Thruster Particle-in-Cell Simulation

In this paper, a hybrid thruster is explored which affords the high mass flow rate of plasma thrusters while maximizing the specific impulse. The two primary processes of this system are the ion cyclotron resonance heating of plasma and subsequent electrostatic acceleration of ions with gridded electrodes. Through a particle-in-cell simulation of these two components, the exhaust velocities of Xenon, Argon, and Helium are compared.

It has been found that while the combination of systems results in a far greater exhaust velocity, the acceleration is largely from the gridded electrodes, and thus Xenon is the most suitable propellant with a specific impulse upward of 4200 s. Advancements in nuclear fusion and fission technologies will facilitate the deployment of high-power plasma thrusters that will enable spacecraft to travel farther and faster in the solar system.