A circuit for igniting and sustaining an electron discharge includes an ignitor circuit. The igniter circuit includes a high voltage transformer and a switch connected in series between a primary of the transformer and a DC source return. The switch is configured to receive a driving signal. A reset circuit is connected in parallel to the primary of the high voltage transformer. A first rectifier is connected in series between a secondary of the high voltage transformer and a keeper. A terminal of the secondary of transformer is connected to a cathode. The circuit for igniting and sustaining the electron discharge also includes a sustaining circuit having a current source with a return connected to a cathode and a second rectifier connected in series between the current source and the keeper.

The disclosure relates to an apparatus for astronautic rotating mass propulsion. The method and apparatus entails rotating a mass to generate thrust. Varying the speed and direction of rotation provides some control of the magnitude and direction of the thrust generated. The apparatus of the invention pertinent to a propulsion system for spacecrafts or astromotive vehicles under conditions of zero to low gravity and atmosphere.

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.

This disclosure describes various techniques and systems for rapid low-cost access to suborbital and orbital space and accommodation of acceleration of sensitive payloads to space. For example, a distributed gas injection system may be used in a ram accelerator to launch multiple payloads through the atmosphere. Additionally or alternatively, multiple projectiles may assemble during flight through the atmosphere to transfer and/or resources to another projectile.

An electromagnetic propulsion system for the movement of spacecraft by means of ejection of the perturbed dark matter. In the present invention, to perturb and accelerate the dark matter, the electromagnetic energy generated by microwave generators is supplied to a number of position-adjustable electromagnetic vibrators that form a phased antenna array inside the waveguide. Since the dark matter permeates the Universe and its reserves are unlimited, it can be used as a working medium in the constant acceleration propulsion system for as long as the electric power supply lasts. Since the electromagnetic propulsion system has infinite reserves of the working medium, the specific impulse is also infinite. The speed of the dark matter jet approaches the speed of light.

Numerous patents have been granted for methods to extract useful zero-point energy (ZPE). However, these methods utilize the Casimir force, which is orders of magnitude too small to power an electrical grid. The method and apparatus described here uses counter-rotating mercury based plasmas pulsed with a high frequency, high voltage discharge to create a coherence with the zero-point field, allowing for unlimited extraction of ZPE, which may ultimately replace polluting fossil fuel derived energy. Mainstream physics models gravity as a curvature of space (general relativity), but there are profound problems with this model. An alternative model of gravity advanced by some physicists models gravity (and inertia) as an induced effect resulting from the interaction of ZPE with subatomic charge. By creating a coherence with the zero-point field, this method causes an interference with this interaction, allowing gravity and inertia to be engineered or nullified, representing a breakthrough in propulsion.

A magnetic field propulsion unit includes a first magnetic field generating device (“FMFGD”) generating a magnetic field; a second magnetic field generating device (“SMFGD”) generating a magnetic field; an energy supply unit providing the FMFGD and the SMFGD with electrical energy; and a control unit controlling the energy supply unit in accordance with a predefined switching scheme. The SMFGD is a rod-like antenna that lies in a plane in which also the FMFGD lies. The control unit is: supplying the SMFGD with electrical energy so that a second magnetic field surrounding the SMFGD is generated; supplying the FMFGD with electrical energy so that a first magnetic field surrounding the FMFGD is generated. The FMFGD is supplied with electrical energy a predetermined period of time after the SMFGD is supplied with electrical energy.

Apparatus and associated methods relate to an in-space propulsion system configured to generate propulsion from a recirculated working fluid. In an illustrative example, the propulsion system may include a boiler configured to generate high pressure gas from the working fluid. The gas may, for example, be ejected from a nozzle into a distributor tube. A radiator coupled to the distributor tube may, for example, facilitate phase transition of the gas back into the working fluid. The fluid may be collected via one or more collection ducts coupled to the radiator. One or more pumps may recirculate the working fluid from the one or more collection ducts back into the boiler. Various embodiments may advantageously recirculate the working fluid such that propulsion is generated in response to an external power source while substantially an entire mass of the working fluid is preserved in the propulsion system.

An improved magnetic pulse thrust device based on inertial propulsion is described; but that it has incorporated a fully magnetic mechanization and that it achieves due in part to its ability to revolutionize its axes of circular motion at a very high number of revolutions per second that increases power and continuity, resulting in a 100% continuous rectilinear motion in a continuous manner, that achieves weightlessness by observing it placed on a scale in a vertical position, thus reducing the gravitational forces of the planets in outer space.

A hypersonic harmonic exciter system to enable hypersonic speed, including a hypersonic harmonic exciter body having a plurality angled sides forming exciter body hollow structure with an access aperture, vibration inducing wave apparatus configured to produce and project vibration harmonic waves that converge on a convergence harmonic point forward of the hypersonic harmonic exciter body, the vibration inducing wave apparatus having vibration apparatus hollow structure with a series of exterior concentrically positioned vibration inducing bands, the vibration inducing wave apparatus inserted in the exciter body hollow structure, and harmonic sound projecting apparatus configured to produce and project harmonic sound waves that converge on the convergence harmonic point forward of the hypersonic harmonic exciter body, the harmonic sound projecting apparatus having sound apparatus hollow structure with a series of exterior concentrically positioned sound emitter bands, the harmonic sound projecting apparatus inserted in the vibration apparatus hollow structure.