Dipolar force field propulsion system

What is claimed is:

1. A dipolar force field propulsion system comprising

means for generating an alternating electric field having its electromotive lines of force extending in a first direction and which vary at a selected frequency, said electric field having an electric field strength of a predetermined magnitude;

means for generating an alternating magnetic field having its magnetic lines of force which extend in a second direction which is at a predetermined angle to said first direction and which crosses and intercepts said electromotive lines of force at a predetermined location to define a spatial force field region and wherein the frequency of oscillation of the alternating magnetic field is substantially equal to the said selected frequency and is at a selected phase angle relating to said alternating electric field, said magnetic field having a flux density which when multiplied times the selected frequency is less than a known characteristic field ionization potential limit;

a source of neutral particles of matter having a selected electric dipole characteristic and having a known characteristic field ionization potential limit which is greater than said magnitude of the electric field strength, said dipoles of said particles of matter being capable of being driven into cyclic motion at said selected frequency by said electric field to produce a reactive thrust;

means for vaporizing said particles of the matter into a gaseous state at a selected temperature below the thermal ionization level thereof and for transporting said vaporized matter in said gaseous state into said spatial force field region defined by said crossed electromotive lines of force and magnetic lines of force which coact with and drive said dipoles into cyclic motion at said selected frequency to produce the reactive thrust which is substantially normal to said first direction of said electromotive lines of force and to the second direction of said magnetic lines of force; and

control means operatively coupled to said means for generating an alternating electric field and to said means for generating an alternating magnetic field and which is responsive to the dielectric properties of the vaporized matter located in the spatial force field region for establishing a predetermined spatial and time relationship between the electric field, magnetic field and dipole cyclic motion for a selected frequency.

2. Means for generating a reactive thrust force adapted to propel an aerospace vehicle comprising

means for generating an alternating electric field which varies at a selected frequency and extends in a first direction, said electrical field having an electric field strength of a predetermined magnitude;

means for generating an alternating magnetic field at substantially said selected frequency which extends in a second direction which is positioned at a predetermined angle to said first direction and which crosses and intercepts said electric field at a predetermined location to define a force field region, said magnetic field having a flux density which when multiplied times said selected frequency is less than selected characteristic field ionization potential limit;

means for vaporizing neutral particles of matter into a gaseous state at a selected temperature which is below the thermal ionization level of said particle, said particle having a selected electrical dipole characteristic, a breakdown characteristic which is greater than the magnitude of the electric field strength and a selected characteristic field ionization potential limit, said dipoles of said matter being capable of being driven into cyclic motion at a selected frequency by said electric field;

means operatively coupled to said vaporizing means for transporting said particles of the material into said force field region wherein said crossing electric field and magnetic field coact with and cause said dipoles of matter to be driven into cyclic motion at substantially said selected frequency produce a reactive thrust force in a direction which is substantially perpendicular to said first direction and said second direction; and

control means operatively coupled to said electric field generating means and said magnetic field generating means and responsive to the dielectric properties of the vaporized particles of matter located in said force field region for establishing a predetermined spatial and time relationship between the alternating electric field, the magnetic field and frequency of the cyclic motion of said dipoles said control means establishing said selected frequency at substantially the resonant frequency of a capacitance and inductance circuit formed by the electric field generating means, said magnetic fie1d generating means and the vaporized particles of matter in the force field region.

3. The propulsion system of claim 1 wherein the predetermined angle between the first direction of the electric field and the second direction of the magnetic field is selected to be 90.degree. .

4. The propulsion system of claim 1 further comprising

means for raising the electronic excitation level of said particles of neutral matter in the vaporized gaseous state to a higher quantum level thereby increasing the magnitude of the selected electric dipole moment characteristic.

5. The propulsion system of claim 4 wherein said electronic excitation level raising means is a laser.

6. The propulsion system of claim 5 wherein said laser raises the quantum level of the particles of material to a quantum level between n=1 and n=20 by controlling the wavelength of the laser in step wise fashion to establish the dipole moment at a selected energy level which varies between the lowest energy level of the material at a quantum level of n=1 and a higher energy level which is below the thermal ionization level of the material at a quantum level of n=20.

7. The propulsion system of claim 4 wherein said electronic excitation level raising means is ultraviolet radiation.

8. The propulsion system of claim 5 wherein said laser originates from an external location.

9. The propulsion system of claim 1 wherein said magnetic field generating means are permanent magnets.

10. The propulsion system of claim 1 wherein said magnetic field generating means is a plurality of spaced, radially aligned superconducting magnets with the poles thereof alternately positioned relative to each adjacent magnet and a rotatable, ferrite magnetic material rotor which cyclically is transported past each of the radially aligned superconducting magnets to generate an alternating magnetic field.

