固体冷气推进剂性能初步分析  

Preliminary Analysis on Properties of Solid Cool Gas Propellant

作　　者：梁振华[1] 刘旭辉[2] 朱朋[1] 叶迎华[1] 吴立志[1] 沈瑞琪[1] 

机构地区：[1]南京理工大学化工学院,江苏南京210094 [2]北京控制工程研究所,北京100080

出　　处：《推进技术》2016年第1期181-187,共7页Journal of Propulsion Technology

基　　金：中央高校基本科研业务费专项资金资助(51201091)

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Na N3/Li F/Na2Si O3=80%/10%/10%时,分解后所含固体杂质较少;当配方为Na N3/Li F/Na2Si O3=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1m N。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 Na N3/Li F/Na2 Si O3=80%/10%/10%,meanwhile,the propellant produces less heat at the radio of Na N3/Li F/Na2 Si O3= 75.5%/15.1%/9.4%. Nitrogen production and thrust properties were characterized. Results show that 1g propellant generates0.333 L nitrogen,and the thrust of the thruster is about 1m N.

关 键 词：微推力器 固体冷气推进剂 热分析 推力测试 

分 类 号：V435[航空宇航科学与技术—航空宇航推进理论与工程]