A method and apparatus for processing a particle shower using a laser-driven plasma is provided. The method comprises interacting a particle shower with a processing laser-driven plasma stage, the particle shower comprising at least one particle species, wherein the laser is a high-energy, ultra-short pulse laser. In some embodiments, the method comprises accelerating, decelerating, trapping, or collimating the at least one particle species in the processing laser-drive plasma stage. Particularly, the embodiments enable generating high energy particle beams that were only possible using accelerators spanning several hundred meters, in a space of a few meters.

A method and apparatus for processing a particle shower using a laser-driven plasma is provided. The method comprises interacting a particle shower with a processing laser-driven plasma stage, the particle shower comprising at least one particle species, wherein the laser is a high-energy, ultra-short pulse laser. In some embodiments, the method comprises accelerating, decelerating, trapping, or collimating the at least one particle species in the processing laser-drive plasma stage. Particularly, the embodiments enable generating high energy particle beams that were only possible using accelerators spanning several hundred meters, in a space of a few meters.

A medical system for providing radiotherapy is disclosed. The system comprises a particle accelerator configured to produce a radiation beam and irradiate at least a part of a subject with the radiation beam. The particle accelerator comprises a plasma zone comprising or configured to receive a plasma, and at least one beam source configured to provide an excitation beam along an axis through the plasma zone. The medical system is configured to provide a plurality of charged particles in the plasma in a region that propagates through the plasma zone behind the excitation beam such that the plurality of charged particles are accelerated to produce a radiation beam comprising the plurality of charged particles with a broadband energy distribution, wherein: at least part or all of the energy distribution of the radiation beam is substantially exponential or power-law; the radiation beam delivers 75% or more of a dose of the charged particles at and below 2 g/cm.sup.2; and/or the energy beam has an energy or energy distribution in the range from 10 eV to 10 MeV.

A medical system for providing radiotherapy is disclosed. The system comprises a particle accelerator configured to produce a radiation beam and irradiate at least a part of a subject with the radiation beam. The particle accelerator comprises a plasma zone comprising or configured to receive a plasma, and at least one beam source configured to provide an excitation beam along an axis through the plasma zone. The medical system is configured to provide a plurality of charged particles in the plasma in a region that propagates through the plasma zone behind the excitation beam such that the plurality of charged particles are accelerated to produce a radiation beam comprising the plurality of charged particles with a broadband energy distribution, wherein: at least part or all of the energy distribution of the radiation beam is substantially exponential or power-law; the radiation beam delivers 75% or more of a dose of the charged particles at and below 2 g/cm.sup.2; and/or the energy beam has an energy or energy distribution in the range from 10 eV to 10 MeV.

A heaterless hollow cathode provides electron emission current in an electric space propulsion system. A mechanical, thermal, and electromagnetic design of the cathode apparatus is presented, and a method of operation for rapid ignition and stabilization of the cathode is provided. The keeper of the cathode apparatus has a thickness change which reduces the flow of heat away from the cathode's emitter assembly. The method for heating the emitter assembly includes controlling applied voltages so that the current flowing from the emitter assembly to the keeper is maintained at a predetermined fixed value. By this method, damage to the electron emitting surfaces of the emitter assembly by electric arcing and/or by depletion of dopant materials is avoided.

A heaterless hollow cathode provides electron emission current in an electric space propulsion system. A mechanical, thermal, and electromagnetic design of the cathode apparatus is presented, and a method of operation for rapid ignition and stabilization of the cathode is provided. The keeper of the cathode apparatus has a thickness change which reduces the flow of heat away from the cathode's emitter assembly. The method for heating the emitter assembly includes controlling applied voltages so that the current flowing from the emitter assembly to the keeper is maintained at a predetermined fixed value. By this method, damage to the electron emitting surfaces of the emitter assembly by electric arcing and/or by depletion of dopant materials is avoided.

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.

This disclosure relates to systems and methods element identification and quantification. The method includes generating pulsed plasma based on an input voltage and a current so that the pulsed plasma interacts with a particle and atomizes the particle when the pulsed plasma is disposed in a flow field, identifying an atomic emission of the pulsed plasma with an optical sensor, determining element identification and quantification based on the identified emission of pulsed plasma, generating DC plasma having an electrical field based on an input DC voltage and a DC current, positioning the DC plasma in a flow field, detecting a change in the electrical field of the DC plasma, and determining a size of the particle based on the change in electrical field.

A neutralizer suitable for use in an ion engine comprises a halogen gas source and an electrode tube comprising an inlet opening connected to the halogen gas source for supplying a halogen gas provided by the halogen gas source into the electrode tube, a discharge space for generating a plasma from the halogen gas supplied into the electrode tube, and an outlet opening for discharging the plasma generated in the discharge space and free electrons from the electrode tube. An electron emitter is arranged in the discharge space of the electrode tube, which is at least partially made of tungsten, a tungsten alloy or a tungsten composite material containing at least one of iridium, rhenium, ruthenium, rhodium and osmium.