTATIC FIELD WHOSE LINES OF FORCE CONCENTRATE ALONG AN AXIS SUBSTANTIALLY PASSING THROUGH SAID IONIZING MEANS, THOSE LINES OF FORCE EMANATING FROM SAID IONIZING MEANS, A PLURALITY OF CONDUCTING SURFACES SPACED FROM EACH OTHER AND DOWNSTREAM FROM SAID ELECTRICALLY ENERGIZED CONDUCTING SURFACE, A CONNECTOR BETWEEN SAID ELECTRICALLY ENERGIZED CONDCTING SURFACE AND
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Cited By (31)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3119233A (en) * 1962-01-18 1964-01-28 Frank L Wattendorf Multiple electrode arrangement for producing a diffused electrical discharge
US3267860A (en) * 1964-12-31 1966-08-23 Martin M Decker Electrohydrodynamic fluid pump
US3322374A (en) * 1964-09-30 1967-05-30 Jr James F King Magnetohydrodynamic propulsion apparatus
US3398685A (en) * 1961-09-11 1968-08-27 Litton Systems Inc Ion drag pumps
US3418500A (en) * 1965-05-18 1968-12-24 Bahnson Co Rotating field electrostatic apparatus
US3459205A (en) * 1965-06-28 1969-08-05 Electro Optical Systems Inc Magnetically controlled fluid amplifier
US3464207A (en) * 1966-10-10 1969-09-02 American Standard Inc Quasi-corona-aerodynamic vehicle
US3469401A (en) * 1967-11-08 1969-09-30 Us Navy Magnetic colloid propulsor
US3584976A (en) * 1968-11-18 1971-06-15 Donald H Schuster Paramagnetic oxygen pump
US3638058A (en) * 1970-06-08 1972-01-25 Robert S Fritzius Ion wind generator
US3938345A (en) * 1973-10-06 1976-02-17 Agency Of Industrial Science & Technology Cooling method by use of corona discharge
FR2364388A1 (en) * 1976-09-14 1978-04-07 Fimml Hans Piston machine with non-contact seal
EP0260995A2 (en) * 1986-09-19 1988-03-23 University Of Surrey Particulate material flow control and apparatus therefor
US6145298A (en) * 1997-05-06 2000-11-14 Sky Station International, Inc. Atmospheric fueled ion engine
WO2002009259A1 (en) * 2000-07-21 2002-01-31 Tomion Mark R Electrodynamic field generator
US20030046921A1 (en) * 2001-06-21 2003-03-13 Vlad Hruby Air breathing electrically powered hall effect thruster
US20030090209A1 (en) * 1998-10-16 2003-05-15 Krichtafovitch Igor A. Electrostatic fluid accelerator
WO2004046620A2 (en) * 2002-11-14 2004-06-03 Magnetizer Industrial Technologies, Inc. Method and apparatus for enhancing heat pump and refrigeration equipment performance
US20040155612A1 (en) * 2003-01-28 2004-08-12 Krichtafovitch Igor A. Electrostatic fluid accelerator for and method of controlling a fluid flow
US20040183454A1 (en) * 2002-06-21 2004-09-23 Krichtafovitch Igor A. Method of and apparatus for electrostatic fluid acceleration control of a fluid flow
US20040217720A1 (en) * 2002-07-03 2004-11-04 Krichtafovitch Igor A. Electrostatic fluid accelerator for and a method of controlling fluid flow
US20050116166A1 (en) * 2003-12-02 2005-06-02 Krichtafovitch Igor A. Corona discharge electrode and method of operating the same
US20050150384A1 (en) * 2004-01-08 2005-07-14 Krichtafovitch Igor A. Electrostatic air cleaning device
US6937455B2 (en) 2002-07-03 2005-08-30 Kronos Advanced Technologies, Inc. Spark management method and device
US20060226787A1 (en) * 2005-04-04 2006-10-12 Krichtafovitch Igor A Electrostatic fluid accelerator for and method of controlling a fluid flow
US7122070B1 (en) 2002-06-21 2006-10-17 Kronos Advanced Technologies, Inc. Method of and apparatus for electrostatic fluid acceleration control of a fluid flow
US20060283171A1 (en) * 2004-09-03 2006-12-21 Metcalfe Tristram W Iii Charged particle thrust engine
