SYSTEM, APPARATUS, AND METHOD FOR GENERATING DIRECTIONAL FORCES BY INTRODUCING A CONTROLLED PLASMA ENVIRONMENT INTO AN

ASYMMETRIC CAPACITOR

FIELD OF THE INVENTION

The present invention relates to asymmetrical capacitors. More particularly, the invention relates to generating a force using asymmetrical capacitors by introducing a controlled plasma environment.

BACKGROUND OF THE INVENTION

Asymmetric capacitors are known to exhibit a net force when sufficient power is applied. An asymmetric capacitor is generally a capacitor that has geometrically dissimilar electrode surface areas. The electrical field surrounding an energized asymmetric capacitor creates an imbalanced force and therefore a motive force of a small magnitude. The challenge over the past decades has been the amount of energy required to produce the motive force, also known as thrust-to-power consumption ratio. Although lightweight, asymmetric capacitor models have demonstrated the ability to produce enough force to overcome the effect of gravity on their own mass, the amount of energy required has been prohibitive to make practical and commercial use of this feature. Another challenge is the "space charge limited current" saturation point (also referred to as "charged space limits") or the limit of charged particles that a given volume of space can accommodate. The amount of particles in a given volume limits the amount of force that can be generated from such volume.

Various researchers have used ions and their movements to produce motive forces for a variety of reasons. Some U.S. patents describe electrostatic charges relative to motive forces in various environments. These patents are incorporated herein by reference. For example, U.S. Pat. No. 1,974,483, issued in September 1934 to Brown, relates to a method of producing force or motion by applying and maintaining high potential electro-static charges in a system of chargeable masses and associated electrodes. U.S. Pat. No. 2,460,175, issued in January 1949 to Hergenrother, relates to ionic vacuum pumps that ionize molecules of gas and then withdraw the molecules by a force of attraction between the molecules and a conductive member energized with a negative potential. U.S. Pat. No. 2,585,810, issued in February 1952 to Mallinckrodt, relates to jet propulsion apparatus and to electric arc apparatus for propelling airplanes. U.S. Pat. No. 2,636,664, issued in April 1953 to Hertzler, relates to pumping methods that subject molecules of a gas to ionizing forces that cause them to move in a predetermined direction. U.S.

Pat. No. 2,765,975, issued in October 1956 to Lindenblad, relates to movement of a gas without moving parts through corona discharge effects on the gas. U.S. Pat. No. 2,949,550, issued in August 1960 to Brown, relates to an electrokinetic apparatus that utilizes electrical potentials for the production of forces to cause relative motion between a structure and the surrounding medium. U.S. Pat. No. 3,120,363, issued in February 1964 to Gehagen, relates to a heavier than air flying apparatus and methods of propulsion and control using ionic discharge. U.S. Pat. No. 6,317,310, issued in November 2001 to Campbell, relates to methods and apparatus, discloses two dimensional, asymmetrical capacitors charged to high potentials for generating thrust.

A non-ionic use of air molecules across an airfoil to produce a lift is seen in U.S. Pat. No. 2,876,965, issued in March 1959 to Streib. This patent relates to circular wing aircraft capable of vertical and horizontal flight using the radial cross-section of the wing as an efficient airfoil.

Brown observed the non-zero net force of an asymmetric capacitor system in a vacuum environment. It appears that this phenomenon can be explained by considering the pressure on the electrode surfaces due to the charged ions evaporated from the electrodes in the absence of the charged ions created in a medium (air). Brown also observed that the force produces relative motion between the apparatus and the surrounding fluid dielectric medium, i.e., the dielectric medium is caused to move past the apparatus if the apparatus is held in a fixed position. Further, if the apparatus is free to move, the relative motion between the medium and the apparatus results in a forward motion of the apparatus. It is possible that these phenomena can be explained by the theory that the momentum transfer of charged ions to the electrode surfaces is the mechanism to produce the net propulsive force, because the energetic ions are redirected and move through and around the capacitor without losing any momentum if the system is held in a fixed position. If the system is free to move, there still will be ions flowing through and around the capacitor as a result of collisions but this flow should be much weaker than that in the case of fixing the system since the ions lose their kinetic energy and momentum through collisions with the electrode surfaces. Further, Klaus Szielasko (GENEFO www.genefo.org "High Voltage Lifter Experiment: Biefi eld-Brown Effect or Simple Physics?" Final Report, April 2002) observed that there was no difference in the motion of the device when the polarity of the system was reversed, thus establishing that the electrostatic force experienced by charged ions is not the mechanism of propulsion. Further guidance supporting the underlying principles can be obtained from Canning, Francis X., Melcher, Cory, and Winet, Edwin, Asymmetrical Capacitors or Propulsion, Glenn Research Center of NASA (NASA/CR-2004-213312), Institute for

Scientific Research, October, 2004, published after the provisional application upon which this application claims the benefit.

The electrokinetic fields generated before the present invention have largely suffered from relatively high energy input yielding low output or net force. While the general concept of asymmetric capacitors and the use of ionic forces are known, the inability to produce sufficient motive force has eliminated many potential uses. Thus, the dilemma heretofore has been to increase the amount of conduction current in an ion processing propulsion system without increasing the power consumption, when the level of high-voltage required must be high enough to create the conduction current in the first place. A further challenge has been the heretofore accepted high voltage input needed based on the above listed efforts and other similar efforts. However, the high voltage input has undesirable secondary effects. These effects include a substantial electromagnetic field and interference, static electricity buildup on surrounding objects, x-radiation, ozone production, and other negative effects. Therefore, there remains a need for an improved asymmetric energy field to produce an improved motive force.

SUMMARY OF THE INVENTION

The present invention provides method, apparatus, and system to generate a motive and other forces by introducing a controlled plasma environment into an asymmetric capacitor. A flow of energy or plasma is directed outward from the apparatus. The present invention uses the asymmetric aspects of the related energy field, but energizes the energy field by several orders of magnitude. This extraordinary increase in motive force is accomplished in part by increasing plasma density, plasma energy (and an equivalent plasma temperature) and related particle velocity, or a combination thereof. The increase allows the use of ionic motive forces for practical applications that heretofore has been unavailable.

In one embodiment, the energy field is energized by applying a system to introduce a controlled plasma environment in the energy field through electromagnetic radiation, such as with a laser or an annular array of light emitting diodes (LEDs). The energy field can be energized by increasing the plasma density, plasma energy and particle velocity, or a combination thereof. Further, the plasma environment can be energized prior to developing a significant asymmetric energy field. In yet another embodiment, the present invention significantly enhances forces at substantially reduced voltage levels using the electromagnetic

radiation compared to the previously required voltage levels without the electromagnetic ^" radiation. Advantageously, the low voltage can reduce or eliminate negative secondary effects caused by the heretofore prior high voltage levels required to energize the asymmetric capacitor engine.

5 The present disclosure provides a method of providing a force with an asymmetric capacitor engine, comprising: applying electromagnetic radiation to particles in a media in proximity to an asymmetric capacitor engine having at least three electrodes of different surface areas and separated by a distance; applying voltage to at least one of the electrodes to generate a net force with the asymmetric capacitor engine; and varying the force by applying the voltage,

10 radiation, or a combination thereof to different combinations of the electrodes.

The present disclosure further provides a system for producing a force, comprising: an asymmetric capacitor engine comprising at least one first electrode having a first surface area and at least two second electrodes each having a second surface area different from the first surface area, the second electrodes being disposed at angles to each other relative to the first

15 electrode; a voltage source coupled to the asymmetric capacitor engine to apply voltage to the engine and generate a net force with the engine, the direction of the net force being dependent on the voltage applied to various combinations of the first electrode and the second electrodes; and an electromagnetic radiation source adapted to apply radiation to particles between the electrodes.

20 The disclosure also provides a system for producing a force, comprising: an asymmetric capacitor engine comprising at least one first electrode having a first surface area and at least one second electrode having a second surface area different from the first surface area; a voltage source coupled to the asymmetric capacitor to apply voltage to the engine and generate a net force with the engine; and at least one electromagnetic radiation source adapted to apply

25 radiation to at least a selected portion of one or more of the electrodes.

BRIEF DESCRIPTION OF THE DRAWINGS

A more particular description of the invention, briefly summarized above, may be had by reference to the embodiments thereof, which are illustrated in the appended drawings and

30 _. described herein. It is to be noted, however, that the appended drawings illustrate only some embodiments of the invention and are therefore not to be considered limiting of its scope, because the invention may admit to other equally effective embodiments.

Figure 1 is a schematic view of an electromagnetic field environment created from an

asymmetric capacitor and related system of the present disclosure. —

Figure 2A is a charged particle schematic diagram of the baseline asymmetric capacitor in a more simplified form to Figure 1.

Figure 2B is a charged particle schematic diagram of the asymmetric capacitor with 5 applied electromagnetic radiation (EMR) ₅ illustrating increased particle density.

Figure 2C is a charged particle schematic diagram of the enhancement of the present invention with electromagnetic radiation illustrating the resulting increased particle density and velocity.

Figure 2d is a schematic diagram showing the volt-ampere characteristic of a Langmuir 10 electrostatic probe.

Figure 3 is a schematic diagram of a motive force of neutral particles momenta experienced collisions with charged particles.

Figure 4 is a schematic diagram of one embodiment of an asymmetric capacitor engine.

Figure 5 a is a schematic diagram of a cross sectional view of one embodiment of a 15 system using the asymmetric capacitor.

Figure 5B is a top view schematic of the embodiment shown in Figure 5 A.

Figure 6 is a schematic diagram of the power budget for one exemplary embodiment.

Figure 7A is a schematic perspective view of one embodiment of an unmanned aerial vehicle (UAV). 20 Figure 7B is a schematic top view of the embodiment of Figure 7 A.

Figure 7C is a schematic side view of the embodiment of Figure 7 A.

Figure 8 A is a schematic perspective view of one embodiment of a manned aerial vehicle (MAV).

Figure 8B is a schematic front view of the embodiment of Figure 8 A.

25. Figure 9 A is a schematic top view of another embodiment of the present invention using an asymmetric capacitor engine.

