US3662554A - Electromagnetic propulsion device for use in the forward part of a moving body - Google Patents

Electromagnetic propulsion device for use in the forward part of a moving body Download PDF

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US3662554A
US3662554A US32066A US3662554DA US3662554A US 3662554 A US3662554 A US 3662554A US 32066 A US32066 A US 32066A US 3662554D A US3662554D A US 3662554DA US 3662554 A US3662554 A US 3662554A
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fluid
magnetic field
electrodes
propulsion device
electromagnetic
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Axel De Broqueville
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    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B63—SHIPS OR OTHER WATERBORNE VESSELS; RELATED EQUIPMENT
    • B63B—SHIPS OR OTHER WATERBORNE VESSELS; EQUIPMENT FOR SHIPPING 
    • B63B1/00—Hydrodynamic or hydrostatic features of hulls or of hydrofoils
    • B63B1/32—Other means for varying the inherent hydrodynamic characteristics of hulls
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B63—SHIPS OR OTHER WATERBORNE VESSELS; RELATED EQUIPMENT
    • B63H—MARINE PROPULSION OR STEERING
    • B63H11/00—Marine propulsion by water jets
    • B63H11/02—Marine propulsion by water jets the propulsive medium being ambient water
    • B63H11/025—Marine propulsion by water jets the propulsive medium being ambient water by means of magneto-hydro-dynamic forces
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F03—MACHINES OR ENGINES FOR LIQUIDS; WIND, SPRING, OR WEIGHT MOTORS; PRODUCING MECHANICAL POWER OR A REACTIVE PROPULSIVE THRUST, NOT OTHERWISE PROVIDED FOR
    • F03H—PRODUCING A REACTIVE PROPULSIVE THRUST, NOT OTHERWISE PROVIDED FOR
    • F03H1/00—Using plasma to produce a reactive propulsive thrust
    • Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
    • Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
    • Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
    • Y02T70/00—Maritime or waterways transport
    • Y02T70/10—Measures concerning design or construction of watercraft hulls

Definitions

  • the present invention relates to an electromagnetic propulsion device intended to be used in the forward part of a moving body and which creates in the surrounding flow medium, or fluid (such as air or water) an electromagnetic force field accelerating the fluid backward and expanding it aside from the body. Overpressure generated by the body motion in the fluid is reduced or suppressed. In case of a supersonic motion, the shock wave generated by that overpressure in front of the body can be minimized or suppressed.
  • Electrostatic devices have been studied in connection with the reduction of the sonic boom in front of a supersonic vehicle, but their action is essentially based on a progressive deceleration of surrounding flow and not its acceleration. For that reason their effect is unstable and furthemiore they have the very poor efficiency of any electrostatic device in the atmosphere.
  • Electro-magnetic propulsion devices having, some similarity with a Hall radial accelerator (as described in the report NASA TN D-3332, Mar. 1966) were suggested. The action of the latter is inside the vehicle and the fluid is not expanded but compressed by the Hall effect, and therefore it cannot suppress a shock wave.
  • the invention provides an electromagnetic propulsion device intended to be mounted in the forward part of a moving body, comprising an electromagnetic coil for generating a magnetic field around said body, the symmetry axis of said magnetic field having substantially the same direction as the relative motion between the body and the surrounding fluid, at least two annular electrodes placed on the outside dielectric surface of said body perpendicularly to the symmetry axis of said magnetic field, one of said electrodes being mounted at the forward end of said body, ionization means for the said fluid between said electrodes around said body, and a power generator having its terminals connected to said electrodes for generating between same an electric field and an electric current in the ionized fluid around said body, the action of said electric current in said magnetic field causing said fluid to rotate such as to produce a centrifugal force while at the same time the electric current due to the Hall effect produces an additional force effective to accelerate the ionized fluid backward and aside from the said body, thereby to increase the centrifugal force and produce a propulsion
  • this propulsion device does not only push the fluid aside from the body by centrifugal and Hall efiects, but that it also accelerates the fluid backward (and does not decelerate the fluid forward as in other magnetic or electrostatic devices) such as to produce a propulsion efi'ect simultaneously with a reduction of the drag due to the overpressure generated by the body motion relative to the fluid.