US20090022340A1 (en) * 2006-04-25 2009-01-22 Kronos Advanced Technologies, Inc. Method of Acoustic Wave Generation
US7532451B2 (en) 2002-07-03 2009-05-12 Kronos Advanced Technologies, Inc. Electrostatic fluid acclerator for and a method of controlling fluid flow
DE102014100575A1 (en) * 2014-01-20 2015-07-23 Technische Universität Dresden Actuator system and electro-hydrodynamic actuator
US20150211499A1 (en) * 2012-08-28 2015-07-30 Xavier Morin Electrothermal device for a propulsion system, especially for a turbojet, propulsion system comprising such an electrothermal device, and associated method

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US2658009A (en) * 1948-05-13 1953-11-03 Ransburg Electro Coating Corp Electrostatic coating method and apparatus
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Cited By (51)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3398685A (en) * 1961-09-11 1968-08-27 Litton Systems Inc Ion drag pumps
US3119233A (en) * 1962-01-18 1964-01-28 Frank L Wattendorf Multiple electrode arrangement for producing a diffused electrical discharge
US3322374A (en) * 1964-09-30 1967-05-30 Jr James F King Magnetohydrodynamic propulsion apparatus
US3267860A (en) * 1964-12-31 1966-08-23 Martin M Decker Electrohydrodynamic fluid pump
US3418500A (en) * 1965-05-18 1968-12-24 Bahnson Co Rotating field electrostatic apparatus
US3459205A (en) * 1965-06-28 1969-08-05 Electro Optical Systems Inc Magnetically controlled fluid amplifier
US3464207A (en) * 1966-10-10 1969-09-02 American Standard Inc Quasi-corona-aerodynamic vehicle
US3469401A (en) * 1967-11-08 1969-09-30 Us Navy Magnetic colloid propulsor
US3584976A (en) * 1968-11-18 1971-06-15 Donald H Schuster Paramagnetic oxygen pump
US3638058A (en) * 1970-06-08 1972-01-25 Robert S Fritzius Ion wind generator
US3938345A (en) * 1973-10-06 1976-02-17 Agency Of Industrial Science & Technology Cooling method by use of corona discharge
FR2364388A1 (en) * 1976-09-14 1978-04-07 Fimml Hans Piston machine with non-contact seal
EP0260995A2 (en) * 1986-09-19 1988-03-23 University Of Surrey Particulate material flow control and apparatus therefor
EP0260995A3 (en) * 1986-09-19 1990-02-07 University Of Surrey Particulate material flow control and apparatus therefor
US6145298A (en) * 1997-05-06 2000-11-14 Sky Station International, Inc. Atmospheric fueled ion engine
US20030090209A1 (en) * 1998-10-16 2003-05-15 Krichtafovitch Igor A. Electrostatic fluid accelerator
US6888314B2 (en) 1998-10-16 2005-05-03 Kronos Advanced Technologies, Inc. Electrostatic fluid accelerator
WO2002009259A1 (en) * 2000-07-21 2002-01-31 Tomion Mark R Electrodynamic field generator
US6404089B1 (en) 2000-07-21 2002-06-11 Mark R. Tomion Electrodynamic field generator
US20030046921A1 (en) * 2001-06-21 2003-03-13 Vlad Hruby Air breathing electrically powered hall effect thruster
US6834492B2 (en) * 2001-06-21 2004-12-28 Busek Company, Inc. Air breathing electrically powered hall effect thruster
US7122070B1 (en) 2002-06-21 2006-10-17 Kronos Advanced Technologies, Inc. Method of and apparatus for electrostatic fluid acceleration control of a fluid flow
US20040183454A1 (en) * 2002-06-21 2004-09-23 Krichtafovitch Igor A. Method of and apparatus for electrostatic fluid acceleration control of a fluid flow
US6963479B2 (en) 2002-06-21 2005-11-08 Kronos Advanced Technologies, Inc. Method of and apparatus for electrostatic fluid acceleration control of a fluid flow
US7532451B2 (en) 2002-07-03 2009-05-12 Kronos Advanced Technologies, Inc. Electrostatic fluid acclerator for and a method of controlling fluid flow
