Analysis and Particle-in-Cell Simulation of Gridded ICRH Plasma Thruster

TL;DR

This paper explores a hybrid plasma thruster combining ion cyclotron resonance heating and electrostatic acceleration, using particle-in-cell simulations to compare exhaust velocities of different propellants, highlighting Xenon as the most suitable.

Contribution

It introduces a novel hybrid plasma thruster design and uses simulations to analyze its performance with various gases, emphasizing the potential for high specific impulse in space propulsion.

Findings

Xenon achieves a specific impulse over 4200 s.

Electrostatic acceleration dominates exhaust velocity.

Hybrid system significantly increases exhaust velocity.

Abstract

Large-payload deep space missions are impractical with current rocket propulsion technologies in use. Chemical thrusters yield a high thrust but low efficiency while ion thrusters are efficient but provide too little thrust for large satellites and manned spacecraft. Plasma propulsion is a viable alternative with a higher thrust than electric ion thrusters and specific impulse far exceeding those of chemical rocket engines. 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.