| 摘要: |
| 为了设计出合理的固体冷气微推力器，固体冷气推进剂的研究显得尤为重要。通过理论计算得出固体冷气推进剂各组分的配比，利用DSC-TG测试技术研究其热分解反应性能，最终得出当固体冷气推进剂配方为NaN3/LiF/Na2SiO3= 80%/10%/10%时，分解后所含固体杂质较少；当配方为NaN3/LiF/Na2SiO3= 75.5%/15.1%/9.4%时，反应放热量较低。研究了固体冷气推进剂的产气和推进性能，结果表明每1g推进剂可产生约0.333L的氮气，推力器所产生的推力约为1mN。 |
| 关键词: 微推力器 固体冷气推进剂 热分析 推力测试 |
| DOI： |
| 分类号: |
| 基金项目:中央高校基本科研业务费专项资金资助(51201091)。 |
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| Preliminary Analysis on Properties of Solid Cool Gas Propellant |
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LIANG Zhen-hua1,LIU Xu-hui2,ZHU Peng1,YE Ying-hua1,WU Li-zhi1,SHEN Rui-qi1
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(1.School of Chemical Engineering，Nanjing University of Science and Technology，Nanjing 210094，China;2. Beijing Institute of Control Engineering，Beijing 100080，China)
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| Abstract: |
| In order to design a reasonable solid cool gas thruster，research on the solid cool gas propellant is particularly important. The components of solid cool gas propellant were obtained by means of theoretical calculation，and then，the thermal decomposition was characterized with Differential Scanning Calorimetry and Thermogravimetric Analysis (DSC-TG). The propellant produces less impurities at the ratio of NaN3/LiF/Na2SiO3= 80%/10%/10%，meanwhile，the propellant produces less heat at the radio of NaN3/LiF/Na2SiO3= 75.5%/15.1%/9.4%. Nitrogen production and thrust properties were characterized. Results show that 1g propellant generates 0.333L nitrogen，and the thrust of the thruster is about 1mN. |
| Key words: Micro thruster Solid cool gas propellant Heat analysis Thrust test |