11. The propulsion system of claim 1 wherein said magnetic field generating means is a coil.

12. A propulsion system comprising

a plurality of U-shaped superconducting pole pieces positioned in spaced alignment to define a substantially rectangular elongated channel;

a plurality of coils positioned one each around the center of one pole piece;

a plurality of pairs of spaced, substantially planar conducting electrodes positioned with each spaced pair extending between the ends of the U-shaped pole pieces wherein one of the planar electrodes is located adjacent the coil and the other planar electrode is spaced therefrom a distance substantially equal to the length of the U-shaped pole pieces defining a spatial region defined on two boundaries by the pair of planar electrodes and on two boundaries by the U-shaped end of the pole pieces, each of the spatial regions of each pole piece and planar electrode pair being in alignment enclosing said substantially elongated channel;

means for electrically connecting one of the planar electrodes of the planar electrode pair in series with the coil associated with its respective pole piece and for electrically connecting each series connected planar electrode pair and coil in parallel with the other series connected planar electrode pairs and being adapted to be connected to an alternating electrical power source;

a radiation source positioned at one end of the substantially rectangular elongated channel for directing radiation through each spatial region defined by each planar electrode pair and pole piece ends;

a plenum positioned at said one end adjacent said radiation source adapted to transport a vaporized propellent gas having neutral particles of matter having a selected dipole characteristic at a controlled rate through said substantially rectangular elongated channel; and

a cryogenic source of propellant gas comprising neutral particles of matter wherein the particles of matter have a selected electric dipole characteristic and a known characteristic field ionization potential limit, said cryogenic source being operatively coupled to said plenum through a means for vaporizing said propellant gas to a level less than the ionization level thereof and applying a continuous stream of vaporized propellant gas to said plenum, said electrical connecting means being responsive to a said alternating electrical power source to produce an alternating electric field across each planar electrode pair and an alternating magnetic field between each pole piece and which was the alternating electric field establishing a plurality of aligned spatial force field region into which the vaporized gas is transported by said plenum into said substantially rectangular elongated channel through each spatial force field region of each planar electrode pair and coil, whereupon the particles of matter of the propellant gas are raised to an electronic excitation level by said radiation source and the crossing electric field and magnetic field which cause the dipoles of the particles of matter to be driven into cyclic motion to produce a reactive thrust.

13. The propulsion system of claim 12 wherein said radiation source is a laser.

14. The propulsion system of claim 12 wherein said means for vaporizing the propellant gas includes cooling means located adjacent each coil and pole piece center which is adapted to absorb heat from said coils which vaporizes said propellant gas passing therethrough.

15. The propulsion system of claim 14 further comprising

a flow meter positioned between said plenum and said vaporizing means to control the flow rate of the vaporized propellant gas into the plenum.

16. The propulsion system of claim 3 wherein said means for generating an alternating electric field is formed of a pair of spaced parallel plates which define a capacitor having a space between the parallel capacitive plates and wherein said means for generating an alternating magnetic field includes a plurality of spaced coils which are spaced relative to each other, said coils and said capacitor being electrically connected in series, resulting in the electric field being phase displaced from the magnetic field by 90.degree., said magnetic means being adapted to direct and concentrate the lines of magnetic force between the capacitive plates to establish an electric field which is located at substantially 90.degree. relative to the magnetic field.

17. The propulsion system of claim 16 wherein said means for generating the alternating magnetic field includes a ferrite coil for further concentrating said magnetic lines of flux.

18. The means for generating a reactive thrust force of claim 2 wherein said means for generating an alternating current electric field is a pair of spaced parallel electrodes which are adapted to distribute charges on a controlled surface and to distribute the charges uniformly on the surface thereof to produce an electric field which extends in said first direction and which is adapted to intercept the magnetic field generated by said means for generating throughout the spatial region in the vicinity of the electrode an alternating magnetic field at substantially right angles to form a crossed dipole magnetic throughout said spatial region field which is substantially at a right angle to the electric dipole field.

19. The dipolar force field propulsion system of claim 1 further comprising

means including an excitation source of radiation positioned at a selected location on the system for producing a field of radiation; and

means including means defining a reflecting surface postion adjacent radiation field producing means for selectively positioning said reflective surface at a controlled angle relative to said excitation source to produce a thrust component of force in a selected direction causing said system to move in a direction opposite to said selected direction of a thrust component of force.

20. The propulsion system of claim 4 further comprising

a source of second neutral particles of matter which is of different species than the source of neutral particles of matter and wherein the second neutral particles of matter have a selected electron dipole characteristics, said second neutral particles of matter being capable of interacting with said neutral particles of matter which have been raised to an electronic excitation level enabling the atoms of said second neutral particles of matter to act as buffer atoms with said neutral particles of matter to permit optical pumping of the neutral particles of matter at raised electronic excitation levels.

21. The propulsion system of claim 20 further comprising

a laser adapted to optically pump said neutral particles of matter.