In this work, the energy characteristics for four designed propellants were studied using thermal investigations. Thermal degradation due to different proportions of the LS/NC formula and different proportions of the LS/SQ-2 propellants were investigated using a differential scanning calorimeter and thermogravimetry. It was found that due to different proportions of the best propellants, the energy and heat sensitivity could meet the requirements for micro-thrusters. Furthermore, it was demonstrated that the quality of different charge micro-thrusters by the impulse tests was consistent with the thermal investigations.