脉冲等离子体推力器特氟隆烧蚀过程数值模拟  

Modeling of Teflon ablation in pulsed plasma thrusters

作　　者：谢泽华[1] 周进[1] 

机构地区：[1]国防科技大学高超声速冲压发动机技术重点实验室,长沙410073

出　　处：《固体火箭技术》2013年第2期210-215,共6页Journal of Solid Rocket Technology

基　　金：国家自然科学基金资助(11172327)

摘　　要：为揭示脉冲等离子体推力器推进剂的烧蚀过程对推力效率的影响,建立了特氟隆的二维两相烧蚀模型,通过与等离子体的流动传热过程进行耦合计算,开展了对推进剂烧蚀过程的数值研究。研究表明,放电过程中电极附近的推进剂表面温度更高,烧蚀速率更大;推进剂烧蚀过程与推力器的放电过程之间的匹配失衡以及放电电流的反复振荡降低了推力效率;放电后期迅速关断放电电流和对推进剂进行冷却,有助于减小因粒子发射带来的推进剂损失,从而提高推力效率。In order to reveal the effects of propellant ablation on thrust efficiency of pulsed plasma thruster, a two-dimensional two-phase model of Teflon ablation was developed. By coupling this model with plasma flow and heat analysis, the propellant abla- tion process was investigated numerically. Results show that places near the electrodes have the higher surface temperature and ab- lation rate during discharge. Results show that the mismatch of ablation and discharge process, together with the oscillation of current, decrease the thrust efficiency. Rapid cutoff of current and propellant cooling at the end of the discharge may help to reduce the propellant losses due to particulate emission, thus the thrust efficiency can be raised.

关 键 词：脉冲等离子体推力器 特氟隆 推进剂烧蚀 推力效率 

分 类 号：V438[航空宇航科学与技术—航空宇航推进理论与工程]