Figure 9B is a schematic side view of the embodiment shown in Figure 9A.

Figure 10 is a partial schematic cross-sectional view of the embodiment shown in Figure 9A.

30 Figure 10a is a schematic diagram of the vehicle in Figure 10 having a body normal axis generally aligned with an earth normal axis.

Figure 10b is a schematic diagram of the vehicle in Figure 10 having a body normal axis at an angle to the earth normal axis.

Figure HA is a partial schematic cross-sectional view of the embodiment shown in Figure 10 as seen from the body normal axis looking toward the vehicle ^* peπpHeryfiflustrating ^" one or more anodes, cathodes, and/or EMR sources.

Figure 1 IB is a schematic diagram illustrating force components of the thrust vector of Figure HA.

Figure 12A is a partial schematic cross-sectional view of the asymmetric engine shown in Figure HA, illustrating a thrust vector directional change.

Figure 12B is a schematic diagram illustrating force components of the thrust vector of Figure 12 A. Figure 13 is a schematic diagram of another embodiment of the asymmetric engine having a multi-directional thrust capability.

Figure 14 is a partial schematic cross-sectional view of a vehicle having an asymmetric engine 100 with a multi-directional thrust capability illustrated in Figure 13.

Figure 15A is a schematic top view diagram of one embodiment of a vehicle illustrating various thrust locations for moving the vehicle.

Figure 15B is a schematic diagram illustrating various thrust vectors on the vehicle shown in Figure 15A for acceleration.

Figure 15C is a schematic diagram illustrating the various thrust vectors on the vehicle shown in Figure 15A for constant velocity. Figure 15D is a schematic diagram illustrating the various thrust vectors on the vehicle shown in Figure 15A for deceleration.

DETAILED DESCRIPTION

The present invention relates to a system, method, and apparatus that generates a force from an asymmetric capacitor by applying electromagnetic radiation (or "EMR" herein) to particles between electrodes in the asymmetric capacitor to ionize the particles. The electromagnetic radiation generates a highly energized state, such as a plasma, in the capacitor for producing an increased force, such as a motive or other force emanating from the capacitor, compared with prior efforts. This force increase is achieved by controlling the plasma density, plasma energy or particle velocity, plasma temperature, negative electrode (cathode) surface area in relation to the anode, or a combination thereof.

The asymmetric capacitor, having different electrodes with different surface areas, gains a net force in the axial direction, that is, in the direction of the line from the large or negative

electrode to the small or positive electrode. This force direction applies regaFdless-of-pol-arity-of-- the supply voltage, because the directions of these net forces do not change when polarity is changed. The net force on the large or negative electrode is much larger than that of the small or positive electrode due to large differences in the surface area. In general, the disclosure provides for applying external energy at favorable frequencies to excite particles into ions, or ions into more energetic ions, to create a plasma condition. The disclosure provides a relatively low energy input for a comparatively large force output by creating a plasma that can be manipulated between the electrodes of the asymmetric capacitor when voltage is applied to the electrodes. The term "plasma" is well known and is intended to include a high energy collection of free-moving electrons and ions, i.e. atoms that have lost electrons. Energy is needed to strip electrons from atoms to make plasma. The energy input to the particles for the plasma can be of various origins: thermal, electrical, or light (ultraviolet light or intense light from a laser). Without sufficient sustaining power, plasmas recombine into a neutral gas. Overview of the invention and asymmetric capacitor

Figure 1 is a schematic view of an electromagnetic field environment created from an asymmetric capacitor and related system of the present disclosure. The figure provides some understanding of the operation of an asymmetric capacitor to better understand the inventive improvement. The size of vectors (i.e., forces in a certain direction) representing the momentum transfer from charged particles is neither scaled nor accurate. The electromagnetic field lines are approximate.

An asymmetric capacitor 2 generally includes a first electrode 4 and a second electrode 6 separated by a distance through a media 11, including a gas, such as air, a vacuum such as space, or a liquid. Operation in the vacuum of space generally would advantageously use the injection of a media with particles. For operation in liquids, generally the engine will be energized and functioning with a plasma between the electrodes and be supplied with vaporized liquid, such as water vapor having properties of gases sufficient to ionize with associated collisions discussed herein. The first electrode has a first surface area calculated around the portion exposed to the media and the second electrode likewise has a second surface area. For an asymmetric capacitor, the surface areas are different. Further, the absolute size of each electrode and relative size of one electrode to the other electrode can cause a difference in net force generated with the electrodes. Generally, the first electrode is an anode and the second electrode is a cathode with the anode having a more positive charge (voltage) than the cathode. Generally, the cathode will

have the larger surface area. The electrodes can be any geometric shape ^~ or combination with- other shapes and have geometric patterns formed within one or more of the electrodes, such as openings and so forth. The anode can be, for example and without limitation, an emitter wire(s), blade(s), or disc(s), and the cathode can be a sheet(s), blade(s), or disc(s). The electrodes can be any suitable material, including copper, aluminum, steel, or other materials capable of establishing the electromagnetic field between the electrodes. Generally, the electrodes include conductive materials to establish the electromagnetic field. For some applications, weight, costs, conductivity, structural integrity, and other factors can determine the exact materials or combination of materials for a particular electrode. For example, and without limitation, a first material having a higher density and/or more conductivity can be applied over a lower density and/or less conductive material to create a composite electrode. Further, the electrodes can be a plurality of surfaces electrically coupled together to alter the surface area of the particular electrode. By convention, a positive voltage is applied to the anode through a power supply 8 and the cathode is negative in relation to the anode, although it is possible to reverse the polarity. In some embodiments, voltage can be applied to both electrodes with the anode generally having a more positive potential. Alternating current (AC) and direct current (DC) can be used. When voltage is applied to at least one of the electrodes, such as the anode, an electromagnetic field is created between the electrodes because the media therebetween is relatively non-conductive compared to the electrodes. For present purposes, the field is discussed in terms of an electric field 12 having electric field lines of varying strength that at a center point between the electrodes are generally parallel to a line 9 drawn between the electrodes and bend and even reverse near the electrodes. The magnetic field 14 has magnetic field lines that are generally perpendicular to the electric field lines at any particular point on the electric field lines. Thus, at the center point between the electrodes, the magnetic field lines will be generally perpendicular to the line 9. The electric field serves to energize particles.16 in the media, creating ions of some charge value and the magnetic field serves to attract the ions in the direction of the magnetic field at the particular location of the ion. Because the electric and magnetic fields extend beyond a straight line from electrode to electrode, particles beyond the straight line and surrounding the electrodes can also be affected. Thus, such particles surrounding the electrodes can be included in the volume defined broadly herein as "between" the electrodes, as shown in the electromagnetic field region 28. The term "particle" is used broadly herein and includes both neutral particles and charged particles (that is "ionized")

particles, unless'the particular context directs otherwise. The particles can be molecules-oratoms- or subatomic particles such as electrons, neutrons, and protons, and other subatomic particles.

More specifically, when a voltage is applied to the asymmetric capacitor 2, the conductive current runs from the smaller or positive electrode 4 to the larger or negative electrode 6. According to Ampere's law, this conductive current creates an azimuthally magnetic field surrounding the capacitor. For clarification, cylindrical coordinates are applied in this system by taking the axial direction in the direction of the line 9 from the negative electrode to the positive electrode. The "daughter" charged particles are created in the medium, generally air, or water vapor or other introduced medium as described herein, and evaporated or otherwise emitted from the electrode surfaces due to collisions with the "parent" electrons and ions, experience a Lorentz force (jxB or en VxB) in addition to the force due to the prescribed electric field (eE), where vector quantities are expressed in the bold letters. Here, "parent" is intended to mean the original charged particle carrying the conductive current and "daughter" is intended to mean the secondary charged particle created by collisions with the parent charged particles. At the top and bottom of the electrode 6, the ions are pushed inward due to this Lorentz force (in cylindrical coordinates: -zx-φ= -r, where (z) represents the axial component of the electric field, (φ) represents the direction of the magnetic field, and (r) represents the direction of motion of ions).

On the upper flat surface of the electrode 6, the ions are pushed upward due to this force (-rx-φ=-z), where the upward direction is the direction toward the smaller relatively positive electrode 4. On the region closer to the top surface, the ions are pushed to the inward and upward direction. Upward movements of the ions are reversed on the lower surface of the larger or negative electrode 6 due to the reversed directions (φ) of the axial component (z) of the electric field at the bottom of the electrode and this in turn reverses the direction (φ) of magnetic field. The forces in this region are considered weaker than those in the upper region as being further away from the first electrode 4, resulting in a net force in the direction of the axial component (z). Ions near the more positive, smaller electrode 4 experience similar movements, but in the opposite direction of the axial component (z).

A motive (that is, thrust) force is the net force from the pressure (created by collisions with energetic ions) all over the body surface of the particular electrode, resulting in the net force 5 on the electrode 4 and the net force 7 on the electrode 6 in the opposite direction to net force 5 on the first electrode 4. The net forces for each electrode are aligned in the direction of the line 9, but in an opposite direction (that is, along a z axis in a coordinate axis system). The net force

on the electrode 6 is larger than that of the electrode 4 because of the differences in electrode surface area. The whole system using an asymmetric capacitor gains a resultant net force 26 by the vector sum of the forces 5, 7 in the axial direction of line 9, i.e., in the direction of the line from the negative or larger electrode to the positive or smaller electrode, regardless of polarity of 5 the supply voltage.

Although movements of associated electrons are completely opposite to those of the ions, the momentum transfer of the electrons is considered trivial and negligible compared to the momentum transfer of the ions. Thus, momentum transfer of the ions to neutral particles is considered the main mechanism to contribute to a net motive force. An ion jet 18 of particles is

10 created in a direction away from the larger electrode 6 distal from the smaller electrode 4 that can further emanate a force from the capacitor.

The order of magnitude of the Lorentz force due to the magnetic field created by the conductive current is generally negligible compared to that of electrostatic force. However, it is believed that the Lorentz forces can be significant at local spots where a strong magnetic field is

15. . possible when the local current density of the plasma is dramatically increased from Ohmic heating and enhanced conductivity. At such spots, the order of magnitude can be mega-amperes per centimeter squared, so that the Lorentz force is comparable to or greater than the electrostatic force.

