Computational Investigations of Performance Improvements for Microlaser Ablation Plasma Thrusters Using Nozzles

Recent work has investigated the microlaser ablation plasma thruster, which is a subkilogram form of satellite propulsion. Computational simulations that investigate the microthruster operation by the ablation of plasma through a nozzle using a magnetohydrodynamic code are presented. The performance improvement to the microthruster with a nozzle is compared with previous simulations wherein a passive solid propellant was ablated without a nozzle. The model provides insight to the plasma generation and expansion from the fuel tape. Results show up to a 36% improvement in the laser momentum coupling coefficient and up to 50% improvement in specific impulse.