Abstract
An inductive pulsed plasma thruster (IPPT) operates by pulsing high current through an inductor, typically a coil of some type, producing an electromagnetic field that drives current in a plasma, accelerating it to high speed. The IPPT is electrodeless, with no direct electrical connection between the externally applied pulsed high-current circuit and the current conducted in the plasma. Several different configurations were proposed and tested, including those that produce a plasma consisting of an accelerating current sheet and those that use closed magnetic flux lines to help confine the plasma during acceleration. Specific impulses up to 7000 s and thrust efficiencies over 50% have been measured. The present state-of-the-art for IPPTs is reviewed, focusing on the operation, modeling techniques, and major subsystems found in various configurations. Following that review is documentation of IPPT technology advancement paths that were proposed or considered.
Highlights
An inductive pulsed plasma thruster (IPPT) is a spacecraft propulsion system that uses short, high current electrical pulses flowing through an inductive coil or set of coils to drive currents in a plasma and expel it at high speed
We have presented a review of state-of-the-art IPPT research and development for both open and closed magnetic flux thruster types
The former is characterized by accelerators that rely on current sheets to entrain and accelerate propellant while the latter typically involves the formation of a compact toroid (FRC or plasmoid) with embedded magnetic fields
Summary
An inductive pulsed plasma thruster (IPPT) is a spacecraft propulsion system that uses short, high current electrical pulses flowing through an inductive coil or set of coils to drive currents in a plasma and expel it at high speed. While the thruster types described in this paper have unique aspects to their operation, at a high level IPPTs operate through a combination of Ampère’s and Faraday’s laws, given respectively as: Aerospace 2020, 7, 105; doi:10.3390/aerospace7080105 www.mdpi.com/journal/aerospace In these equations the electric and magnetic field vectors are E and B, the current density vector is j, and the permeability of free space is μ0. The other category is comprised of thrusters in which closed magnetic flux surfaces are embedded within and aid in confinement of the plasma Plasmas in this configuration are generally known as compact toroids, with those under development for spacecraft propulsion known as field-reversed configuration (FRC) thrusters [5] or plasmoid thrusters [6]. Following the same structure as the review of the present state-of-the-art, we provide a discussion of various potential means to improve different thruster variant designs by enhancements to current modeling capabilities and through advancement in the capabilities of specific subsystems and components
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