With the basic understanding of the operation of an asymmetric capacitor, attention is

20 drawn to further discussion of the inventive aspects. In at least one embodiment, creating an enhanced ionized environment of particles within a volume of media between the asymmetric capacitor's electrodes enhances the charged particle density, temperature of the particles, or both. The enhanced charged particles can be raised to a plasma level environment that can be controlled in terms of plasma density and average plasma temperature (and therefore affecting

25 particle velocity). The term "plasma" is intended to mean generally an electrically neutral, highly ionized gas composed of ions, electrons, and neutral particles. It is a phase of matter distinct from solids, liquids, and normal gases.

The enhanced ionized environment of particles can be created by providing electromagnetic radiation, such as ultraviolet radiation, infrared radiation, radio-frequency

30 radiation, other frequencies, or a combination thereof, into the particles. The environment generally includes at least a partial plasma. One or more electromagnetic radiation sources 20, 2OA can be used to provide such radiation. Advantageously, certain wavelengths of radiation can be used dependent on the particles to be ionized to raise the particles to a plasma state. The

sources 20, 2OA can be powered by one or more power supplies 22, 22A, which can be the same as the power supply 8.

The value of net forces derived from the asymmetric capacitor according to the teachings herein can be raised without increasing input power to the capacitor from the power supply 8. Naturally, input power is required for the electromagnetic radiation sources to ionize and perhaps create the controlled plasma environment. However, the net gain to the system can energize the electric field by a significant margin, and even by an order of magnitude or more.

The particles in the electromagnetic field created by the power to the electrodes can be further energized by applying electromagnetic radiation to the volume between the electrodes. The electromagnetic radiation can increase a plasma density between the electrodes, including the volume of particles within the electric field. The electromagnetic radiation can also increase the plasma temperature that increases particle velocities by using alternative sources of electromagnetic radiation. In some embodiments, the electric field can be increased both in plasma density and in temperature. Further, the electric field can be energized prior to developing a significant asymmetric energy field.

Increasing the plasma density and/or plasma temperature allows an increase in what heretofore has been a limiting factor on power output through the net force from an asymmetric capacitor system, despite many decades of effort. A term known as "space-charge-limited current," described more fully below, is the maximum amount of charge from ions within a given space before saturation occurs and limits further charges. Increasing the saturation value can allow an increase in the net force and power output.

Prior efforts focused on high voltage with attendant limitations and complications. The inventors developed an alternative and improved method of increasing the plasma density and/or temperature with the attendant increase in saturation level by allowing a relatively low voltage to be used for the asymmetric capacitor and amplifying the energy to the particles through electromagnetic radiation of one or more wavelengths. The result was an unexpected non-linear response that greatly increased the net force as output from the asymmetric capacitor over any known asymmetric capacitor arrangement using the same voltage. In some embodiments, the increase was an order of magnitude or more. Advantageously, the low voltage can reduce or eliminate negative effects that heretofore resulted from the high voltage levels required to energize the asymmetric capacitor engine.

Further, the inventors determined that injecting particles into the electric field increases the generated force that the system of the present disclosure can accommodate due to the

__ increased capacity to use additional particles by an increased saturation value. Injected particles _ can include gaseous particles, such as hydrogen, helium, or other gases and materials. The injection can be supplemental to the media in which the asymmetric capacitor operates or instead of such medium. Further, injecting particles can enhance the ability of the asymmetric capacitor 5 to operate under less than standard conditions of pressure (1 atmosphere), such as the relative vacuum of space or other low or essentially no pressure conditions.

Figures 2A, 2B, 2C are schematic diagrams of an asymmetric capacitor with charged particles that contrast the significant enhancements to the vector sum of forces in accordance with the present teachings. Figure 2A is a charged particle schematic diagram of the baseline

10 asymmetric capacitor in a more simplified form to Figure 1. A first electrode 4 and a second electrode 6 have different surface areas exposed to particles to be energized and form the basic asymmetric capacitor 2 configuration. The particles 16 between the electrodes (i.e. the particles in the electromagnetic field 28) have a certain density and velocity 24. The velocity is indicative of the energy level of the particular particle and hence temperature. As described in Figure 1, the

15 particle interactions create a net force on the asymmetric capacitor as a whole, illustrated as force 26.

Figure 2B is a charged particle schematic diagram of the asymmetric capacitor with applied electromagnetic radiation, illustrating increased particle density. Applying electromagnetic radiation to the particles significantly provides increased power output in the

20 way of a resultant net force with the asymmetric capacitor. It is believed the application of electromagnetic radiation increases the plasma density. The electrodes 4, 6 can be operated at a given power level. An electromagnetic radiation source 20 can apply electromagnetic radiation to the particles 16 to provide energy to the particles. More particularly, in at least one

. embodiment, the electromagnetic radiation can be applied with a laser, one or more light

25 emitting diodes (LEDs), or other photon emission sources. The radiation is used to create at least a partial ionization of the media between the electrodes, including generally the media in which the asymmetric capacitor operates. Advantageously, the wavelength used by the laser can be a relatively short wavelength, such as infra-red (IR) and ultra-violet (UV) or shorter. For example, research into photo-ionization indicates that at specific frequencies of about or below 1024 nm

30 for O ₂ and about or below 798 nm for N ₂ , both of these atmospheric molecules will photo-ionize and become ready for manipulation by electrical fields in the same way as similar molecules ionized by high-voltage. Although the frequencies can vary with differing efficiencies of ionization, a commercially viable range of frequencies is believed to be about 750 nm to about

1024 ^" rihϊ for O ₂ , and from about 248 nm to about 798 tim for N ₂ . Such gas-specific ^" frequencies ^" are sometimes referred to as Fraunhofer frequencies. These harmonic frequencies cause the specific gas to ionize with relatively little energy input. Less energy to ionize the particles to prepare the plasma creation contributes to more force output per energy input unit. Further, a combination of frequencies can be provided to the media. In the example above, if the media is air comprising largely oxygen and nitrogen, then energy at the specific frequency for each component can be applied to the media to achieve more efficient ionization. Still further, other electromagnetic radiation can be applied at various frequencies, some short wave and others long wave, which can add further energy to the particles. The frequencies can be applied simultaneously to the particles or in stepped fashion and in different sequences separate or in combination with a sequence of the voltage applied to the capacitor. Such simultaneous or sequenced application advantageously leads to a higher efficient to the engine.

Another source of radiation is to use a 248 nm laser with high energy femtosecond pulses to ionize the air (possibly an order of 10 ¹¹ particles/cm ³ ). Further, the system can use a longer wavelength such as 750 nm IR to stabilize the plasma by reducing a plasma neutralization occurring undesirably by recombination with other particles to produce neutral particles that may not contribute to the force in any substantial way. The frequency or frequencies to be applied are exemplary and largely depend on the media in which the asymmetric capacitor is operated and the particular particles to be energized, as could be determined by one with ordinary skill in the art provided the guidance and disclosure contained herein without undue experimentation. Such person would generally include one skilled in physics, such as plasma physics. The disclosure generally provides for increasing efficiently the energy into the particles, through other than the prior single reliance on voltage across electrodes of the asymmetric capacitor, to create the plasma and to yield a relatively large force. By ionizing the particles in the volume within and around the asymmetric capacitor with electromagnetic radiation, such as UV and/or IR light, the media density and energy is increased to the point that at least a partial plasma is produced. The plasma can be accelerated and steered by electric and magnetic fields, which allows it to be controlled and applied.

An increased plasma density and temperature has a double benefit: it provides a greater number of particles to cause molecular collisions and further ionization within the same volume; and the energy of the particles is also increased imparting greater energy during collisions. The increased capacity of ionization results in more impacts and a greater net force 26 compared to Figure 2A.

The increased plasma density can allow a reduction in the voltage to the electrodes for-a- given net force and reduction of negative high-voltage effects. The lower voltage is possible because the UV or IR frequency or other electromagnetic energy is applied to the particles.

It is believed that the present invention also addresses two different limiting physical laws involved in saturation of space-charge-limited current. One type is the saturation of emission of electrons from the negative electrode, and is believed to include the emission of ions from the positive electrode as well. For example, this phenomenon can be observed in a vacuum diode. Generally, the emission rate of elections from the cathode governs a saturation of space- charge-limited current since this emission rate is limited by thermionic emission from a heated cathode. This means that the emission rate seems to reach its maximum value at a certain applied voltage.

A second type of saturation is the saturation of the election density (and the ion density as well) in the plasma sheath region surrounding the electrode. It is believed that this second saturation is more dominant for the asymmetric capacitor case than the first saturation mentioned, because the medium (such as air) is ionized to form plasma by collisions with the parent charged particles.

Below is a brief explanation of a general phenomenon that a plasma exhibits near the surface of a structure (in this case, the surface of the electrode). Plasma tends to shield out its electrical potentials that are applied to it and the edge of this shielding changes based on. the density and temperature of the plasma. The thickness of this shielding is called the "Debye length" and the region inside this plasma shielding is called the "Debye sphere" (not necessarily near the wall) or the "Plasma sheath" for the region near the wall.

The Debye length is proportional to the square root of the election temperature and inversely proportional to the square root of the plasma density. For example: consider a rough estimate of this length using the ion density of 1.0E+15 particles per cubic meter ("#/m ³ ") and the electron temperature of 10 KeV with the result obtained being about 2.3 cm for the Debye length (or thickness of ion clouds). If the plasma temperature, especially of elections, is increased without changing its density, expansion of the Debye length or sheath thickness should be observed. On the other hand, if the plasma density is increased without changing temperature, then the shrinkage of the Debye length or sheath thickness should be observed.

