A method for producing thrust via the asynchronous transmission of current through two generally parallel wires.

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 system for propelling craft which is applicable in any environment. It employs an alternating magnetic field supplied by a coil. A parallel plate capacitor is situated so that the flux of the magnetic field flows between the plates of the capacitor. The capacitor is charged and discharged in synchronization with the alternating magnetic field. The changing magnetic field creates an electric field that applies a force to the charge in the plates which is then transferred to the body of the device. Any induced reactive electric force on the coil affects equally the protons and electrons in the wires of the coil creating the magnetic field, thus the force is non-reactive. At the same time, the changing electric field in the capacitor creates a magnetic field. The current in the coils and/or the surface current in the ferromagnetic material (if present) experiences a force from the magnetic field. The magnetic field created by these currents, however, has no free charge between the plates of the capacitor with which to react, thus this force is also non-reactive. The two forces are in opposite directions, but are not the same magnitude, thus the device is propelled in a single direction.

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, and an exhaust nozzle from which the heated propellant expands to provide an exhaust velocity of, for example, 7-16 km/sec. The launch vehicle can be utilized with the launch system, which can further comprise a launch tube formed of at least one tube, which can be electrically conductive and which can be combined with at least one insulator tube. An electrical energy source, such as a battery bank and associated inductor, can be provided.

Thrusting systems and vehicles are disclosed. One thrusting system includes a signal generator and a waveguide. The signal generator is configured to generate an electromagnetic wave. The waveguide is coupled to the signal generator to receive the electromagnetic wave such that at least a portion of electric and magnetic components of the electromagnetic wave extend in a direction transverse to a wave axis of the electromagnetic wave. The waveguide includes a dielectric material positioned to extend in a direction of the wave axis along a portion of the waveguide. An interaction between the electromagnetic wave and the waveguide induces a net force on the waveguide. One vehicle includes a thrusting system substantially as described above.

A method for producing thrust via the asynchronous transmission of current through two generally parallel wires.

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, and an exhaust nozzle from which the heated propellant expands to provide an exhaust velocity of, for example, 7-16 km/sec. The launch vehicle can be utilized with the launch system, which can further comprise a launch tube formed of at least one tube, which can be electrically conductive and which can be combined with at least one insulator tube. An electrical energy source, such as a battery bank and associated inductor, can be provided.

A centrifugal force propulsion device is disclosed. The device includes an asymmetrical device enclosure, having a first end wider than a second end. The device includes a magnetically charged mass and a rotating electromagnetic field source encircling the asymmetrical device enclosure, where the asymmetrical device enclosure is accelerated to a high revolutions-per-minute, resulting in a force vector in a direction of the first end of the robotic arm assemblies, and interchangeable robotic arm assembly attachment tools attachable to the attachment end for each of the robotic arm assemblies. The device may include a belt-driven centrifugal force propulsion system including a first pulley coupled to a second pulley by a weighted belt, where the first pulley has a first pulley size greater than a second pulley size and a power source coupled to either of the pulleys to generate a net force vector in the direction of the first pulley.

Photon drive and photon turbine When light reflects from a mirror it transfers sometimes more and sometimes less momentum to the mirror when mirror has dielectric in front compared to mirror in vacuum. Bouncing focused light between two mirrors fixed in a chasing where in front of one there is dielectric material and in front of the other there is vacuum, creates a net force difference. The second way to produce the force is through drag which light feels when it travels through dielectric material. This drag continuously transfers part of the light's momentum to the material. Net force from bouncing light between two mirrors can be used for linear propulsion in low friction environments such as outer space. When we redirect the light into a circular motion using coiled up fiber optic cable on the outer rim, than light creates rotating motion that can be used for electricity generation.

The present invention relates to a new form of air, land, underwater, or space propulsion, achieved by the use of suitable electromagnetic interactions. When using a longitudinal electromagnetic field emitter (1), which emits longitudinal electric or magnetic fields, with asymmetric electric or magnetic field derivatives, through space in the direction of element (2), optionally focused or amplified by element (3), we develop directional forces in elements (1) and (2). This is possible due to a new electromagnetic propulsion mechanism that uses the conservation of total momentum where the sum of mechanical momentum and field momentum must always be conserved resulting in a constant and zero total sum of the two components, where the variation in electric or magnetic field momentum will generate a corresponding change in the mechanical momentum of the assembly, thus generating propulsion forces.