Electrodynamic field generator

Details Electrodynamic field generator Electrodynamic field generator

2000-07-21

2002-06-11

Nguyen, Tran (Department: 2834)

Electrical generator or motor structure

Dynamoelectric

Rotary

C290S00100C, C290S00100C, C244S02300R, C244S02300R

Reexamination Certificate

active

06404089

ABSTRACT:

FIELD OF THE INVENTION
The present invention is related in general to rotary direct current (DC) electrical generators which incorporate permanent magnet fields, and in particular to similar electromechanical generating devices whose principal purpose is to produce a useful continuous high-voltage DC corona discharge. This invention also pertains to the field of aerospace vehicles which are capable of propulsion through the utilization of an ultra-high-voltage corona or arc discharge of a special type and form.
DESCRIPTION OF RELATED ART
In order to provide background information so that the present invention may be completely understood and appreciated in its proper context, reference is made hereinbelow to a number of related art patents. These cited references contain certain similarities to the present invention, primarily related to the objective of producing electrically-developed thrust. However, key differences and limitations with regard to achieving this objective are in evidence.
The related art disclosed in U.S. Pat. No. 2,949,550 proposes three attendant objects which are quite similar to certain of the objects of the present invention: (i) to provide an apparatus for the direct conversion of electrical potential to usable kinetic energy; (ii) to provide such an apparatus having a hollow body or housing which contains a source of high electrical potential; and (iii) to provide a self-propelling vehicular apparatus which includes a pair of electrically conductive body portions joined by an insulative portion, whereby said conductive portions constitute electrodes. A further similarity is that the vehicular embodiment proposed preferably be of a circular disc shape somewhat thicker in its center than at its edges. The device set forth in this Patent just cited is noticeably different from the present invention, however, in that a positive voltage is applied to the housing periphery and a negative voltage is applied at the central axis. The proposed arrangement is furthermore limited to operation within a gaseous dielectric medium, upon which it is reliant for the production of the claimed motive force, and is to be operated at a potential gradient less than that which would produce a visible corona. This device moreover makes no provisions for the production and/or extraction of vast quantities of useful thermal kinetic energy, as the present invention does.
The related art disclosed in U.S. Pat. No. 3,071,705 is based on three empirical principles of electrostatics which also figure prominently in explaining the actual shape of the discharge current field that will be produced by the present invention: (i) electrostatic lines of force tend to concentrate on the surface of a charged conductor in those places with the smallest radius of curvature; (ii) they are normal to the surface from which they emanate; and (iii) they do not cross but will bend under the influence of another charged body. The device set forth in this Patent just cited is in fact quite similar to that of the Patent cited immediately before, in that relatively massive positive atmospheric ions and entrained neutral air molecules are repelled from the positive electrode toward the negative electrode along a linear axis—thereby inducing an air flow or “electric wind” which represents the fundamental source of thrust. It is therefore once again limited to operation in a gaseous dielectric medium, and does not make use of a flow of negative and greatly less massive electron current in the course of thrust production—which may achieve comparatively enormous acceleration and even relativistic velocity and specific impulse at a similar given level of applied potential gradient—as the present invention does.
The related art disclosed in U.S. Pat. No. 3,177,654 actually addresses the issue of producing electrically-developed thrust which is not limited to atmospheric operation, and the stated primary object thereof is to provide a propulsion system for enabling controlled flight in the atmosphere which may continue extensively into space without changing the system's basic operation. One embodiment thereof also proposes a circular disc-shaped vessel wherein high-voltage electrode elements ionize atmospheric gases by corona discharge, and a pulsed electromagnet arrangement causes the ejection of the resultant plasma from the propulsion chamber—producing thrust by reaction. This device furthermore addresses the issue of producing local thrust differential(s) on the body or housing thereof, for purposes of flight maneuvering and/or directional control, by providing for a plurality of such pulsed discharge propulsion units arranged in concentric rings (within the discoid body) and having individual divergent nozzles. As such, however, the device set forth in this Patent just cited actually constitutes an ionized jet propulsion method, requiring the use of either a gaseous medium like air or the onboard storage and release of relatively massive ionizable reaction material for any operational capability in space. Moreover, the pulsed mode of operation used, which limits the ionizing potential gradient to a value of less than breakdown field intensity, significantly restricts the level of power produced as thrust as compared to the continuous DC discharge field current produced by the present invention—at voltages which may be greatly in excess of breakdown intensity. Finally, this said device relies upon an unspecified source of generated electrical power in operation which must be assumed would have to be nuclear if conventional in nature, for said device to avoid otherwise having to carry a massive and range-limiting onboard store of fuel, and not upon convenient and protracted-use permanent magnets of high energy density as the prime energy source (as the present invention does).
U.S. Pat. No. 3,464,207 discloses a quasi-corona aerodynamic vehicle which bears only a limited relationship to the present invention, but which is referenced nonetheless as being further indicative of the predominant trend in conceptualization in relation to devices intended for producing electrically-developed thrust. This device also relies upon pulsed corona discharge operation between spaced electrodes at less than breakdown field intensity, thereby greatly constraining the propulsive power obtained. It is furthermore effective only in a gaseous dielectric medium and is based upon an electric wind pressure gradient arising of an admitted incompletely-understood mechanism. This same device evidences a great deal of theoretical complexity and construction material specificity, which might seem to indicate a narrow range of feasibility. Such attributes are not uncommon in the field of electrical aerospace propulsion, and are, to a degree, shared even by the present invention. Nevertheless, it is interesting to note that sizeable thrust in the form of an aerodynamic pressure gradient or lift of up to 30 lbs./ft
2
of external electrode area or more is asserted to be obtainable from said same device by utilizing asymmetrical electrodes or electrode arrays, rather than using electrodes or electrode arrays of approximately equal area (as the present invention does)—which therefore present a uniform cross section of discharge current conduction.
PCT Application WO 85/03053 discloses a flying apparatus whose primary similarity to the present invention is that it incorporates a hollow annular flywheel which provides gyroscopic stability and encircles a relatively stationary central cabin and/or payload area. The device set forth therein also provides free-rolling means to center and stabilize the flywheel or rotor within a discoid housing, and addresses the issue that horizontal flight maneuvering and/or directional control may be accomplished by altering the local angular acceleration of the rotor—as does the present invention. This said other device, however, relies upon the questionable concept that the very large angular momentum of the rotating flywheel is somehow able to compensate the potential energy caused by gravitation and

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