The present invention relates to a new form of air, land, underwater or space propulsion achieved by the use of suitable electromagnetic interactions. By using capacitors formed by symmetric or asymmetric conductors (1) and (2), surrounded by a dielectric (3), subjected to asymmetric voltage pulses or with asymmetric electric field derivative we obtain directional propulsion forces. This is possible due to a new electromagnetic propulsion mechanism that uses conservation of total momentum where the sum of the mechanical momentum with the electric field momentum should always be conserved resulting in a constant and zero total sum of the two components, where the change in electric field momentum will generate a corresponding change in the mechanical momentum of the capacitor thus generating propulsion forces where the inertia forces are attenuated and can generate force fields.

A high frequency gravitational wave generator including a gas filled shell with an outer shell surface, microwave emitters, sound generators, and acoustic vibration resonant gas-filled cavities. The outer shell surface is electrically charged and vibrated by the microwave emitters to generate a first electromagnetic field. The acoustic vibration resonant gas-filled cavities each have a cavity surface that can be electrically charged and vibrated by acoustic energy from the sound generators such that a second electromagnetic field is generated. The two acoustic vibration resonant gas-filled cavities are able to counter spin relative to each other to provide stability, and propagating gravitational field fluctuations are generated when the second electromagnetic field propagates through the first electromagnetic field.

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 disclosure relates to a launch system, a launch vehicle for use with the launch system, and methods of launching a payload utilizing the launch vehicle and/or the launch system. The disclosure can provide for delivery of the payload at a terrestrial location, an Earth orbital location, or an extraorbital location. The launch vehicle can comprise a payload, a propellant tank, an electrical heater wherein propellant, such as a light gas (e.g., hydrogen) is electrically heated to significantly high temperatures, an exhaust nozzle from which the heated propellant expands to provide an exhaust velocity of, for example, 7-16 km/sec, and sliding electrical contacts in electrical connection with the electrical heater. The launch vehicle can be utilized with the launch system, which can further comprise a launch tube formed of concentric electrically conductive tubes, as well as an electrical energy source, such as a battery bank and associated inductor.

A high frequency gravitational wave generator including a gas filled shell with an outer shell surface, microwave emitters, sound generators, and acoustic vibration resonant gas-filled cavities. The outer shell surface is electrically charged and vibrated by the microwave emitters to generate a first electromagnetic field. The acoustic vibration resonant gas-filled cavities each have a cavity surface that can be electrically charged and vibrated by acoustic energy from the sound generators such that a second electromagnetic field is generated. The two acoustic vibration resonant gas-filled cavities are able to counter spin relative to each other to provide stability, and propagating gravitational field fluctuations are generated when the second electromagnetic field propagates through the first electromagnetic field.

Systems and methods of interacting complex electric fields and static electric fields to effect motion are disclosed. An example method includes producing an action force having a reaction force perpendicular to the action force by interacting a relative velocity electric field based on charge of a moving first charged object and a static charge on a second charged object in a different inertial frame of reference. Another example method includes producing an action force having a reaction force perpendicular to the action force by interacting an acceleration generated electric field based on acceleration of a first charged object and a static charge on a second charged object in a different inertial frame of reference. Another example method includes producing an action force having a reaction force perpendicular to the action force by interacting a scalar electric potential and static electric field.

The present application relates to optical-mechanical systems and methods for moving a solid object by applying conservation of angular momentum to a configuration of a laser light beam that emanates from the solid object. The system includes a rotatable housing and an axially movable laser light source coupled to the housing and configured to emit a first light beam along a first path. The system can include a first beam splitter disposed along the first path for splitting the first light beam into a second light beam and a third light beam. The system can cause the third light beam to travel in a closed path, as an approximation of a circular path of initial radius, and of decreasing radius. The system can further include a second beam splitter, axially movable first, second and third mirrors, and a third beam splitter disposed at one end of the housing.

The present disclosure relates to a launch system, a launch vehicle for use with the launch system, and methods of launching a payload utilizing the launch vehicle and/or the launch system. The disclosure can provide for delivery of the payload at a terrestrial location, an Earth orbital location, or an extraorbital location. The launch vehicle can comprise a payload, a propellant tank, an electrical heater wherein propellant, such as a light gas (e.g., hydrogen) is electrically heated to significantly high temperatures, an exhaust nozzle from which the heated propellant expands to provide an exhaust velocity of, for example, 7-16 km/sec, and sliding electrical contacts in electrical connection with the electrical heater. The launch vehicle can be utilized with the launch system, which can further comprise a launch tube formed of concentric electrically conductive tubes, as well as an electrical energy source, such as a battery bank and associated inductor.

The present invention discloses an electromagnetic propulsion device for generating unidirectional force and method thereof. The electromagnetic propulsion device comprises one or more pod units, a power source, a control unit. Each pod unit comprises an enclosure, one or more magnetic flux-controlling cores, one or more pairs of magnetic materials, and one or more electrically conductive elements. The one or more pod units operatively form a structure of the vehicle in a pre-defined shape, configured to generate the unidirectional force. The pre-defined shape is configured to provide a distributed propulsion and a control redundancy based on arranging the one or more pod units in defined geometries to form the structure of the vehicle. The control unit is configured to activate and deactivate the one or more pod units, regulate thrust levels, and change propulsion direction of the vehicle.

Disclosed are a method of flying on the moon and a device for flying using the method. A medium on a surface of a moon and a medium accelerating module are used in the flying method. The medium is transferred into the medium accelerating module, accelerated by the medium accelerating module, and ejected out of the medium accelerating module by using a power supply. A counterforce is generated in accordance with the momentum conservation, and the counterforce overcomes the lunar gravity and drives a load to take off. The method is suitable for the environment of the moon where flight by means of atmospheric buoyancy is impossible due to the shortage of atmosphere.