  • the fluid can be pushed aside from the body by the electromagnetic forces (and not by a pressure gradient as in ordinary flow) without or with a reduced increase of pressure such that the fluid is actually expanded aside from the body.
  • the shock wave is only generated by compression flow, such a propulsion device also reduces drag and can suppress the shock wave generated in front of a supersonic body.
  • FIG. 1 is a schematic elevational view of a body nose incorporating a particular embodiment of the electromagnetic propulsion device according to the invention
  • FIG. 2 is a horizontal view of the body of FIG. 1;
  • FIGS. 3, 4 through 8 show schematically in vertical projection (FIGS. 3, 5 and 7) and in horizontal projection (FIGS. 4, 6 and 8) the magnetic field configurations, the electric current lines and the resulting forces;
  • FIG. 9 is an elevational view of a body nose incorporating a variant of the propulsion device according to the invention.
  • FIG. 10 illustrates an ionization device according to the invention.
  • FIGS. 1 and 2 show (in elevational and horizontal view respectively) the forward part of a body 1 which may be the nose of an aircraft having a general axial symmetry aboutlom gitudinal axis 2.
  • the propulsion device according to the invention is used for the aircraft propulsion or as an assist part of the aircraft propulsion system together with conventional propulsion devices, and acting at the same time to reduce or suppress the front shock wave, thereby to reduce drag and noise. It may also be used for the aircraft deceleration by inverting the force field as will be seen hereinafter.
  • the electromagnetic coil 5 generates a magnetic field having a symmetry axis that is illustratively coinciding with the aircraft axis 2.
  • the field is a poloidal magnetic field, in contrast to a toroidal magnetic field.
  • a toroidal magnetic field is a magnetic field which can be represented in cylindrical coordinates by the equation:
  • a poloidal magnetic field is a magnetic field which is not toroidal or whose magnetic lines of force are perpendicular to those of a toroidal magnetic field.
  • Such a magnetic field is general and it can be represented in cylindrical coordinates by the equation: a
  • Toroidal coils which produce approximately force-free magnetic fields are used. They provide a toroidal magnetic field inside a torus (including the coils) and a poloidaP magnetic field outside the torus. The magnetic stresses of the toroidal magnetic field are opposite to the stresses of the poloidal magnetic field. Therefore the resulting stresses on the coils are strongly reduced or balanced.
  • the poloidal magnetic fields are the most common magnetic fields, but the term poloidal" has been introduced considering that only the poloidal component of the magnetic field would be outside the vehicle and consequently the only active component.
  • This field is represented by vector H and has field lines 50 that go through the body envelope and have in the surrounding space a configuration as shown in FIGS.
  • the coil itself can advantageously be made of superconductors disposed inside a torus 5 (e.g. cooled by liquid Helium), the disposition of the conductors being such that the magnetic field approaches a force free or balanced" state, thereby reducing the magnetic stresses in the coil such that a dimensionally large (i.e.
  • edge may be blunt or pointed and the shape of the electrode thereat can then be considered as the limit of the ring.
  • the power generator symbolized by box 6 is connected to the electrodes by the connections 7 and 8 with the appropriate polarityJt may comprise any current generator such as a dynamo driven by a gas turbine, etc. It can also advantageously use the magnetic field inside the vehicle and the necessary energy can be found in the magnetic field itself which then would serve as an energy source.
  • Means for ionizing the surrounding fluid may comprise any device such as a particle emitter, a high frequency electromagnetic field generator, etc.
  • the ionization is assumed to be initiated by means (not shown) such as a spark generator, a device for applying an instantaneous high voltage between the electrodes, etc.
  • the ionization is assumed to be maintained by the electric field generated by said power generator.
