A Neutralizer for an ion thruster of a spacecraft comprises a cathode for emission of electrons, a support with an opening inside which the cathode is supported in a radially spaced manner, and an electrically conductive shielding which surrounds said opening and is electrically insulated from the support, wherein a ring is mounted between the shielding and the cathode and is electrically insulated from the shielding and radially spaced from the cathode.

The present technology is directed to plasma systems and associated methods, including propulsion systems for flight vehicles. A representative system includes a plurality of coils. The coils include a first coil positioned along a force axis, a second coil positioned along the force axis and spaced apart from the first coil, and a third coil that is magnetically shielded. A controller is operatively coupled to the coils and is configured to (a) increase energy to the first coil to generate a magnetic field in a portion of the plasma adjacent to the first coil, (b) decrease energy to the first coil and increase energy to the second coil to translate the resulting superposed magnetic field through the plasma to a position adjacent the second coil, and (c) transfer energy from the second coil to the third coil and decrease energy to the second coil to reduce the magnetic field in the plasma.

A device for forming a quasi-neutral ion-electron beam, including: a chamber; a set of means for forming an ion-electron plasma in the chamber; and means for extracting and accelerating charged particles from the plasma out of the chamber. The particles are capable of forming the beam and the extraction and acceleration means that include a set of at least two grids located at one end of the chamber.

Plasma which is supplied from a supply passage (1) is accelerated with a Hall electric field (E) which is generated through interaction of electrons (e.sup.) emitted from a cathode (3), a radial direction magnetic field (Bd), and an electric field (Ex).

A plasma motor for extracting a positive ion flow has a single ionization stage and a device for supplying the ionization stage with an ionizable electronegative gas. The plasma motor further has a device for creating an electric field so as to produce the ionization of the gas in the ionization stage. The device for creating the electric filed includes a device for extracting a negative ion flow and, a device for extracting a positive ion flow, connected to the ionization stage. The extraction of a positive ion flow and the extraction of a negative ion flow are of the same amplitude, ensuring the electrical neutrality of the motor. The extraction of a positive ion flow and the extraction of a negative ion flow allow the neutrality of the motor to be ensured.

An electron acceleration device using thermionic fission cells and an electromagnetic scoop coil for power. A power control junction and electron injector control that feeds free electrons in packets into the acceleration components that consist of a series of induction linac module units, having quadrupole magnet units in series between the induction module units. Has on-board xenon gas for a deep space electron source. At the high speed electrons exit from the device, deflector plates control the exit path of the electrons to direct the course of a craft.

A device for forming a quasi-neutral ion-electron beam, including: a chamber; a set of means for forming an ion-electron plasma in the chamber; and means for extracting and accelerating charged particles from the plasma out of the chamber. The particles are capable of forming the beam and the extraction and acceleration means that include a set of at least two grids located at one end of the chamber.

A propulsion device for vehicles, such as a spacecraft operating within a vacuum configured to ionize a fuel gas. Specifically, a soft ionization system pulls electrons from passing gas molecules directly into conductors and introduces ionized gas molecules into a static accelerating field. The ionized gas is utilized at a point of creation such that a chamber, housing, or channel to contain the ionized gas is not required.

A method of operating a spacecraft propulsion system comprises injecting electrons into the plasma surrounding the spacecraft prior to creating the stream of ions, and after commencing creation of the ion stream, continuing the injection of electrons in an amount sufficient to maintain the spacecraft at a positive potential. This method may be implemented in a single thruster. In spacecraft with multiple thrusters the same method may be implemented in each thruster. Where the propulsion system comprises a plurality of thrusters, the method may comprise: operating at least one of the thrusters as a drive thruster, and operating at least one of the thrusters as an auxiliary or reserve thruster. The electron source of the at least one auxiliary thruster may be operated before creation of the ion stream to inject the electrons into the plasma surrounding the spacecraft.