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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1014m-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 model of Hall effect thruster plume is established by combining particle grid element and Monte Carlo collision. In the model, the electrons are treated as fluids and subject to isentropic assumptions. The ions (Xe + and Xe2 +) are described by particles and the neutral atoms are the background gases. The self-consistent potential is obtained by solving a non-quasi-neutral, linear Poisson’s equation. The results of simulation and experimental data show that the model can predict the physical properties of plume reliably. The simulation results agree well with the experimental data when the incident angle of incidence is 30 ° ~ 40 °. The number density of ions in the backflow area can reach 1014m -3 , Can cause damage to the aircraft surface; and the plasma density and electron temperature decay rapidly along the axis.