The fluid driven motor device, which does not use a magnet or an armature coil, includes a motor casing chamber containing a fluid mixture, a shaft disposed within the chamber, and a plurality of ray guns arranged on the periphery of the chamber. The shaft has a plurality of cell holders, onto which a corresponding plurality of membrane cells is attached. Each membrane cell holds a predetermined quantity of a liquid. The membrane cells expand and contract continuously based on the firing of the subatomic rays by the plurality of ray guns. This expansion and contraction cycle causes the shaft to rotate. The device has several advantages such as being very energy and heat efficient, having lesser weight as compared to conventional electromagnetic coil based motors.

The fluid driven motor device, which does not use a magnet or an armature coil, includes a motor casing chamber containing a fluid mixture, a shaft disposed within the chamber, and a plurality of ray guns arranged on the periphery of the chamber. The shaft has a plurality of cell holders, onto which a corresponding plurality of membrane cells is attached. Each membrane cell holds a predetermined quantity of a liquid. The membrane cells expand and contract continuously based on the firing of the subatomic rays by the plurality of ray guns. This expansion and contraction cycle causes the shaft to rotate. The device has several advantages such as being very energy and heat efficient, having lesser weight as compared to conventional electromagnetic coil based motors.

A method and means to produce a force for propulsion comprises a source of free electrons and a means to produce pseudoelectrons; whereas, a gravitating body such as the Earth provides a repulsive fifth force on the pseudoelectrons. Pseudoelectrons are produced by absorption of high-energy photons by free electrons or by angular momentum exchange between polarized relativistic free electrons and a collision partner such as H3+. The free electrons to undergo transitions to pseudoelectron states may be first formed in the ground spin state. The pseudoelectrons experience a fifth force (F2) away from the Earth and move upward (away from the Earth).

A method and means to produce a force for propulsion comprises a source of free electrons and a means to produce pseudoelectrons; whereas, a gravitating body such as the Earth provides a repulsive fifth force on the pseudoelectrons. Pseudoelectrons are produced by absorption of high-energy photons by free electrons or by angular momentum exchange between polarized relativistic free electrons and a collision partner such as H3+. The free electrons to undergo transitions to pseudoelectron states may be first formed in the ground spin state. The pseudoelectrons experience a fifth force (F2) away from the Earth and move upward (away from the Earth).

The present invention discloses systems and methods for electromagnetic field spacecraft propulsion. The system includes reaction thrust assemblies comprising conductor coils with alternating segments of magnetic field shield assemblies. Unshielded reaction thrust assembly segments are bracketed by field activation coils generating shaped magnetic fields. The action of the magnetic fields on currents in the unshielded coil segments of the reaction thrust assemblies produce unidirectional Lorentz Forces, thereby generating thrust without reaction mass, while reaction momentum is carried away by Poynting Vector fields in conformity with the currently understood principles of electrodynamics.

The present invention discloses systems and methods for electromagnetic field spacecraft propulsion. The system includes reaction thrust assemblies comprising conductor coils with alternating segments of magnetic field shield assemblies. Unshielded reaction thrust assembly segments are bracketed by field activation coils generating shaped magnetic fields. The action of the magnetic fields on currents in the unshielded coil segments of the reaction thrust assemblies produce unidirectional Lorentz Forces, thereby generating thrust without reaction mass, while reaction momentum is carried away by Poynting Vector fields in conformity with the currently understood principles of electrodynamics.

Asteroid redirection systems are provided that use cosmic ray and muon-catalyzed micro-fusion. These systems include a micro-fusion propulsion system providing thrust for redirecting an asteroid, as well as micro-fusion electrical generation powering an ion drive. The systems deploy deuterium-containing fuel material as a localized cloud interacting with incoming ambient cosmic rays to generate energetic fusion products. Dust or other particulate matter in the fuel material converts some cosmic rays into muons that also catalyze fusion. The fusion products provide thrusting upon the asteroid, or when produced near turbines facilitates electrical generation, which can then power an ion drive.

Omnivorous solar thermal thrusters and adjustable cooling structures are disclosed. In one aspect, a solar thermal rocket engine includes a solar thermal thruster configured to receive solar energy and one or more propellants, and heat the one or more propellants using the solar energy to generate thrust. The solar thermal thruster is further configured to use a plurality of different propellant types, either singly or in combination simultaneously. The solar thermal thruster is further configured to use the one or more propellants in both liquid and gaseous states. Related structures can include valves and variable-geometry cooling channels in thermal contact with a thruster wall.

Omnivorous solar thermal thrusters and adjustable cooling structures are disclosed. In one aspect, a solar thermal rocket engine includes a solar thermal thruster configured to receive solar energy and one or more propellants, and heat the one or more propellants using the solar energy to generate thrust. The solar thermal thruster is further configured to use a plurality of different propellant types, either singly or in combination simultaneously. The solar thermal thruster is further configured to use the one or more propellants in both liquid and gaseous states. Related structures can include valves and variable-geometry cooling channels in thermal contact with a thruster wall.

A fuel less pneumatic and hydraulic lift system flight system provides the following systemic components. A chassis supporting an electric battery and a pressurized base hydraulic cylinder, a hydraulic fluid pumping assembly fluidly coupled to the pressurized base hydraulic cylinder; a lift mechanism assembly providing an attractive levitation plate mounted to the chassis; and a repulsive levitation plate mounted to a carriage, wherein the repulsive levitation plate is disposed in a magnetic pole repulsive alignment relative to the attractive levitation plate causing a magnetic lift effect to the chassis; and a plurality of propulsions jets mounted to the chassis, wherein the plurality of propulsion jets enabling motive functionality using hydraulic fluid propulsion and pneumatic pressure via the hydraulic fluid pumping assembly in conjunction with the magnetic lift effect.