小功率电弧喷射发动机的数值计算

推进技术 ›› 2002, Vol. 23 ›› Issue (5): 370-374.

小功率电弧喷射发动机的数值计算

汤海滨,刘宇,张正科

北京航空航天大学宇航学院北京100083;北京航空航天大学宇航学院北京100083;北京航空航天大学宇航学院北京100083

发布日期:2021-08-15
基金资助:
国家自然科学基金资助项目(50086001)。

Numerical calculation on low power arcjet thrusters

School of Astronautics, Beijing Univ. of Aeronautics and Astronautics, Beijing 100083, China;School of Astronautics, Beijing Univ. of Aeronautics and Astronautics, Beijing 100083, China;School of Astronautics, Beijing Univ. of Aeronautics and Astronautics, Beijing 100083, China

Published:2021-08-15

摘要/Abstract

摘要： 为详细了解电弧喷射发动机内部工作过程和相关工作参数对其性能的影响,参照实验用发动机的工作参数建立了模型,数值模拟了电弧喷射发动机工作通道内流场和电磁场。利用NND格式求解耦合电磁源项N S方程,Gauss Seidel迭代加超松弛方法求解椭圆型电磁场方程,计算得到的发动机工作通道内流场、电磁场结构,与实验数据进行了对比。结果表明,对同一结构尺寸的发动机,随推进剂流量变化,发动机性能存在最佳值;在一定流量范围内,实验数据和计算结果相符。

关键词: 电弧喷射发动机;等离子体射流;流动分布;数值仿真

Abstract: In order to realize the work process on arcjet thrusters in detail and study their operating performance, a fluid dynamics model was developed and the work channels of thruster were numerically simulated and analyzed. Using the operating parameters of experimental thrusters, Non oscillatory and Non free parameters Dissipative (NND) explicit scheme was applied to solve N S equation with coupling electromagnetic sources by time dependent method, Gauss Seidel iteration and successive overrelaxation (SOR) technique to solve elliptic electric potential equation. Flow fields and electromagnetic fields of work channels were obtained. Test data were compared with numerical results. The results showed that there was a high thruster performance with propellant mass flow changed. The calculated results showed good agreement with the test results to a certain extent.

Key words: Arcjet thruster;Plasma jet;Flow distribution;Numerical simulation

汤海滨,刘宇,张正科. 小功率电弧喷射发动机的数值计算[J]. 推进技术, 2002, 23(5): 370-374.