Dipolar force field propulsion system

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.

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.