摘要
将三维MHD双温入口模型的计算结果作为入口条件,运用DSMC(Direct Simulation Monte-Carlo)/PIC(Particle in Cell)流体混合算法,模拟实验室PPT样机羽流。验证计算显示,该模型具有模拟脉冲等离子体推力器羽流的能力。对不同初始电压和电容下的羽流场进行了模拟,给出了出口平面返流质量流率的变化情况和20μs羽流中离子和CEX离子的分布情况。计算结果显示,高能量状态对应高质量流率,高质量流率对应高动量,高动量离子和中性粒子对航天器撞击会造成更强影响。
DSMC（Direct Simulation Monte-Carlo）/PIC（Particle in Cell） fluid hybrid method was used to simulate the Laboratory PPT（pulsed plasma thruster） sample plume from end to end with the boundary condition from three-dimension MHD two-temperature entrance model.The plumes at different initial voltage and capacitance were simulated.The results show that the PPT plume from end to end could be simulated by this model.The variation of backflow mass flux on the plane above the thruster exit and distribution of plume ion and CEX ion at different capacitance were achieved.It shows that high energy brings about high mass flow-rate and high mass flow-rate brings about high momentum,the impact of ion and neutral particles with high momentum have stronger influence on spacecraft.
出处
《固体火箭技术》
EI
CAS
CSCD
北大核心
2010年第6期660-666,共7页
Journal of Solid Rocket Technology
基金
国家自然科学基金资助项目(No.10772195)
