Particle‐in‐cell simulation of an optimized high‐efficiency multistage plasma thruster

Abstract

Electric propulsion attracts increasing attention in contemporary space missions as an interesting alternative to chemical propulsion because of the high efficiency it offers. The High‐Efficiency Multistage Plasma thruster, a class of cusped field thruster, is able to operate at different anode voltages and operation points and thereby generate different levels of thrust in a stable and efficient way. Since experiments of such thrusters are inherently expensive, multi‐objective design optimization (MDO) is of great interest. Several optimized thruster designs have resulted from a MDO model based on a zero‐dimensional (0D) power balance model. However, the MDO solutions do not warrant self‐consistency due to their dependency on estimation from empirical modelling based on former experimental studies. In this study, one of the optimized thruster designs is investigated by means of particle‐in‐cell (PIC) analysis to examine the predicted performance characteristics with self‐consistent simulations. The 0D power balance model is used to develop additional diagnostics for the PIC simulations to improve the physics analysis. Using input parameters for the 0D power balance model from the PIC simulations allows further improvement for the design optimization.

Ion Electric Propulsion System Electric Breakdown Problems: Causes, Impacts and Protection Strategies

“…In low pressure, PIC simulation is more suitable than fluid model to simulate the behavior of charged particles [7], [106], [107]. These simulations provide a detailed understanding of the plasma dynamics, including particle trajectories, collisions, and interactions with electric fields.…”

“…With the fast development of aerospace technology in the past decades [1]- [3], the space missions require reliable and high-performance propulsion systems, especially electric propulsion systems [4]- [6]. Although the traditional chemical thruster can produce high thrust, the electric thruster can generate a much larger exhaust velocity of the propellant than that of the chemical thruster by heating or ionizing the propellant and forming a high speed jet [7], [8]. It means the electric thruster can change the velocity of the aerospace with a much smaller propellant mass, which is suitable and has been widely used in spacecraft and satellite power systems [9], [10].…”

PIC Simulations of the MS4 Thruster

“…Thus, cheaper methods for design optimization are needed. Computer simulations, such as the Particle-in-Cell (PIC) model, have shown successfully their potential for design optimization, especially in combination with simpler balance equation models using genetic algorithms [4,5].…”