A modular micro-cathode arc thruster for use in satellites. An exemplary satellite has a plurality of stacked modular arc thrusters, each having an external anode, an internal cathode, and an insulator therebetween. The arc thrusters are situated in a housing, wherein the housing has an opening to eject exhausted thrusters. Once an arc thruster is expended, the push rod ejects that arc thruster and the next arc thruster takes its place.

As is scientifically well know magnetic flux is a physical force (i.e. the Lorentz force and Ampere's force). The invention utilizes a plurality of electromagnetic and or plasma coils to create high pressure, high velocity magnetic flux directed through variable exhaust nozzles or a cone shaped electrical coil to create thrust for spacecraft.

According to some embodiments, a system for widening and densifying a scrape-off layer (SOL) in a field reversed configuration (FRC) fusion reactor is disclosed. The system includes a gas box at one end of the reactor including a gas inlet system and walls of suitable heat bearing materials. The system further includes an exit orifice adjoining the gas box, wherein the exit orifice has a controllable radius and length to allow plasma to flow out from the gas box to populate the SOL with the plasma. The system may also include fusion products, which decrease in speed in the plasma in the SOL, allowing energy to be extracted and converted into thrust or electrical power and further allowing ash to be extracted to reduce neutron emissions and maintain high, steady-state fusion power.

A thruster has a first stage and a second stage. The first stage is a plasma source that outputs a plasma. The second stage is an accelerator. In one embodiment, the second stage is a plasma accelerator that accelerates the plasma. In another embodiment, the second stage is an ion accelerator that accelerates the ions from the plasma.

A plasma reactor is provided together with a method for generating kinetic energy to propel a craft. The reactor includes an inlet for plasma; a reactor core having an interior chamber and an exterior chamber, the interior chamber being configured to rotate within the exterior chamber; a pair of opposing polar field generators, a first polar field generator connected proximal to an inlet of the interior chamber, and a second polar field generator connected proximal to an outlet of the interior chamber, the pair of polar field generators configured to induce a current in the plasma to generate a toroidal flow therein, wherein the toroidal flow compresses the plasma into a z-pinch flow in a central column between the first polar field generator and the second polar field generator; turbine blades located between the interior chamber and the exterior chamber for generating thrust to convert the z-pinch flow to kinetic energy; and an outlet.

Systems and methods establish plasma in a rotating magnetic field. An exemplary embodiment is a plasma thruster that establishes a first transverse magnetic field with respect to a system axis of a plasma propulsion system; establishes a second transverse magnetic field oriented orthogonally to the first transverse magnetic field, wherein the second transverse magnetic field is out of phase with the first transverse magnetic field; and establishes a magnetic field aligned with the system axis using a plurality of magnet elements oriented along the system axis. A plasma containment portion defines an interior region, wherein an interior region of a plasma containment portion accommodates a plasma that is established by a rotating magnetic field component that is cooperatively established by the first transverse magnetic field and the second transverse magnetic field, and wherein the plasma is accelerated out of the plasma containment portion by magnetic forces to generate a propulsion force.

A microwave electrothermal thruster (MET) and its control system is disclosed and claimed. The MET control system uses a dielectric resonator oscillator (DRO) in series with a GaN MMIC-based Solid State Power Amplifier (SSPA) to generate microwave energy, transfer it to a thrust chamber, and heat a propellant that exits a nozzle, providing thrust. The control system uses feedback to provide autonomous control of the MET. A wide variety of propellants may be used, including, for example, hydrazine, ammonia, and water.

A satellite thruster increases satellite efficiency. The Linear Actuated CAT has a stepper motor to move the ablative electrode forward. A LabVIEW program and Arduino microcontroller are used to analyze the Linear Actuated CAT to determine how many steps are required for re-ignition, arc current, and the validity of the feed system. Results from testing show that micro-stepping the stepper motor is an effective way to replenish the cannibalized electrode for propellant.

A micro-hollow cathode discharge device. The device includes a first electrode layer comprising a first electrode. A hole is disposed in the first electrode layer. The device also includes a dielectric layer having a first surface that is disposed on the first electrode layer. The hole continues from the first electrode layer through the dielectric layer. The device also includes a semi-conducting layer disposed on a second surface of the dielectric layer opposite the first surface. The semi-conducting layer is a semiconductor material that spans across the hole such that the hole terminates at the semi-conducting layer. The device also includes a second electrode layer disposed on the semi-conducting layer opposite the dielectric layer.

A process and system for the extraction of metals and gases contained on planets and asteroids (mining and refining) and for space debris remediation may include geographically localizing a material to be extracted/remediated; performing a risk analysis on the material to determine whether the material presents a serious risk of instantaneous fracture or disaggregation; using the risk analysis to qualify or refuse the material; capturing and stabilizing the qualified material in an ablation cylinder on a plasma machine (PERT station); deploying multiple magnetic hydraulic cylinders around the qualified material; equalizing and stabilizing the PERT station and the qualified material; performing ablation and destruction of the qualified material; and transforming pure elements from the ablation cylinder.