An interest in the development of subkilogram forms of satellite micropropulsion has led to the design of the micro-laser plasma thruster ( LPT). Previous work succeeded in constructing a working computational model of the micro-thruster’s operation in the magnetohydrodynamic code MACH2; however, the previous work was limited to simulating only the non-energetic solid propellant ablation mode of the thruster. Recent experiments have shown that the use of an exothermic propellant might be more benecial for higherthrust modes of operation. This work reviews improvements made to the computational model to simulate both the sub-detonation experimental ablation and laser-supported detonation of the glycidyl azide polymer fuel used in experiments. Simulation results indiciate that the sub-detonation ablation of this fuel demonstrates an improvement in the coupling coecient of 70% and in the specic impulse of 20% over the non-energetic solid-propellant case. The laser-supported detonation shows an increase in the coupling coecient and specic impulse over the baseline solid-propellant case by at least two orders of magnitude. The laser-supported detonation simulation also indicates vast damage to the fuel tape, but the possibility of implementing rigid-wall boundary conditions to the fuel tape is presented.