  • the power generator would produce a glow discharge (which must be close to an arc discharge at the atmospheric pressure). It is favored by the annular configuration and the transverse magnetic field such that it has a good efficiency with a small electrode corrosion.
  • the expanding and centrifugal forces reduce heat transfer with the dielectric outside surface.
  • devices may simultaneously be used for a better efficiency or to have ionization varying according to operating conditions.
  • the forces produced in the fluid by the device as described and their reaction applied to the vehicle through the magnetic coil may be divided into different species. Their action will be better understood by assuming three different operating conditions in which only one species is predominant, the other ones being then relatively negligible.
  • the body velocity is slow enough such that the induced electric current is negligible and the magnetic field strength and the fluid pressure are such that the Hall effect is negligible (since the Hall coefficient C w 1' is proportional to the electron cyclotron frequency a) which in turn is proportional to the magnetic field strength, and inversely proportional to the electron collision frequency 1/? which in turn is proportional to the pressure).
  • the air rotation produces underpressure due to the centrifugal force F, and the underpressure in turn reacts with the body surface, accelerating the fluid backward F and inducing to the bodythrough its surface a propulsion reaction F S similar to the sucking effect in a cyclone.
  • the vector relationship of the forces is seen in FIG. 3.
  • the centrifugal force F produced by the air rotation reacts with the body surface such that it can be divided into two components: F, is perpendicular to the surface and F is tangent to the surface.
  • the surrounding fluid is accelerated backward: due to the axial symmetry, F s in turn can be divided into two components: F that is perpendicular to the symmetry axis and F, that is parallel to the symmetry axis, which gives the said propulsion reaction.
  • the fluid radial acceleration due to the body motion U is obtained by a pressure gradient, i.e. an
  • the body motion U induces an azimuthal electric current j assketched in FIGS. 5 and 6, generating a decelerating compressure force F, as well as the reaction F thereof.
  • This induced force increases the pressure gradient or overpressure in front of the body, increasing drag and shock stand-off distance as it was proposed to be used for the re-entry of satellites.
  • the device according to the invention is characterized by its capability of inverting said induced force thanks to the Hall effect asit will be seen in the third case.
  • the azimuthal Hall current j will be larger than and opposite to the induced electric current and their combined action F H will be reversed, as sketched in FIGS. 7 and 8, with a propulsion reaction F R applied to the body through the magnetic coil.
  • the transverse component j of the electric current causes the surrounding fluid to rotate, inducing a centrifugal force as in the first case, but, for a large Hall coefficient, i.e. at low pressure or high altitude, this action will be negligeable (j j n)-
  • the Hall force F can be divided into two components, a radial force F,., similar to the centrifugal force, and a backward acceleration force F, both of them being necessary in order to reduce or suppress the overpressure produced by the body motion.
  • the pressure gradient can be replaced by the radial force F, to curve the streamlines aside from the body, but the conservation of mass condition implies a similar backward acceleration of the surrounding fluid along those contracting streamlines which are progressively narrowing, by the F component.
  • the device according to the invention generates radial expansion simultaneously with a backward acceleration that it can actually suppress the overpressure generated by the body motion and, thanks to its axial symmetry, this is achieved in the whole surrounding fiow.
  • the device according to the invention can work as a deceleration device when, for instance, the applied electric field is reversed or when C,,(uB, vB,)B is larger than E ,B, LB, wB which is the condition for partially recovering the body kinetic energy. It is also possible to make the deceleration varying, thanks to the Hall effect, when varying the applied electric field.
  • the device according to the invention can also be used inside a channel in order to accelerate a fluid without large variations of the channel cross section and pressure.
  • the magnetic coil may be disposed outside of the channel and the device will work as an electromagnetic pump or accelerator. It will not be very different from a radial Hess accelerator, except for the magnetic field convergence. It can be used together with the outside fluid acceleration, using the same magnetic field, in order to increase the total thrust.
  • the nose of the body would be hollow.