In the plasma sheath, there is a potential gradient due to the difference in the electron and ion velocities. The sheath created on the negative electrode tends to repel the excessive incoming elections and the sheath created on the positive electrode tends to repel the excessive

incoming ions. This shielding results in the steady state of the ion and electron densities inside the sheaths. ^{' " "" "'}

Referring to Figure 2D before describing Figure 2C, Figure 2D shows the volt-ampere characteristic of a Langmuir electrostatic probe as a possible explanation of the change in the saturation that appears to occur from supplying the electromagnetic radiation to the asymmetric capacitor. The current is not to scale correctly, as the actual electron current is much larger (such as three orders of magnitude) than that of ions.

To generate the graph, a voltage applied to a probe (not shown) is varied and the current collected by the probe is measured. Vf is the plasma floating potential (i.e. the probe potential for net zero current) and Vp is the plasma potential. An analogy of this characteristic can be made to the asymmetric capacitor case. Consider the point of Vf as the condition just before the voltage is applied to the system, i.e., zero. If a variable voltage is applied to the system, the following is likely going to happen. At the initial stage, the current increases since both the ion and electron currents increase. This is seen by the line of V-I characteristic from Vf toward B for the negative electrode and from Vf toward C for the positive electrode. When the applied voltage reaches to the point that the potential of the negative electrode becomes -Vf, the ion current reaches its steady state, i.e., ion current saturation. This current is called the "Bohm current." This steady state is reached, although the total current still increases since the electron current is still increasing at the point that the potential of the positive electrode is +Vf, assuming that Vp - 2Vf > 0. When the applied voltage reaches to the point that the potential of the positive electrode becomes Vp, then the total current saturates since the electron current reaches to its steady state. However, if the applied voltage is further increased to the value that the potential drop inside the plasma sheath is greater than the potential energy to ionize atoms, then the current increases abruptly at point D. In some capacitors without the improvements disclosed herein, point D corresponds to a range from 23 kV to 3OkV. Increasing voltage beyond that point does not yield a substantial and corresponding benefit.

Consider two different example asymmetric capacitor performances with different applied voltages, 1 gram/watt for 30 KV as case 1 and 324 grams/watt for HOV as case 2, can be located on the V-I characteristic curve. Case 2 is located at a point somewhere on the curve between Vf and C for the positive electrode and at a point somewhere on the curve between Vf and B for the negative electrode. In some cases, the point could be left from the point B but generally should be symmetric to the point for the positive electrode to achieve larger forces.

^{~" "} " ^" Case 1 is located at a point somewhere "on the saturated electron "current state;" i.e., between C and D for the positive electrode and at the symmetric point to the left for the negative electrode. It is believed that photo-ionization, heating, or a combination thereof using UV, IR or RF or other electromagnetic radiation of O ₂ and N ₂ molecules raises the energy levels 5 sufficiently, to cause one or more electrons to leave the respective atom (herein "ionization") which will ready the particles for manipulation by electrical fields in the same way as similar molecules ionized by high-voltage. Sufficient energy creates a plasma. It is believed that ionization changes the saturation of space-charge-limited current, since it appears that ionization should change the plasma density and change the plasma state inside the sheath. Now, looking at 10 this V-I characteristic curve, ionization will increase the plasma potential Vp as well as Vf. Therefore, the curve will be shifted to the right. This shifting will increase the values of the saturated current. The Bohm current is expressed as

where n ₀ is the background plasma density, e is electron charge, A is the surface area of the

15 probe, K is Boltsmann's constant, T _e is electron temperature, and M is the ion mass. This equation also indicates that the saturated value of the ion current can be increased by increasing plasma density and electron temperature. It is believed that this is also true for the electron current.

Figure 2C is a charged particle schematic diagram of the enhancement of the present

20 invention with electromagnetic radiation illustrating the resulting increased particle density and velocity. The velocity is increased by an increase in energy. Ionization by use of UV and/or IR light can create a weakly ionized (i.e. partial) plasma. Further, UV and/or IR light as a form of electromagnetic radiation can increase the plasma density significantly. In addition to applying

. electromagnetic radiation from an electromagnetic radiation source 20, if some other methods to

25 heat the plasma are applied, the value of the saturated current will further increase. The plasma heating can be performed independently from plasma density increase by an application of electromagnetic radiation of a different frequency by another electromagnetic radiation source 2OA. Advantageously, both plasma density increase and plasma heating can be utilized by using multiple frequencies from sources 20, 2OA. In one embodiment, the sources 20, 2OA can be a

30 single unit capable of radiating multiple wavelengths, or multiple units. Total momentum (p) imparted to neutral particles by transfer from charged particles is the product of mass x velocity (p=mv). Therefore, total momentum transfer to neutral particles (shown in Figure 3 as particles

16α; T6B, 16C) from charged particles 16 in Figure 2c ^' -iasTboflra greater muπberfor greater ^" mass within the region 28 and higher energy due to the temperature increase for greater velocity. There are several methods to add energy to a plasma. One of them is to use radio frequency (RF) electromagnetic radiation. In this method, there can be generally three different frequency ranges to apply: an electron cyclotron frequency, a lower hybrid frequency, and an ion cyclotron frequency. Another approach is to use the method of neutral beam injection into the plasma. In this method, high-speed neutral particles are injected into plasma and these energetic neutral particles become energetic (high speed) ions by losing electrons through collisions with less energetic (low speed) ions, which in turn become low speed neutral particles by receiving those electrons. This method, however, requires a device to create such a highspeed neutral beam and this in turn requires a large power supply. On the other hand, the RF heating of plasma can be achieved by using a magnetron and a power source similar to, for example, a microwave oven.

These mentioned heating methods use external sources. Without those external sources, it is reasonable to expect that some heating of the plasma can be done internally by Ohmic heating and heating by compression due to magnetic pressure in the system. However, Ohmic heating becomes less effective as the plasma temperature increases since the plasma resistivity inversely depends on the ³ / ₂ power of its (electron) temperature. Therefore, it will be very effective to use an external source of heating at this point. After the current in the system increases by this method, then the plasma can be further heated by magnetic compression, because it is expected that quite a strong magnetic field is created in the system at this point. Sequencing or joining these different methods of heating can be a very efficient method of systematic heating.

In at least one embodiment, the present disclosure uses UV and/or IR photo-ionization combined with RF heating. Increasing the plasma density, especially in combination with increasing the plasma energy and therefore velocity and equivalent temperature, using the methods outlined above will enhance the motive force of the system. The increase in the net force 26 (not to scale) is illustrated as larger in Figure 2C compared to Figures 2B, 2A. It is believed that such methods can enhance the motive force by several orders of magnitude. In addition to a medium having particles in which the asymmetric capacitor 2 operates, other gases can be provided to the asymmetric capacitor to supplement the medium or in lieu of the medium. The need for supplementation can occur for example, when the medium is space or other no or low particle media. For example, hydrogen or helium could be used with the

advantages of being independent of the atmosphere, having reduced UV or IR wavelength complexity to a single frequency for the UV or IR photo-ionization, and permitted RF frequency optimization for hydrogen ion temperature increased effect. Further, a combination of gases could be substituted in place of a single gas. Still further, particles such as vaporized mercury or other particles useful to create and maintain propulsive and other forces could be injected into a volume in which the asymmetric capacitor operates.

Figure 3 is a schematic diagram of a motive force of neutral particles momenta experiencing collisions with charged particles. This diagram illustrates the how the neutral particles contribute to the net force with the capacitor. It illustrates the primary force derivation as momentum transfer from charged particles 16 in Figure 2B, 2C to neutral particles 16A, 16B, 16C. Particles 16A with an upward vector have a positive contribution to the upward thrust. Particles 16B with a downward vector have a negative contribution to the upward thrust. Particles 16C with only a horizontal vector have no contribution to the thrust. The net force 5 A on the first electrode 4 is generally downward, the net force 7A on the second electrode 6 is generally upward and the resultant new force on the asymmetric capacitor 2 is the vector sum of forces 5A and 7A to result in net force 26. This force can be related to thrust acting on the physical propulsion unit. Some additional force may derive from ion jets and associated air pumping by redirected charged particles.

In addition, further efficiency can be realized by producing a pulsed power, instead of steady power. The system can pulse the electromagnetic radiation applied to the particles, the voltage applied to at least one of the electrodes, or a combination thereof. Several options exist to produce the pulsed power. Pulsed power can be more efficient, as it decreases the average energy consumption. For example and without limitation, experiments and modeling of a standard asymmetric capacitor powered by -25 kV DC steady state at ~1 mA demonstrate no measurable reduction in force when the applied power is pulsed (-100 Hz timing with -10 ms pulse duration).

Another variation is to control the surface area on one or more of the electrodes by the surface texture, porosity, or openings provided therethrough. For example, the surface area on an electrode can be increased by providing openings through the electrode. Advantageously, the openings can be located in the electrode to assist in affecting the flow of particles into and out of the field between the electrodes.

Further, an oxide or other material can be used to coat the electrodes to increase force by supplying a source of additional particles. The coating can be bombarded with energetic ions and neutral particles and coating particles will be added to the other particles in the plasma.

The asymmetric capacitor can function as an "engine" for a structure coupled to the capacitor or to direct energy emanating from the capacitor. The engine can be used in virtually any field, including without limitation, air, land, space (enhanced by injecting particles into the engine system) and sea vehicles, both manned and unmanned, and virtually any device or system that needs a motive force to move or a volume of energy that can be emanated and directed from the capacitor. Further, the present invention can apply to small items, including nano-sized items and to relatively large items. Another use for the invention is to generate a flow of energy or plasma directed outward from the apparatus.

In at least one embodiment, the asymmetric capacitor has few, if any, moving parts and the engine can be turned off and on at will with little concern for idling as found in typical rotational engines producing motive power. The present invention using the atmospheric air, and/or a discrete medium, such as hydrogen, helium or another medium in the place of atmospheric air, has the characteristics of a "digital" thrust system in that it can be solid state with little to no analog components, such as pumps, ignition systems, fluid fuel control, compressors, turbines and nozzle controls. Electrical energy from fuel cells can be switched to cathode and anode, UV and/or IR solid state light emitting diodes and lasers, and solid state RF emitters. Thrust can be controlled from any value starting at zero to maximum on a timeline commensurate with overall vehicle control system demands. The analog equivalent usually has a sustained starting cycle, and may also have a minimum idle condition and an acceleration timeline significantly longer than overall control system requirements might require. Thus, the asymmetric capacitor with the improvements herein as a motive force engine can be termed a "digital" engine.

