微波等离子体推力器流动模拟(英文)  

Simulation of microwave plasma thruster flow

作　　者：陈茂林[1] 毛根旺[1] 杨涓[1] 夏广庆[1] 

机构地区：[1]西北工业大学航天学院,西安710072

出　　处：《固体火箭技术》2009年第3期294-297,326,共5页Journal of Solid Rocket Technology

摘　　要：采用N-S方程求解了100 W微波等离子体推力器(MPT)选用不同推进工质时的性能参数;并采用直接蒙特卡洛模拟方法(DSMC)对MPT羽流进行了数值模拟。结果表明,几种工质的推力变化不大,氦气为23.6 mN,氮气为24.8mN,氩气为24.8 mN;但比冲区别较大,氦气为565.2 s,氮气为243.7 s,氩气为180.2 s。羽流场中,密度、压强及温度沿轴向和径向均逐渐减小;轴向速度在轴线附近变化不大,采用氩气工质时,约1 700 m/s,在远离轴线区域,沿流动方向逐渐增大,沿径向逐渐减小;径向速度沿轴向变化不大,沿径向逐渐增大,并在接近流动区域边界时迅速减小。The performanee of 100 W microwave plasma thruster （MPT） with different propellants was calculated with N-S equations, and the plume was simulated by the direct simulation Monte-Carlo （DSMC） method. Results show that the thrust seldom ehanges under various propellants, being 23.6 mN for helium, 26.5 mN for nitrogen and 24.8mN for argon; while the speeific impulse has great difference. The specific impulse is 5 652 N · s/kg for helium as propellant, 2 437 N · s/kg for nitrogen and 1 802 N · s/kg for argon respectively. In plume, the density, pressure and temperature reduce along the axial direction and the radial direction. The axial velocity changes a little near the axes, about 1 700 m/s for argon propellant, while it velocity increases along the axial direction and decreases along the radial direction far away from the axes;and the radial velocity increase along the radial direction but it rapidly decreases near flow region boundary.

关 键 词：微波等离子体推力器 羽流 直接蒙特-卡洛模拟方法 

分 类 号：V439[航空宇航科学与技术—航空宇航推进理论与工程]