  • propulsion device reducing also the drag and noise generated by the front shock wave in case of a supersonic body. It can also be used for deceleration with body kinetic energy partial recovery, by increasing drag. In this case it will reduce heat transfer produced at hypersonic speed, by increasing shock stand-off distance.
  • the structure of the invention may be used with auxiliary devices for certain conditions of operation.
  • Variable geometry, retractable wings, auxiliary propulsion devices, etc. may be used without objection.
  • annular electrodes may be used, as shown in FIG. 9, which illustrates a body 1 similar to that shown in FIG. 1.
  • Four electrodes 61 to 64 are shown similar to electrodes 3 and 4 in FIGS. 1 and 2. It may also be advantageous to provide an additional pair of annular electrodes such as 65 and 66 where the body diameter is larger in order to suppress or modify the reaction couple applied to the vehicle.
  • Electrodes 67 to 72 substantially parallel to the direction of the fluid motion relative to the body, may also be used for modifying the motion direction or be used as auxiliary propulsion or deceleration device.
  • Ionization devices may also be used in order to modify locally or generally the surrounding fluid ionization.
  • one illustrative embodiment of such a device is schematically shown in FIG. 10.
  • Electrodes such as 72 and 73, e.g. of annular shape, are disposed on the outside surface of the dielectric body envelope 1.
  • Another electrode 75 is disposed on the inside surface of the body envelope.
  • the electrodes 72 and 73 are connected to a DC voltage source 74 which may be constituted by the electric field generator.
  • Electrode 75 is connected to an AC voltage source 76. Ionizing alternative glow discharge is thus induced between the dielectric body surface 71 and the outside electrodes 72 and 73.
  • the frequency and voltage of source 76 are to be adjusted in term of the operating conditions.
  • the invention was described illustratively in its application to a body moving in an electrically non conducting surrounding fluid, e.g. in the atmosphere.
  • the invention is not limited thereto but it will be apparent that it is applicable to a body moving in an electrically conducting fluid as well such as the ionosphere or sea water.
  • provision of ionization means is not necessary for ionizing the surrounding fluid or initiate said ionization as explained hereabove.
  • the operation of such a device is quite identical to that described in the foregoing.
  • Electromagnetic propulsion device to be mounted in the forward part of a body adapted to move in an ionizable fluid medium, comprising an electromagnetic coil for generating a poloidal magnetic field around said body, the symmetry axis of said magnetic field having substantially the same direction as the relative motion between the body and the surrounding fluid; at least two annular electrodes placed on the outside dielectric surface of said body perpendicularly to the symmetry axis of said magnetic field, one of said electrodes being mounted at the forward end of said body; and a power generator having its terminals connected to said electrodes for generating between same an electric field sufficient to provide for ionization of the fluid and an electric current in the ionized fluid around said body, the combined action of said electric current in the fluid subjected to said magnetic field causing said fluid to rotate such as to produce a centrifugal force, the electric current due to the Hall effect producing simultaneously an additional force effective to accelerate the ionized fluid backward and radially aside from the said body to increase the centrifugal force and produce
  • the electromagnetic propulsion device of claim 1 comprising means for changing the applied electric field strength and polarity to adapt the device to operating conditions and for reversing the force field direction in order to produce a deceleration effect with a body kinetic energy partial recovery.
  • the electromagnetic propulsion device of claim 1 further comprising a pair of annular parallel electrodes disposed on the outside surface of said body perpendicularly to the symmetry axis of said magnetic field thereby to modify or suppress the reaction rotation couple applied to said body.
  • the electromagnetic propulsion device of claim 1 further comprising at least two electrodes disposed on the outside surface of said body substantially parallel to the fluid relative motion, for changing the direction of motion and for increasing thrust or deceleration.
  • the ionization means comprise at least one device for producing an ionizing alternative glow discharge between the said electrodes and the body dielectric surface, thereby to modify the ionization of the fluid around said body.