Further, the system can include portable power for the asymmetric capacitor 2 and/or the electromagnetic sources 20, 2OA. One method of providing portability is to use chemical-to- electrical power conversion. Such techniques include, among others: fuel cells powered by hydrogen, paraffin, petroleum and other fuels; photon capture or solar panels; artificially enhanced photosynthesis; and genetically modified organisms. Other techniques include solar power, stored energy such as in batteries, controlled fusion or fission, and other sources that can provide a power supply from a fixed location attached to a mobile object using the asymmetric capacitor in the manner disclosed herein. The term "fixed location" is used broadly and includes

for example the ground, a fixed structure, or a structure in motion in a different direction or velocity relative to asymmetric capacitor and any structure coupled to the capacitor.

. Performance prediction, optimization and tuning can be accomplished empirically. Another approach is to use a plasma simulation. Issues related to analysis of this system are highly nonlinear and it appears that a magneto-hydrodynamic (MHD) treatment of plasma is appropriate, because the time evolution of plasma around the electrodes complicates the structure of the electric and magnetic field in a self-consistent way. Since the plasma in this system is a weakly ionized, partial plasma, a two-fluid or three-fluid MHD treatment may be useful to predict performance. The kinetic treatment of plasma is probably not necessary for this issue, because the velocity distributions of electrons and ions are believed to behave as a Maxwellian distribution. However, this treatment can be useful in designing a more practical device in terms of efficiency, upscale, and control, since the energy losses due to radiation, including blackbody, Bremsstrahlung, and impurity radiation, and the micro-instabilities in the plasma that the MHD treatment cannot predict can be considered. Example 1

In at least one embodiment, electromagnetic radiation, such as photonic (including UV and/or IR) and RF energy can be delivered into a volume of the asymmetric capacitor system. The electrodes can be at least partially copper, aluminum, or other conductive material. One or more porous electrodes can be used to increase the total surface and the Bohm current. One or more (such as an annular array of LEDs) electromagnetic radiation sources are attached to locations above the anode, between the anode and cathode, under the cathode or any combination thereof to energize particles between the electrodes (that is at least somewhere in the surrounding fields of the electrodes). A further electromagnetic radiation source can be an RF emitter device using pulsed magnetrons with variable frequency. In some embodiments, 10 kW pulsed magnetrons with variable frequency are preferred. A commercial-off-the-shelf laser or LED array and RF device may be used. Advantageously, the method of attachment of the electromagnetic radiation sources to the asymmetric capacitor allows the sources to treat the plasma uniformly. A commercially available laser uses the 248 nm laser line with high energy femtosecond pulses to ionize air (possibly on the order of 10 ^u #/cm ³ ) and also uses a longer wave length laser (such as a 750 nm infrared laser) to stabilize the plasma. By stabilize, the term is intended to mean that this relatively longer wave length laser reduces or prevents the plasma ^: from neutralizing itself through recombination of the ions. However, the frequency generated from this device needs to be varied in order to heat the surrounding plasma uniformly, because

the electron cyclotron frequency and ion cyclotron frequency depend on-the-magnetic-field- intensity and it is expected that this intensity varies in the system. Waveform modulation of the DC current enhances ionization. Performance tuning is enhanced by variable output current voltage. Figure 4 is a schematic diagram of one embodiment of an asymmetric capacitor engine

100. The components listed are merely exemplary and without limitation. Other components can be substituted, added, or subtracted therefrom. In general, the engine 100 includes an asymmetric capacitor 110, including an anode 112 and a cathode 114, as described above. One or more sources of electromagnetic radiation 120, 122 can be used to provide radiation of one or more wavelengths to particles in a volume in proximity to the electrodes, also as described above. For example and without limitation, the electromagnetic radiation source 120 can include a photonic source of UV or IR light provided by one or more lasers. Similarly and without limitation, the electromagnetic radiation source 122 can include an RF source, such as can be provided by one or more magnetrons. The frequency generated from this device can be varied in order to heat the surrounding plasma uniformly, because the electron cyclotron frequency and ion cyclotron frequency depend on the magnetic field intensity and this intensity varies in the system. A power supply 118 can be coupled to the asymmetric capacitor 110 to provide power to at least one of the electrodes. The power supply 118 can be any suitable power supply capable of delivering the energy to the anode and cathode. The power supply 118 can also provide energy to one or more of the electromagnetic radiation sources 120, 122. Alternatively, the power supply can be multiple units capable of delivering the power to the individual elements. A source 126 of particles can be coupled to the asymmetric capacitor to provide particles in addition to particles in the media in which the engine operates or in lieu of such particles. For example, the source can be a compressed gas cylinder or other storage device for a supply of particles.

Figure 5 a is a schematic diagram of a cross sectional view of one embodiment of a system using the asymmetric capacitor. The engine 100 includes an asymmetric capacitor 110 having an anode 112 and a cathode 114. In one embodiment, the anode can be made from one or more highly porous relatively thin disks, blades, or. wires, compared to the cathode, which generally has a larger surface area. Without limitation, the cathode 114 can be made from a highly porous relatively thick aluminum disk. The level of porosity is determined based on the limit of structural integrity of the system including electrodes, and other considerations such, as stability. The electrode surfaces can be coated with a material such as oxide film or other

coating to further increase performance.

An electromagnetic radiation source 120, such as a laser or LED device can ^~ be ^~ any suitable laser or other device delivering the required wavelength to the particles that are to be ionized. For such particles, exemplary wavelengths could be without limitation in the UV and IR range such as less than or equal to 1024 nm for O ₂ and less than or equal to 798 nm for N ₂ . An electromagnetic radiation source 122, such as an RF heating device, can also be used, as described above.

Further, one or more reflectors 124 can be positioned in or around the area to be ionized. The reflectors can increase the efficiency of the laser device and/or RF heating device by more uniformly photo-ionizing molecules and heating the plasma and by redirecting the energy otherwise dissipated away from the fields of the capacitor. Generally, one or more supports 116a, 116b, 116c, 116d will support the anode, cathode, reflectors, or any combination thereof, either directly or indirectly through other supports being coupled to other surrounding structures, such as an engine case 128. The engine 100 can further be coupled to a larger structure, described below. To facilitate the coupling, one or more engine supports 106 can be used.

A power supply 118 can supply power to the anode 112, cathode 114, electromagnetic radiation source 120 (such as a laser or LED), electromagnetic radiation source 122 (such as an RF source), or any combination thereof. A particle source 126 can be coupled directly or indirectly to the asymmetric capacitor 110 to provide supplemental or primary particles (such as in space) to the capacitor. One or more injection nozzles 126A and/or 126B can direct the particles from particle source 126 to either the intake or volume between the electrodes to provide uniform and controlled particle injection. A power conduit 102 can be provided from a fixed location 104. Alternatively, the power supply 118 can be a portable power supply that is self-contained independent of a fixed location for at least some time period before refurbishing or recharging can be performed.

Figure 5B is a top view schematic of the embodiment shown in Figure 5 A. In at least one embodiment, the anode 112 and/or the cathode 114 of the engine 100 can include one or more openings 136 in order to increase the exit surface area of the particular electrode or electrodes having the openings. The openings can be arranged in a pattern to create a vortex ring or other patterns to enhance the efficiency and resulting force of the capacitor. The openings 136 can allow air or other media in which the cathode or anode operates to pass through the electrodes into the region between the anode, cathode, or both. The increased surface area can provide greater efficiency to the engine 100.

--Figure 6 is schematic diagram of the power budget for one exemplary embodiment-- The- power supply 118, referenced above, can be used to supply power to the asymmetric capacitor through a first power supply portion 130, specifically to the anode and cathode, referenced above. Without limitation, one exemplary wattage range is about 200 watts (W) or greater but such values can be scaled appropriately to optimize performance for the specific application. A second power supply portion 132 can be used to provide power to the laser device or LED array, referenced above. Similarly, one exemplary power range is about 300 W or greater. A third power supply portion 134 can be used to supply power to the RF heating device, referenced above. One exemplary power range can be about 1500 W or greater for this embodiment. The power supply portions can be formed as a unitary power supply or as multiple power supplies. Naturally, other embodiments can have different power budgets and this embodiment is only illustrative.

The disclosure provides for a structure to be coupled to the asymmetric capacitor so that a motive force from the asymmetric capacitor can provide a thrust to the structure. The structure can support equipment, one or more persons or other living organisms, or other items of interest, herein broadly termed "payload."

Figure 7A is a schematic perspective view of one embodiment of an unmanned aerial vehicle (UAV). Figure 7B is a schematic top view of the embodiment of Figure 7 A. Figure 7C is a schematic side view of the embodiment of Figure 7A. The figures will be described in conjunction with each other. The UAV 150 includes a frame 152 coupled to one or more asymmetric capacitor engines 100. Each engine can be in the form of an engine described above with an anode, cathode, and one or more electromagnetic radiation sources such as one or more photon emitter devices (such as lasers) and heating devices or some combination thereof. The UAV also includes various electronics 154 suitable for control of the UAV. In at least one embodiment, power can be supplied to the UAV through a power conduit 102, which can be coupled to a remote power supply such as on ground level or other fixed location 104. In some embodiments, the power supply 118 can be provided on the UAV itself. The UAV also includes sensors 156, 103 to accommodate image, electromagnetic, and data capture for processing and display. Advantageously the UAV 150 can include three engines, although more or less engines can be used. The three engines assist in providing planar control, such as pitch, roll, and perhaps yaw, of the UAV.

^'" One advantage of the UAV and other items powered by the engine lOO isTfteTTelatively ^"" low acoustic, electromagnetic, and/or radar cross-section signature. This feature can be particularly useful for certain vehicles and craft.

