Numerical validation of a zero-field micro-MPD thruster baseline (Part I)

The objective of the current study is to establish and validate a simple numerical framework that approximates the internal electrothermal flow behavior of a micro-scale MPD thruster under zero-field (B = 0) conditions. The present work intentionally excludes applied magnetic field effects and air-breathing operation, and instead focuses on a baseline validation using argon as a calibration gas. The small simulation model is validated through comparison with a literature MPD thruster case and with micro-MPD experimental results. As a result, thrust and specific impulse due to Joule heating are generally reproduced for both cases. This study constitutes Part I of a two-stage program and provides a prerequisite baseline for applied-field and air-breathing simulations to be addressed in Part II.