  • Electromagnetic propulsion device to be mounted in the forward part of a moving body surrounded by an electrically conducting fluid, comprising an electromagnetic coil for generating a magnetic field around said body, the symmetry axis of said magnetic field having substantially the same direction as the relative motion between the body and the surrounding fluid; at least two annular electrodes placed on the outside dielectric surface of said body perpendicularly to the symmetry axis of said magnetic field, one of said electrodes being mounted at the forward end of said body; and a power generator having its terminals connected to said electrodes to produce an electric current between said electrodes in the electrically conducting fluid surrounding said body, the action of said electric current in said magnetic field causing said fluid to rotate and to produce a centrifugal force while at thesame time the electric current, due to the Hall efi'ect, produces an additional force effective to accelerate the ionized fluid backward and laterally aside from the said body to increase the centrifugal force and produce a propulsion force acting on said body.
  • the electromagnetic propulsion device of claim 6 comprising means for changing the applied electric field strength and polarity to adopt the device to operating conditions and for reversing the force field direction in order to produce a deceleration effect with a body kinetic energy partial recovery.
  • the electromagnetic propulsion device of claim 6, comprising a pair of annular parallel electrodes disposed on the body external surface perpendicularly to the symmetry axis of said magnetic field, thereby to modify or suppress the reaction rotation couple applied to said body.
  • the electromagnetic propulsion device of claim 6, comprising at least two electrodes disposed on the outside surface of said body, substantially parallel to the fluid relative motion, for changing the direction of motion and for increasing thrust or deceleration.

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Cited By (28)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4663932A (en) * 1982-07-26 1987-05-12 Cox James E Dipolar force field propulsion system
US4891600A (en) * 1982-07-26 1990-01-02 Cox James E Dipole accelerating means and method
WO1990014265A1 (de) * 1989-05-24 1990-11-29 Laukien Guenther Verfahren und vorrichtung zum antreiben von wasserfahrzeugen
WO1991001915A1 (de) * 1989-07-28 1991-02-21 Laukien Guenther Verfahren und vorrichtung zum antreiben von wasserfahrzeugen
US5087215A (en) * 1990-03-08 1992-02-11 Leonid Simuni Ocean-going vessel and method for increasing the speed
US5263661A (en) * 1992-09-11 1993-11-23 Riley Jennifer K Sonic boom attenuator
WO1994000342A1 (en) * 1992-06-26 1994-01-06 British Technology Group Usa Inc. Electromagnetic device and method for boundary layer control
WO1994010032A1 (en) * 1992-10-26 1994-05-11 British Technology Group Usa Inc. Multiple electromagnetic tiles for boundary layer control
US5354017A (en) * 1990-07-09 1994-10-11 Orlev Scientific Computing, Ltd. Method for controlling turbulence
WO1995000391A1 (en) * 1993-06-25 1995-01-05 British Technology Group Usa Inc. Multiple electromagnetic tiles for boundary layer control
US5437421A (en) * 1992-06-26 1995-08-01 British Technology Group Usa, Inc. Multiple electromagnetic tiles for boundary layer control
US5964433A (en) * 1995-11-20 1999-10-12 The Trustees Of Princeton Univ. Staggered actuation of electromagnetic tiles for boundary layer control
US6179250B1 (en) * 1999-02-10 2001-01-30 Laurence Waters Air and space vehicle propulsion system