Naturally, other embodiments could include manned aerial or ground hover vehicles, and 5 guided vehicles, as well as a host of other items on land, in or under the sea, or in the air, or in space. The present invention creates a universal motive force system, generally used for propulsion. The invention can also generate a flow of energy or plasma directed outward from the apparatus. In one embodiment, the engine has no moving parts and can reduce total cost of ownership including acquisition and maintenance costs.

10 In at least one embodiment, some exemplary design characteristics are variable and extensive range; variable speed and high speed capability; low acoustic, electro-magnetic and RCS signature; variable pulsed power supply, in the range of about 120-160+ VDC or VAC, 1.6-16+ A, -2+ kW; and low maintenance due to few if any moving parts with some light maintenance to the nodes due to erosion.

15 Figure 8 A is a schematic perspective view of one embodiment of a manned aerial vehicle

(MAV) 170. Figure 8B is a schematic front view of the embodiment of Figure 8 A. The figures will be described in conjunction with each other. The MAV can also be used as a ground hover vehicle. The MAV 170 generally includes a frame 172, a subframe 174, and one or more engines 100 coupled thereto with appropriate controls. The frame 172 is generally shaped and

20 sized for one or more persons. The ergonomics can vary and in at least one embodiment can resemble an aircraft flight seat. The subframe 174 is formed of structural elements and is coupled to the frame 172. The subframe 174 can provide support for the one or more engines 100 coupled to the MAV 170. The engines can be mounted at various elevations, such as below or above the frame 172 or at an elevation therebetween. In some embodiments, a higher

25 elevation may provide greater stability by having a lower center of gravity of the pay load.

Although the number of engines can vary, advantageously multiple engines 100 can provide positional control for the MAV 170. In at least one embodiment, the engines 100 can tilt in one or more axes relative to the subframe 174 to create a variety of thrust vectors having a magnitude and direction. Such tilt can be automatic or manual.

30 The positional control can be done automatically, manually, or a combination thereof.

For example, a controller 176, such as a "joystick," can provide planar control, such as pitch and roll control. A controller 178 can provide yaw control and be actuated by an operator's feet on the MAV 170. The controllers. can include the necessary electronics, cabling, control wires, and

other components as would be known to those with ordinary skill in the art Further, the MAV_ 170 can include a power controller 180 to control the power to the one or more engines 100. Further, control of the MAV 170 can be augmented using gyroscopes or other stability control systems. In some embodiments, the MAV 170 can also include a recovery chute 182. The recovery chute can be applied in an emergency for the safety of the person or persons on the MAV.

Figure 9A is a schematic top view of another embodiment of the present invention using an asymmetric capacitor engine. Figure 9B is a schematic side view of the embodiment shown in Figure 9A. The figures will be described in conjunction with each other. The system can further include a vehicle 148 that can be a plurality of shapes, including geometric shapes, such as circles, ellipsis, squares, rectangles, as well as various irregular shapes. The vehicle 148 can include a communication system 158 and a payload 160. The payload 160 can vary, depending on the purposes of the vehicle. For example, a reconnaissance vehicle could include various sensors as part of the payload. The payload 160 can further be retractable for different operations when traveling or in use.

For reference and further description in the following drawings, a longitudinal axis 162 is defined through the outer extremities of the vehicle 148. For a round, symmetrical vehicle such as shown in Figs. 9A, 9B, the longitudinal axis would be across its diameter. A body normal axis 164 is defined through the vehicle 148 in a relatively perpendicular path to a longitudinal axis 162. Generally, the body normal axis will extend through a central portion of the vehicle, particularly symmetrical vehicles. Because a round body by definition has a single diameter that can be drawn at any orientation around the body from the body normal axis, a round vehicle has a theoretically infinite number of longitudinal axes. For the exemplary embodiment shown in Figures 9A, 9B that can be used in an air medium for flight, the body normal axis can generally be aligned with an earth normal axis, although it is understood that the orientation of the vehicle, such as pitch, roll and yaw, can change that alignment. Further, a radial axis 166 is defined as a line circumferential to the vehicle body about an axis, such as the body normal axis, and is used to indicate angular orientations of the vehicle or portions thereof relative to the axis. Further, the radial axis can be used to indicate angular orientations of some reference point on the vehicle relative to a fixed datum, such as the ground. When the angular orientation is given relative to a line of flight, the angular orientation is known as "yaw" in aerodynamic terms. The angular orientation can be expressed in degrees or radians.

^" Similar terminology is used herein for elongated vehicles. ^' For such ^' vehicles, The longitudinal axis 164 would generally be a major axis, such as between a nose and a tail. A lateral axis would be a minor axis, such as across the width. The body normal axis is generally at the intersection between the longitudinal and lateral axes. The radial axis is generally a circle circumscribed about the outer perimeter of the vehicle relative to a reference axis, such as the longitudinal, lateral, or body normal axis. At any given angular orientation relative to a particular reference axis, a radial plane is defined as being orthogonal to a reference axis or to a combination of axes where orthogonal means relating to or composed of right angles to the reference axis or axes, so that a force having a force component acting in the radial plane would act in a radial direction relative to the reference axis or axes.

An asymmetric capacitor engine 100 can be coupled to the vehicle 148. In some embodiments, the engine 100 can be disposed near a periphery of the vehicle. The engine can extend substantially continuous around the periphery, or can be divided into portions around the periphery, or can be located at other locations more central to the vehicle. The location of the engine and engine components can be located at various portions as can be appropriate for the particular design. One or more controllers can be used to navigate the vehicle, and can be automatic, manual, or remote controlled. It is believed that an engine disposed toward a periphery provides greater control for rapid movement, although such locations can vary, depending on the shape of the vehicle, the function of the vehicle, and the various thrust components from the engine. The engine 100 can include one or more anodes and one or more cathodes with one or more EMR sources. In at least one embodiment, and as described below, the engine 100 can include a series of anodes, cathodes, EMR sources, or a combination thereof that can be selectively energized to provide vectored thrust components corresponding with the radial and normal axes. The forces generated from the engine(s) can have force components in the various orthogonal directions (generally referenced as "x-y-z axes") for each engine and a resultant force for the vehicle in general. For illustrative and non-limiting purposes, the engine shown in Figure 9a is distributed around the vehicle and the forces and force components will be described in reference to the body normal axis 164. However, it is to be clearly understood that the forces can act and be described in reference to other axes, as would be understood by those with ordinary skill in the art given the teaching provided in this disclosure and thus are not limited to the normal axis.

While the shape of the vehicle can vary as has been described above, in at least one embodiment, a lenticular shape may be used in that the vehicle may have a circular shape with tapering periphery. The asymmetric engine 100 can be disposed around the circular periphery with a greater cross-section in a central portion for carrying a payload. The lenticular vehicle 5 can provide inherent directional stability by actuating various combinations of an anode/cathode/EMR source of the engine. The vehicle 148 can be launched from the ground or other surface. It may particularly be launched from a rotary aircraft such as a helicopter or other aircraft for various functions, including surveillance, payload delivery, recovery assistance, and other uses. In at least one aspect, an aerial launch concept could be based on a concept similar to

10 "throwing a Frisbee" to provide stability and velocity of the vehicle as it exits from the airborne aircraft that might have countervailing turbulence. A spinning vehicle can provide gyroscopic inertial stability during the time required to clear the turbulence, as the engine responds and stabilizes the vehicle for flight purposes. The lenticular vehicle has a further advantage in that it does not require banking to change headings, or require changing pitch to change altitude. It

15 simply turns, climbs, or descends by energizing various portions of the asymmetric capacitor engine 100. The vehicle can also have a low observable signature for radar, thermal, and visual tracking. The vehicle can further be stabilized under gusting conditions or countervailing turbulence by monitoring changes in the pitch and yaw of the vehicle in energizing different portions of the asymmetric capacitor engine in response. Further, the vehicle can include a

20 plurality of the multi-directional cathode configurations described in reference to Figures 13 and 14, exclusively or in combination with the single cathode arrangements, described, in Figure 10. The multi-directional cathode configurations can provide additional positive and negative pitch control. Still further, the vehicle can itself create a rotation about the body normal axis for gyroscopic inertia by energizing one or more portions of the asymmetric capacitor engine at an

25. angle to a radial plane relative to a body normal axis to create a thrust vector at an angle δ having a radial force component, as shown in Figures 12A, 12B. For example, the gyroscopic inertia can be advantageous to stabilizing the vehicle during recovery efforts by an aircraft creating turbulence. As a further enhancement to the operation of the vehicle 148, various sensors for movement can be included. The sensors can provide guidance for confined spaces. For

30 example, echolocation and optical spatial tracking in three dimensions can be provided to an autopilot so that the vehicle can enter and maneuver in irregular areas. Such areas can include corridors, stairs, rooms, wells, shafts, caves, and other confines.

Figure- 10-is -a-partial schematic cross-sectional view of the embodiment- shown-in-Figure-

9A. The vehicle 148 can be coupled with the asymmetric capacitor engine 100 that includes one or more asymmetric capacitors and one or more EMR sources directed to the one or more asymmetric capacitors. The asymmetric capacitor 110 includes a plurality of electrodes having different surface areas, such as one or more anodes 112 and one or more cathodes 114. The asymmetric capacitor 110 can be mounted at an angle γ relative to the normal axis 164. The alignment of the Gauss lines surrounding the asymmetric capacitor 110, as described above, yields a vectored resultant force at the angle γ, as describe more fully in reference to Figures 1 IA and 1 IB, generally aligned along an axis 142 between the centers of the surface areas. Figure 10a is a schematic diagram of the vehicle in Figure 10 having a body normal axis generally aligned with an earth normal axis. Figure 10b is a schematic diagram of the vehicle in Figure 10 having a body normal axis at an angle to the earth normal axis. The figures will be described in conjunction with each other. The angle γ of the thrust vector relative to the body normal axis 164 shown in Figure 10 can help provide inherent stability to the vehicle as it moves and pitches, rolls, and/or yaws. In Figure 10a, the vehicle body normal axis 164 is aligned with an earth normal axis 144, that is, the angle σ shown in Figure 10b is approximately zero. Exemplary thrust vectors 140a, 140c are shown at the angle γ relative to the body normal axis 164, and relative to the earth normal axis 144 due to the alignment between the body normal axis and the earth normal axis. The thrust vectors 140a, 140c have equal force components with respect to the body normal axis and the earth normal axis.

