固体冷气推进剂性能初步分析

推进技术 ›› 2016, Vol. 37 ›› Issue (1): 181-187.

固体冷气推进剂性能初步分析

梁振华¹,刘旭辉²,朱朋¹,叶迎华¹,吴立志¹,沈瑞琪¹

南京理工大学化工学院，江苏南京 210094,北京控制工程研究所，北京 100080,南京理工大学化工学院，江苏南京 210094,南京理工大学化工学院，江苏南京 210094,南京理工大学化工学院，江苏南京 210094,南京理工大学化工学院，江苏南京 210094

发布日期:2021-08-15
作者简介:梁振华，男，硕士生，研究领域为固体冷气微推力器。E-mail: liang_zhenh@qq.com 通讯作者:沈瑞琪，男，博士，教授，研究领域为激光物理和化学、化学芯片技术、推进技术、复杂化学系统仿真技术、含能材料的燃烧和爆炸控制技术等方面。
基金资助:
中央高校基本科研业务费专项资金资助(51201091)。

Preliminary Analysis on Properties of Solid Cool Gas Propellant

School of Chemical Engineering，Nanjing University of Science and Technology，Nanjing 210094，China,Beijing Institute of Control Engineering，Beijing 100080，China,School of Chemical Engineering，Nanjing University of Science and Technology，Nanjing 210094，China,School of Chemical Engineering，Nanjing University of Science and Technology，Nanjing 210094，China,School of Chemical Engineering，Nanjing University of Science and Technology，Nanjing 210094，China and School of Chemical Engineering，Nanjing University of Science and Technology，Nanjing 210094，China

Published:2021-08-15

摘要/Abstract

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

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

梁振华,刘旭辉,朱朋,叶迎华,吴立志,沈瑞琪. 固体冷气推进剂性能初步分析[J]. 推进技术, 2016, 37(1): 181-187.

LIANG Zhen-hua¹,LIU Xu-hui²,ZHU Peng¹,YE Ying-hua¹,WU Li-zhi¹,SHEN Rui-qi¹. Preliminary Analysis on Properties of Solid Cool Gas Propellant[J]. Journal of Propulsion Technology, 2016, 37(1): 181-187.

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