RU2166667C1 (ru) * 1999-09-16 2001-05-10 Мулин Вадим Венедиктович Способ получения тяги и устройство, реализующее этот способ
US6404089B1 (en) * 2000-07-21 2002-06-11 Mark R. Tomion Electrodynamic field generator
US6492784B1 (en) 1999-03-05 2002-12-10 Gravitec, Inc. Propulsion device and method employing electric fields for producing thrust
US20030193319A1 (en) * 2002-04-12 2003-10-16 Wood James Rick Ion powered platform
US20040007149A1 (en) * 2002-07-12 2004-01-15 Arthur Vanmoor Hydrodynamically and aerodynamically optimized leading and trailing edge configurations
US20050217237A1 (en) * 2003-10-10 2005-10-06 Willett Everett W Thrust, with or without the ejection of propellant
US20060073976A1 (en) * 2004-10-01 2006-04-06 Pohlman Marlin B Method of gravity distortion and time displacement
US7234667B1 (en) * 2003-12-11 2007-06-26 Talmage Jr Robert N Modular aerospace plane
US7380756B1 (en) 2003-11-17 2008-06-03 The United States Of America As Represented By The Secretary Of The Air Force Single dielectric barrier aerodynamic plasma actuation
US20080217965A1 (en) * 2007-03-10 2008-09-11 Honda Motor Co., Ltd. Plasma Wind Deflector for a Sunroof
US20150232172A1 (en) * 2014-02-20 2015-08-20 Donald Steve Morris Airfoil assembly and method
US20220340308A1 (en) * 2021-04-23 2022-10-27 United States Of America As Represented By The Administrator Of Nasa System and method for lift augmentation of atmospheric entry vehicles during aerocapture and entry, descent, and landing maneuvers
US11685493B1 (en) * 2020-03-18 2023-06-27 Hyalta Aeronautics, Inc. Encapsulated magneto hydrodynamic drive
US20230344370A1 (en) * 2022-04-20 2023-10-26 James Howard Bushong, JR. Methods for generating electromagnetic force-fields
US12283421B2 (en) 2021-03-17 2025-04-22 Brian Faircloth Methods and apparatuses for producing ultra-strong magnetic fields, and propulsion systems and methods utilizing planetary magnetic fields

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US2949550A (en) * 1957-07-03 1960-08-16 Whitehall Rand Inc Electrokinetic apparatus
US3162398A (en) * 1959-01-26 1964-12-22 Space Technology Lab Inc Magnetohydrodynamic control systems
US3446464A (en) * 1967-03-09 1969-05-27 William A Donald Method and apparatus for reducing sonic waves and aerodynamic drag

Patent Citations (3)

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US2949550A (en) * 1957-07-03 1960-08-16 Whitehall Rand Inc Electrokinetic apparatus
US3162398A (en) * 1959-01-26 1964-12-22 Space Technology Lab Inc Magnetohydrodynamic control systems
US3446464A (en) * 1967-03-09 1969-05-27 William A Donald Method and apparatus for reducing sonic waves and aerodynamic drag

Cited By (36)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4891600A (en) * 1982-07-26 1990-01-02 Cox James E Dipole accelerating means and method
US4663932A (en) * 1982-07-26 1987-05-12 Cox James E Dipolar force field propulsion system
WO1990014265A1 (de) * 1989-05-24 1990-11-29 Laukien Guenther Verfahren und vorrichtung zum antreiben von wasserfahrzeugen
US5352139A (en) * 1989-05-24 1994-10-04 Gunther Laukien Method and apparatus for the propulsion of water vehicles
WO1991001915A1 (de) * 1989-07-28 1991-02-21 Laukien Guenther Verfahren und vorrichtung zum antreiben von wasserfahrzeugen
US5249990A (en) * 1989-07-28 1993-10-05 Laukien Guenther Method and apparatus for the propulsion of water vehicles
US5087215A (en) * 1990-03-08 1992-02-11 Leonid Simuni Ocean-going vessel and method for increasing the speed
US5354017A (en) * 1990-07-09 1994-10-11 Orlev Scientific Computing, Ltd. Method for controlling turbulence
US5437421A (en) * 1992-06-26 1995-08-01 British Technology Group Usa, Inc. Multiple electromagnetic tiles for boundary layer control