If by displacement or gust response, the body normal axis 164 deviates from the earth normal axis 144 by an angle σ as shown in Figure 10b, the thrust vector 140a is now inclined at an angular value of (γ - σ) relative to the transposed earth normal axis 144', while maintaining its angle γ relative to the body normal axis 164. The force component aligned with the earth normal axis is greater at the smaller inclined angle (γ - σ) compared to the original angle γ and creates a greater force in the direction of the earth normal axis. In contrast, the thrust vector 140c now has an angular value of (γ + σ) relative to the transposed earth normal axis 144", while maintaining its angle γ relative to the body normal axis 164. The force component aligned with the earth normal axis is smaller at the greater inclined angle (γ + σ) compared to the original angle γ and creates a reduced force in the direction of the earth normal axis. The relative force components of the thrust vectors 140a, 140c creates a righting moment for the body normal axis 164 to become coincident to the earth normal axis 144.

The asymmetric engine can be a pair of asymmetric electrodes having an anode and- a cathode or can be a plurality of anodes and/or cathodes. The engine can further include one or more EMR sources to supply EMR energy to facilitate creating a plasma environment around the electrodes. Advantageously, various portions of the engine can be energized to create different forces at different locations in the orthogonal directions. For example, voltage can be applied to one or more of the electrodes and the force generated from the portions of the electrodes can be magnified by applying the EMR energy to those portions. This mode of operation can be particularly useful when one or more of the electrodes is relatively larger than the EMR source that allows a focused application of the EMR to portions of the asymmetric capacitor. In at least one example, the vehicle 148 can include an anode and a cathode surrounding the periphery or some portion thereof and the EMR source can be divided into discrete EMR sources for the anode/cathode combination to provide forces at various locations of the vehicle. Likewise, the engine can include multiple anode/cathode combinations in different portions of the vehicle, such that specific combinations can be energized and the EMR source applied thereto to provide the forces at the various locations.

In keeping with the description herein, the asymmetric capacitor can be energized by a power supply 118. In at least one embodiment, the power supply can include a battery source, such as nickel cadmium batteries, nickel halide batteries, fuel cells, and other portable energy sources. Also, as described herein, one or more EMR sources 120, 122 can be used to create the plasma environment in conjunction with the asymmetric capacitor 110. Further, the engine 100 can include a row or series of EMR sources 120, 122 disposed around the periphery as discrete sources capable of independent actuation in conjunction with the one or more asymmetric capacitors. The one or more EMR sources 120, 122 can be radially disposed in the embodiment inboard and outboard of the asymmetric capacitor 110 along the radial axis 166, shown in Figure 9a. In at least one mode of operation, the EMR source can vary the EMR to the asymmetric capacitor by varying the EMR pulse width, that is pulse-width modulation, to control the amount of force generated through the asymmetric capacitor 110 and the overall engine 100. In another mode, the voltage can be varied to the electrodes, and still further the pulse width of the EMR and the voltage can be varied in combination. The modulated EMR pulse width can provide a response significantly greater in rate of generation and magnification of the force from the asymmetric electrodes compared to simply varying the voltage to the electrodes.

Figure 1 IA is a partial schematic cross-sectional view of the embodiment shown in Figure 10 as seen from the body normal axis 164 looking toward the vehicle periphery, such as

" ^"~ SOtne" portion" of the vehicle marked in Figure 9a. Figure li.A ^~ illustrates"Orre ^" orτnore ^~ anOdes7 cathodes, and/or EMR sources. For clarity, discussions about Figures 1 IA-I IB, and subsequently Figures 12A-12B, will be kept to two dimensions. However, it is to be clearly understood that the forces act and can be described in reference to three orthogonal axes, as would be understood by those in the art given the teaching provided in this disclosure and thus are not limited to two axes.

In one embodiment of the asymmetric engine 100, an array of one or more anodes, cathodes, and EMR sources can be arranged about a periphery of the vehicle 148, shown in Figures 9A ₃ 9B, 10. The number of components, spacing arrangements, and location can vary and the illustrated embodiment is to convey the concept of using one or more anodes, cathodes, EMR sources, or a combination thereof, to control the thrust vectors in magnitude and direction to propel the vehicle 148. The asymmetric engine 100 will generally have at least one anode and at least two cathodes, where the cathodes are at angles to each other relative to the anode. The anode and cathodes can be in different asymmetric capacitors of the asymmetric engine or can be in an asymmetric capacitor having multiple anodes and/or cathodes.

In at least one embodiment, one or more anodes 112A, B, C can be selectively energized. Similarly, one or more cathodes 114A, B can be selectively energized, as well as one or more EMR sources 122A, 122B. Energizing one or more of the various anodes, cathodes, and/or EMR sources can vary the thrust vectors generated by the asymmetric engine 100 in magnitude, direction, or both.

Further, the one or more anodes, cathodes, and EMR sources can be staggered at different locations, so that selective actuation can produce variations in the thrust vectors. In the illustration shown in Figure HA, the thrust vector 140 is produced substantially in alignment with the body normal axis 164 by selectively energizing an asymmetric capacitor and an EMR source coupled with the asymmetric capacitor, or portions thereof. The thrust vector 140 in the upward direction illustrated in Figure 1 IA would correspond to a lifting force for the vehicle 148 coupled to the engine. For maximum thrust, all anodes and cathodes and EMR sources could be energized. For throttled thrust, and various controlled directional thrusts, one or more combinations of the one or more anodes, cathodes and/or EMR sources can be energized. For example, anodes 112A, B, C can be energized in conjunction with cathodes 114A, 114B. At the same time, anode 112M, cathode 114M, and EMR source 122B may not be energized (that is, neutral). Depending on the location of the energized anode, cathode and/or EMR source, the performance of the vehicle 148 can be affected in pitch, yaw, roll, acceleration, deceleration, and

_ constant velocity. In at least one embodiment, the portions _, or "sectors" of combinations of one or more anodes, cathodes, and/or EMR sources can be divided up into approximately three degrees of arc around the periphery of the vehicle 148. Naturally, other combinations and sector sizes can be made. Similarly, if the asymmetric capacitor were constructed such that various EMR sources could create a plasma at different portions of the asymmetric capacitor, then the asymmetric capacitor could be generally energized with voltage and the various EMR sources selectively energized to control the thrust vectors generated by the asymmetric capacitor portions and the force from asymmetric capacitor overall. One such embodiment could include an asymmetric capacitor substantially around the entire periphery of the vehicle 148. Alternatively, one or more asymmetric capacitors could occupy significant portions of the overall asymmetric capacitor engine, such as 15% or more of the periphery, including dividing into thirds or fourths. Smaller EMR sources could focus on portions of the asymmetric capacitor(s). The asymmetric capacitor(s) could be energized, including around the periphery, and the EMR sources could control the force generated by specific portions of the asymmetric capacitor or portions thereof while the asymmetric capacitor(s) remain energized.

Figure 1 IB is a schematic diagram illustrating force components of the thrust vector shown in Figure 1 IA. The thrust component will generally be in the direction or orientation of a line through the centers of the electrodes' surface areas of the asymmetric capacitor. For example, in Figure 10, the anode and cathode are arranged at an angle γ to the normal axis 164. Thus, as shown in Figure HB, the thrust vector 140 would generally be at the angle γ to the normal axis, but generally aligned in the plane 168, which itself is aligned with the body normal axis, due to the alignment of the asymmetric engine and the energized anodes and/or cathodes. The thrust vector could be conceptually separated into force components, as is known to those with ordinary skill in the art, to provide a first force component 165 generally aligned with the body normal axis 164 and a second force component 167 in the plane 168 generally perpendicular to the first force component. The magnitude of the force components vary according to the magnitude of the thrust vector 140 and the angle γ.

The thrust vector at angle γ, shown in Figure HB, can be altered by changing the physical orientation of the anode/cathode. Depending on the location of the particular asymmetric capacitor or portion thereof and the desired thrust vector direction, different angles can be used in different portions of the vehicle. For example and without limitation, more centrally disposed asymmetric capacitors can be aligned at a smaller angle γ and other

asymmetric capacitors or portions disposed toward a periphery of the vehicle can be aligned at a greater angle γ. Other variations are certainly possible including aligning asymmetric capacitors or portions thereof with other axes, such as a longitudinal or lateral axis, or a combination thereof. Figure 12A is a partial schematic cross-sectional view of the asymmetric engine shown in

Figure HA, illustrating a thrust vector directional change. Figure 12B is a schematic diagram illustrating force components of the thrust vector of Figure 12A. The figures will be described in conjunction with each other. This schematic illustrates how the thrust vectors can be varied by energizing a variety of anodes, cathodes, and/or EMR sources, such as shown and described in reference to Figure HA. In Figure 12A, anodes 112A ₅ B, C are energized as were described above for Figure HA. However, additional cathodes can be energized and include 114A, B, C, D. Because the geometric shift in energized components causes a variance in the directional flow of the electrons and particles in the Gauss lines, such as those shown in Figure 1, the thrust vector 140 in Figure 12B can be directed at a different angle δ with respect to the plane 168 than the thrust vector 140 shown in Figure HB. Stated differently, the thrust vector 140 has a zero angle δ in Figure HB because it exists in the plane 168 and a non-zero angle δ in Figure 12B, because it has a radial component orthogonal to the plane 168.

The various force components from the thrust vector can be illustrated in referenced to Figure 12B as an exemplary and non-limiting thrust vector. For reference, the force components are described relative to the body normal axis, although it is understood that other axes can be referenced as appropriate. The thrust vector 140 has a force component 165 aligned with the body normal axis 164 and a force component 169 perpendicular to the body normal axis, that is, in a radial direction. Referring briefly to Figure HB, another force component 167 is aligned with the plane 168. Thus, by extension, the force component 169 in Figure 12B would be in a radial direction orthogonal to the plane 168. The various forces and their components can be directed to control the vehicle in its translational and/or rotational movements.

