摘要
采用粒子网格单元与蒙特卡洛碰撞相结合的方法，建立霍尔效应推力器羽流的二维轴对称模型。模型中电子作为流体处理且服从等熵假设，离子（Xe＋和Xe2＋）采用粒子描述，中性原子为背景气体。自洽电势通过求解非准中性、线性化Poisson方程获得。模拟结果与实验数据相比较表明，模型能够可靠预估羽流的物理特性；粒子入射发散角为30°-40°时模拟结果与实验数据吻合较好；倒流区离子数密度可达10^14m^-3，会对飞行器表面造成损害；且等离子体密度和电子温度沿轴线方向衰减很快。
A two-dimensional axisymmetric hybrid particle-in-cefl and Monte Carlo Collision model is developed to study the Hall effect thruster plume. The model is based on a fluid description of electrons with a non-isothermal temperature obeying isentropic assumption and a particle description of ionic components （ Xe ＋ and Xe2＋） , and the neutral atoms are set as background. The self-consistent electric potential is obtained from non quasi-neutrality and linear Poisson equation. Comparisons of simulation resuits with experimental data suggest that the model can be used to reliably predict physics characteristics of the plume. With the particle injected divergence angle of 30° ~ 40°, a better agreement with experiment results can be obtained. The ion number density of 10^14m-3 can in the baekflow region, which cause damages to the spacecraft surface. And the plasma density and electron temperature fall quickly along the axial line.
出处
《固体火箭技术》
EI
CAS
CSCD
北大核心
2009年第6期638-643,共6页
Journal of Solid Rocket Technology