WO1994000342A1 (en) * 1992-06-26 1994-01-06 British Technology Group Usa Inc. Electromagnetic device and method for boundary layer control
US5320309A (en) * 1992-06-26 1994-06-14 British Technology Group Usa, Inc. Electromagnetic device and method for boundary layer control
US5263661A (en) * 1992-09-11 1993-11-23 Riley Jennifer K Sonic boom attenuator
WO1994010032A1 (en) * 1992-10-26 1994-05-11 British Technology Group Usa Inc. Multiple electromagnetic tiles for boundary layer control
WO1995000391A1 (en) * 1993-06-25 1995-01-05 British Technology Group Usa Inc. Multiple electromagnetic tiles for boundary layer control
US5964433A (en) * 1995-11-20 1999-10-12 The Trustees Of Princeton Univ. Staggered actuation of electromagnetic tiles for boundary layer control
US6179250B1 (en) * 1999-02-10 2001-01-30 Laurence Waters Air and space vehicle propulsion system
US6492784B1 (en) 1999-03-05 2002-12-10 Gravitec, Inc. Propulsion device and method employing electric fields for producing thrust
RU2166667C1 (ru) * 1999-09-16 2001-05-10 Мулин Вадим Венедиктович Способ получения тяги и устройство, реализующее этот способ
US6404089B1 (en) * 2000-07-21 2002-06-11 Mark R. Tomion Electrodynamic field generator
US20030193319A1 (en) * 2002-04-12 2003-10-16 Wood James Rick Ion powered platform
US20040007149A1 (en) * 2002-07-12 2004-01-15 Arthur Vanmoor Hydrodynamically and aerodynamically optimized leading and trailing edge configurations
US7017508B2 (en) * 2002-07-12 2006-03-28 Arthur Vanmoor Hydrodynamically and aerodynamically optimized leading and trailing edge configurations
US20050217237A1 (en) * 2003-10-10 2005-10-06 Willett Everett W Thrust, with or without the ejection of propellant
US7380756B1 (en) 2003-11-17 2008-06-03 The United States Of America As Represented By The Secretary Of The Air Force Single dielectric barrier aerodynamic plasma actuation
US7234667B1 (en) * 2003-12-11 2007-06-26 Talmage Jr Robert N Modular aerospace plane
US20060073976A1 (en) * 2004-10-01 2006-04-06 Pohlman Marlin B Method of gravity distortion and time displacement
US20080217965A1 (en) * 2007-03-10 2008-09-11 Honda Motor Co., Ltd. Plasma Wind Deflector for a Sunroof
US7735910B2 (en) 2007-03-10 2010-06-15 Honda Motor Co., Ltd Plasma wind deflector for a sunroof
US20150232172A1 (en) * 2014-02-20 2015-08-20 Donald Steve Morris Airfoil assembly and method
US11685493B1 (en) * 2020-03-18 2023-06-27 Hyalta Aeronautics, Inc. Encapsulated magneto hydrodynamic drive
US12017743B1 (en) * 2020-03-18 2024-06-25 Hyalta Aeronautics, Inc. Encapsulated magneto hydrodynamic drive
US12283421B2 (en) 2021-03-17 2025-04-22 Brian Faircloth Methods and apparatuses for producing ultra-strong magnetic fields, and propulsion systems and methods utilizing planetary magnetic fields
US20220340308A1 (en) * 2021-04-23 2022-10-27 United States Of America As Represented By The Administrator Of Nasa System and method for lift augmentation of atmospheric entry vehicles during aerocapture and entry, descent, and landing maneuvers
US12125636B2 (en) * 2021-04-23 2024-10-22 United States Of America As Represented By The Administrator Of Nasa System and method for lift augmentation of atmospheric entry vehicles during aerocapture and entry, descent, and landing maneuvers
US12283418B2 (en) 2021-04-23 2025-04-22 United States Of America As Represented By The Administrator Of Nasa Electrode design for lift augmentation and power generation of atmospheric entry vehicles during aerocapture and entry, descent, and landing maneuvers
US20230344370A1 (en) * 2022-04-20 2023-10-26 James Howard Bushong, JR. Methods for generating electromagnetic force-fields

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