Other energized combinations can be made, including fewer or greater number of anodes and/or electrodes. Similarly, the plasma environment can be affected and, therefore, the magnitude and direction of the thrust by energizing a variety of EMR sources relative to the energized anode/cathode combinations.

. Figure 13 is a schematic diagram of another embodiment of the asymmetric capacitor engine having a multidirectional thrust capability. In at least one embodiment, the multidirectional capability, such as a reversing thrust capability, can be accomplished by

supplementing an anode/cathode with an additional cathode distal from the first cathode. JFor_ example, an anode 112 can be disposed between cathodes 114, 114' or at some angle to the cathodes. Stated differently, using a line between the anode and one of the cathodes, the other cathode can be disposed at some angle relative to that line, so that the cathodes are disposed at an angle to each other relative to the anode. The angle θ will be greater than 0° and less than 360° in at least two dimensions. A power supply 118 can provide power to all or some combination of the anode/cathode arrangement and can, itself, include subcomponents for varying the power input to each of the anode/cathodes. As described above, the force generated from the asymmetric engine 100 can be enhanced by providing the EMR sources 120A ₅ 122A between the anode 112 and the cathode 114. Similarly, a plasma environment can be created and/or enhanced between the anode 112 and the cathode 114' by utilizing one or more EMR sources

120B, 122B. In some embodiments, the EMR sources 120A, 120B can be combined into a single unit as can be EMR sources 122 A, 122B for energizing the plasma environment around the anode/cathode combination shown in Figure 13. As a further illustration, the energy input to anode 112/cathode 114' combination can be varied relative to the energy input into the anode 112/cathode 114 combination. For example, in an exemplary operating regime, it may be advantageous to provide more energy to the anode 112/cathode 114 combination than the anode 112/cathode 114' combination. To amplify the produced force, one or more of the EMR sources 120A, 122A can be more directed toward the anode 112/cathode 114 combination. Other cathodes can be coupled with the anode to further vary the thrust vectors generated by the various anode/cathode combinations, and the exemplary embodiment of two cathodes with the one anode is merely illustrative of the concept that allows different thrust vectors from the asymmetric capacitor engine without necessarily physically moving the various components. It is believed that the various thrust vectors from the different anode/cathode combinations can generally react more quickly than physically moving the various components to accomplish a similar change in thrust direction.

Figure 14 is a partial schematic cross-sectional view of a vehicle having an asymmetric engine 100 with a multi-directional thrust capability illustrated in Figure 13. The asymmetric capacitor 110 can include the anode 112 with the cathodes 114, 114'. Similar to the illustration in Figure 10, one or more EMR sources 120, 122 can be provided to enhance the thrust generated by the asymmetric engine 100. A power supply 118 can provide power to the engine. The magnitude and the direction of thrust 140 can be varied by energizing either the combination of the anode 112 with the cathode 114 or the anode 112 with the cathode 114' and various EMR

- — sources 120, 122. If the anode 112/cathode 114-combination is- energized— the-thrust vector is generally upward. If the anode 112/cathode 114' combination is energized, the thrust vector is in changed to a different direction, that is, generally downward in the illustration. The magnitude of either thrust vector can be varied by the amount of input into either of the combinations. 5 Further, in at least one embodiment, the mounting angle of the asymmetric capacitor UO can change the radial thrust component depending on the angle γ, described in Figures 10, 14 for example, or angle δ, described in Figures 12A, 12B, or a combination thereof.

Figure 15A is a schematic top view diagram of one embodiment of a vehicle illustrating various thrust locations for moving the vehicle. Figure 15B is a schematic diagram illustrating 0 various thrust vectors on the vehicle shown in Figure 15A for acceleration. Figure 15C is a schematic diagram illustrating various thrust vectors on the vehicle shown in Figure 15A for constant velocity. Figure 15D is a schematic diagram illustrating various thrust vectors on the vehicle shown in Figure 15A for deceleration. The figures will be described in conjunction with each other. These figures illustrate various modes of operation for the vehicle 148. The 5 asymmetric capacitors (or portion thereof) 11 OA-D shown in Figure 15A are representative only of various exemplary locations of asymmetric capacitors used to generate the thrust vectors or portions of one or more asymmetric capacitors that are energized and/or radiated from the EMR sources to produce the thrust vectors.

As one mode of operation, the vehicle can be accelerated to the right as shown in the 0 figures by applying a greater amount of thrust to the right than is required under constant conditions. For illustrative purposes and without limitation, the thrust vector 140A could be formed by energizing one or more anodes, cathodes, and/or EMR sources associated with an asymmetric capacitor (or portion thereof) HOA disposed at an angle γ, referenced above. Thus, the thrust vector 140A could be aligned with the body normal axis 164, such as in the plane 168 5 in Figure 1 IB, as viewed from the left of the vehicle toward the body normal axis of the vehicle.

Other combinations of anode/cathode/EMR sources could be energized that would be at angles to the direction of movement, such as at asymmetric capacitors (or portion thereof) HOB,

HOD. To generate a thrust vector 140B at the asymmetric capacitor 11OB, one or more anodes, cathodes, and/or EMR sources could be energized to create an angular thrust vector at an angle δ, 0 such as illustrated and described in reference to Figures 12A, 12B. Further, the thrust vectors can act at an angle δ, described above, by the asymmetric capacitor in that portion of the vehicle being aligned initially at that angle, if desired. Other asymmetric capacitors could be aligned in other angles in that portion of the vehicle to be energized for different modes of operation.

The thrust vectors 140A, 140B would generally also produce a- lifting-force that would- create an upward pitch on the left side of the vehicle 148, as viewed in the perspective of Figure 15B. To offset the upward pitch on the vehicle, an asymmetric capacitor HOC could be energized to create an offsetting thrust vector 140C to change the pitch, if desired. The thrust vector 140C could be aligned in its respective plane, such as the plane 168 shown in Figure 1 IA, relative to the body normal axis 164 as viewed from the right of the vehicle. When viewed from the right, the thrust vector 140C could be similar to the thrust vector 140 illustrated in Figure HA.

It is apparent that by altering the thrust vectors' magnitude and/or direction, the thrust vectors can also create a spinning motion to the vehicle. Such spinning motion can be used at times to provide gyroscopic inertial stability.

For constant velocity where the forces on the vehicle are more constant, the thrust vectors could be varied in magnitude and direction as shown in Figure 15C. For example, the thrust vector 140B could be aligned in its respective plane relative to the body normal axis 164 and thrust vectors 140A and 140C, while having a force component opposite each other, could be aligned with the normal axis 164 in each of their respective planes, so that the various thrust vectors from their relative perimeter positions viewed toward the normal axis 164 could appear as the thrust vector 140 shown in Figures 1 IA, 1 IB. Each thrust vector could vary in magnitude, for example to hover, ascend or descend vertically, or maintain a constant lateral velocity in a particular direction.

In a deceleration mode, the tiirust vectors could apply greater thrust against the direction of movement than under constant conditions to act as a "brake" for the vehicle. For example, thrust vector 140C could still be aligned with the body normal axis 164 in its plane but could, upon certain applications, have a greater magnitude than, for example, the thrust vector would have in Figures 15B, 15C. Further, the thrust vector 140B could be created at an angle δ relative to its respective plane, such as described in reference to Figure 12B. To control the pitch, the thrust vector 140A could be used having a force component opposite that of the thrust vectors 140B, 140C.

Various basics of the invention have been explained herein. The various techniques and devices disclosed represent a portion of that which those skilled in the art of plasma physics would readily understand from the teachings of this application. Details for the implementation thereof can be added by those with ordinary skill in the art. The accompanying figures may contain additional information not specifically discussed in the text and such information may be

described in a later application without adding new subject matter. AdditipnaUy _^ xarious combinations and permutations of all elements or applications can be created and presented. All can be done to optimize performance in a specific application.

The term "coupled," "coupling," and like terms are used broadly herein and can include any method pr device for securing, binding, bonding, fastening, attaching, joining, inserting therein, forming thereon or therein, communicating, or otherwise associating, for example, mechanically, magnetically, electrically, chemically, directly or indirectly with intermediate elements, one or more pieces of members together and can further include integrally forming one functional member with another. The various steps described herein can be combined with other steps, can occur in a variety of sequences unless otherwise specifically limited, various steps can be interlineated with the stated steps, and the stated steps can be split into multiple steps. Unless the context requires otherwise, the word "comprise" or variations such as "comprises" or "comprising", should be understood to imply the inclusion of at least the stated element or step or group of elements or steps or equivalents thereof, and not the exclusion of any other element or step or group of elements or steps or equivalents thereof.

Further, any documents to which reference is made in the application for this patent as well as all references listed in any list of references filed with the application are hereby incorporated by reference. However, to the extent statements might be considered inconsistent with the patenting of this invention such statements are expressly not to be considered as made by the applicants).

Also, any directions such as "top," "bottom," "left," "right," "upward," "downward," and other directions and orientations are described herein for clarity in reference to the figures and are not to be limiting of the actual device or system or use of the device or system. The device or system may be used in a number of directions and orientations.

REFERENCES

1. Szielasko, Klaus, High Voltage "Lifter " Experiment: Biefeld-Brown Effect or Simple Physics?, Genefo, April 2002.

2. Stein, William B., Electrokinetic Propulsion: The Ionic Wind Argument, Purdue University, Energy Conversion Lab, September 5, 2000.

3. Bahder, Thomas B. and Bazi, Chris, Force on an Asymmetric Capacitor, Army Research Laboratory, September 27, 2002.

4. Bahder, Thomas B. and Bazi, Chris, Force on an Asymmetric Capacitor, Army Research Laboratory, March 2003.

5. Bilen, Sven, G., Domonkos, Mathew T., and Gallimore, Alec D., 7?2e Far-Field Plasma Environment of a Hollow Cathode Assembly, University of Michigan, AIAA Conference, June 1999.

6. Canning, Francis X., Melcher, Cory, and Winet, Edwin, Asymmetrical Capacitors for Propulsion, Glenn Research Center of NASA (NASA/CR-2004-213312), Institute for Scientific Research, October, 2004.