An electrodeless plasma thruster with closed-ring-shaped gas discharge chamber (1, 10) can include a gas discharge chamber (1, 10) closed-ring-shaped in fluid communication with a propellant storage system (10, 70). An antenna (3, 30) can be positioned on the exterior of the gas discharge tube (1, 10). A guide tube (2, 20) can be coupled with the gas discharge chamber (1, 10) at a first end and have a second open end. A magnetic system (7, 50) can be positioned on the second end of the guide tube (2, 20). The magnetic system (7, 50) can be electrically coupled with a power supply. The power supply can be electrically coupled with a power converter (11, 80) and a control module.

This application describes creating, modifying, and bending electromagnetic solitons at large scales for the various applications. An electromagnetic soliton generator system controls the magnetic soliton such that the orientation, rotation rate, pitch angle, and magnetic field strength of the solitons are modified to provide the described standing waves and generate a magnetic flux differential.

An intake system for an atmosphere-breathing electric thruster is disclosed, comprising an inlet for inflow of atmosphere particles, an outlet for coupling to the thruster for fueling collected atmosphere particles to the thruster, a collector arranged between the inlet and the outlet comprising multiple channels for allowing inflowing atmosphere particles to pass through the channels towards the outlet, the channels defining an inlet area and a length, wherein a position of at least part of the channels is adjustable to alter at least one of the inlet area and the length.

A method and apparatus uses a VLF transmitter, a VLF receiver, and/or a low earth orbit satellite including a rocket engine. A VLF wave transmitted into space is converted to an ambient wave. The ambient wave acts as a signal wave for a whistler traveling wave parametric amplifier. Rocket exhaust is generated in atmospheric plasma. The rocket exhaust includes kinetic energy acting as a Lower Hybrid wave source. The Lower Hybrid wave source produces a Lower Hybrid wave, which acts as a pump wave for the parametric amplifier. Nonlinear mixing of the signal wave and the pump wave in the atmospheric plasma simultaneously parametrically amplifies the ambient wave and generates an idler wave and a parametrically amplified wave. The parametrically amplified wave (1) reduces the density of energetic protons or killer electrons in the Van Allen radiation belt, and (2) improves communications between the VLF transmitter and VLF receiver.

A propellant distributor or anode includes a plenum chamber and a plurality of outlets. The at least one plenum chamber is configured to receive a flow of propellant from an inlet, and the plurality of outlets are configured to distribute the flow of propellant into an inner channel wall and an outer channel wall of a discharge channel.

The invention provides an electrothermal RF plasma production system and thruster design, and associated components, that may be used in terrestrial applications and/or miniaturized to the mass, volume, and power budget of Cube Satellites (CubeSats) to meet the propulsion needs of the small satellite (?5 to ?500 kg) constellations and larger satellite buses.

The invention provides an electrothermal RF plasma production system and thruster design, and associated components, that may be used in terrestrial applications and/or miniaturized to the mass, volume, and power budget of Cube Satellites (CubeSats) to meet the propulsion needs of the small satellite (?5 to ?500 kg) constellations and larger satellite buses.

An aerodynamic platform or spacecraft including a habitable 1G centripetal force rotating gravity producing interior corridor within an aerodynamic shell and an aerodynamic drone booster launch system with reentry and reuse capability.

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.

A satellite propulsion system and methods of operating the same include a first ionization stage and a second acceleration stage. The first ionization stage has a plasma source configured to produce an arc discharge and emit a preliminary plasma. The plasma source includes an external magnetic field configured to magnetize the arc discharge. The second acceleration stage has an accelerator positioned in series with the plasma source. The accelerator is configured to accelerate the preliminary plasma out through the accelerator, thereby creating an accelerated plasma flow. The application of an activation threshold voltage to the accelerator results in a surge in system performance parameters.