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ABSTRACT
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.
Funding
This project is jointly supported by the Special National Foundation of China (Grant No. 13317) and the International Cooperation Project in Shanxi Province (Grant No. 2015KW-08)