US20040217720A1 (en) * 2002-07-03 2004-11-04 Krichtafovitch Igor A. Electrostatic fluid accelerator for and a method of controlling fluid flow
US7262564B2 (en) 2002-07-03 2007-08-28 Kronos Advanced Technologies, Inc. Electrostatic fluid accelerator for and a method of controlling fluid flow
US7594958B2 (en) 2002-07-03 2009-09-29 Kronos Advanced Technologies, Inc. Spark management method and device
US6937455B2 (en) 2002-07-03 2005-08-30 Kronos Advanced Technologies, Inc. Spark management method and device
US20060055343A1 (en) * 2002-07-03 2006-03-16 Krichtafovitch Igor A Spark management method and device
WO2004046620A2 (en) * 2002-11-14 2004-06-03 Magnetizer Industrial Technologies, Inc. Method and apparatus for enhancing heat pump and refrigeration equipment performance
WO2004046620A3 (en) * 2002-11-14 2004-12-16 Ronald J Kita Method and apparatus for enhancing heat pump and refrigeration equipment performance
US6919698B2 (en) 2003-01-28 2005-07-19 Kronos Advanced Technologies, Inc. Electrostatic fluid accelerator for and method of controlling a fluid flow
US20040155612A1 (en) * 2003-01-28 2004-08-12 Krichtafovitch Igor A. Electrostatic fluid accelerator for and method of controlling a fluid flow
US7157704B2 (en) 2003-12-02 2007-01-02 Kronos Advanced Technologies, Inc. Corona discharge electrode and method of operating the same
US20050116166A1 (en) * 2003-12-02 2005-06-02 Krichtafovitch Igor A. Corona discharge electrode and method of operating the same
US20050150384A1 (en) * 2004-01-08 2005-07-14 Krichtafovitch Igor A. Electrostatic air cleaning device
US7150780B2 (en) 2004-01-08 2006-12-19 Kronos Advanced Technology, Inc. Electrostatic air cleaning device
US20080030920A1 (en) * 2004-01-08 2008-02-07 Kronos Advanced Technologies, Inc. Method of operating an electrostatic air cleaning device
US20090288385A1 (en) * 2004-09-03 2009-11-26 Metcalfe Iii Tristram Walker Charged particle thrust engine
US8112982B2 (en) 2004-09-03 2012-02-14 Metcalfe Iii Tristram Walker Charged particle thrust engine
US20060283171A1 (en) * 2004-09-03 2006-12-21 Metcalfe Tristram W Iii Charged particle thrust engine
US7584601B2 (en) 2004-09-03 2009-09-08 Metcalfe Iii Tristram Walker Charged particle thrust engine
US8049426B2 (en) 2005-04-04 2011-11-01 Tessera, Inc. Electrostatic fluid accelerator for controlling a fluid flow
US20060226787A1 (en) * 2005-04-04 2006-10-12 Krichtafovitch Igor A Electrostatic fluid accelerator for and method of controlling a fluid flow
US7410532B2 (en) 2005-04-04 2008-08-12 Krichtafovitch Igor A Method of controlling a fluid flow
US20090047182A1 (en) * 2005-04-04 2009-02-19 Krichtafovitch Igor A Electrostatic Fluid Accelerator for Controlling a Fluid Flow
US20090022340A1 (en) * 2006-04-25 2009-01-22 Kronos Advanced Technologies, Inc. Method of Acoustic Wave Generation
US10047732B2 (en) * 2012-08-28 2018-08-14 Xavier Morin Electrothermal device for a propulsion system, especially for a turbojet, propulsion system comprising such an electrothermal device, and associated method
US20150211499A1 (en) * 2012-08-28 2015-07-30 Xavier Morin Electrothermal device for a propulsion system, especially for a turbojet, propulsion system comprising such an electrothermal device, and associated method
DE102014100575A1 (en) * 2014-01-20 2015-07-23 Technische Universität Dresden Actuator system and electro-hydrodynamic actuator

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