Provided herein are various leptonic power sources, leptonic control systems, and leptonic-powered engines. An apparatus includes a leptonic source configured to emit beam electrons to ionize a material into a plasma according to a selectable ionization degree and deposit charge onto a plurality of cathodes in a progressively more negatively charged arrangement to establish an electric field of a selectable intensity in the plasma.

High propellant throughput Hall-effect thrusters (HETs) and components thereof are disclosed. A compact and high propellant throughput HET has an improved magnetic circuit that mostly shields the discharge chamber walls from high-energy ionized propellant, low-profile sacrificial pole covers to delay magnetic pole erosion, a unique discharge chamber subassembly, a mechanically crimped cathode emitter retainer to increase efficiency, a center-mounted hollow cathode, or a combination thereof. Such feature(s) may balance propellant throughput and thruster performance, minimize the volume of the thruster envelope, and/or simplify the thruster assembly.

This device, the (‘Demon’ Quantum Mechanical, (H/C)/(Propulsion) system), replaces entirely, the (antiquated system of using Cryogens for cooling, in satellite applications). This device, is the ONLY application, which uses (Quantum Mechanics) for Propulsion/Thrusting. This device is the ONLY design to use (Quantum Mechanics) to (simultaneously Heat and Cool) in any application. This device is the ONLY design to use (Quantum Mechanics) to (simultaneously Heat and Cool) and for (Propulsion) in any application, —and due to the system (operating methods) and (weightless environment), —with EXPONENTIALLY greater (fuel) efficiency. This device (extends the (working service life) of Satellites requiring cooling) from MONTHS, to 50+ YEARS/more.

Disclosed is a radio-frequency plasma generating system including a radio-frequency generator and a plasma source, the radio-frequency generator being inductively or capacitively coupled to the plasma source through a resonant electric circuit, the radio-frequency generator being adapted to receive direct current power from a direct current power supply and for generating radio-frequency power at a frequency f, the radio-frequency power including a reactive radio-frequency power oscillating in the resonant electric circuit and an active radio-frequency power absorbed by the plasma. The radio-frequency plasma generating system includes a unit for measuring an efficiency of conversion E of direct-current power to active radio-frequency power absorbed by the plasma and a unit for adjusting the frequency f as a function of the measured efficiency of conversion E to maintain the efficiency of conversion E in a predetermined range within a RF plasma operational range.

Provided herein are various leptonic power sources, leptonic control systems, and leptonic-powered engines. In one example, an apparatus includes a housing having apertures through which material can enter and exit, and an anode coupled to the housing upstream from a cathode. A leptonic source emits beam electrons into the housing to ionize the material into a plasma according to a selectable ionization degree and deposit charge onto the cathode to establish an electric field in the plasma. A magnetic field source produces a magnetic field in the plasma at selectable angle to the flow of the plasma to at least partially entrain plasma electrons. Ions of the plasma are accelerated downstream in the housing by the electric field and impart momentum to a portion of the material to produce a thrust proportional to the selectable ionization degree of the plasma and a selectable intensity of the electric field.

A Hall-effect thruster assembly includes a plurality of magnetic sources for creating a magnetic circuit. The plurality of magnetic sources are positioned between a first end and a second, opposite end of the Hall-effect thruster. The plurality of magnetic sources define a longitudinal axis extending through the first end and the second end. The first end is configured as a discharge end. A mount assembly is coupled to the second end. The mount assembly is configured to secure the plurality of magnetic sources to a spacecraft. A magnetic element is supported by the mount assembly. The magnetic element is positioned relative to the plurality of magnetic sources by the mount assembly.

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.

A time average peak value of low frequency magnetic noise or low frequency conductive noise generated from a power supply device which drives a Hall thruster is suppressed without mass of a satellite significantly increased. A pulse width control circuit (22) of a Hall thruster power supply device (10) outputs a spread signal (58) obtained by performing spread spectrum on a pulse signal based on a control signal (54). A voltage output circuit (21) outputs output voltage (52) to a Hall thruster (50) in accordance with the spread signal (58) output by the pulse width control circuit (22).

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.

A satellite thruster increases satellite efficiency. The Linear Actuated μCAT has a stepper motor to move the ablative electrode forward. A LabVIEW program and Arduino microcontroller are used to analyze the Linear Actuated μCAT 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.