微波等离子体推力器流动模拟(英文)

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,氮气为23.6 mN,氮气为24.8mN,氩气为24.8 nuN;但比冲区别较大,氮气为565.2 s,氮气为243.7 8,氢气为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.

Simulation of microwave plasma thruster flow

The performance of 100 W microwave plasma thruster (MPT) with different propellants was calculated with N-S e-quations, and the plume was simulated by the direct simulation Monte-Carlo (DSMC) method. Results show that the thrust seldom changes under various propellants, being 23.6 mN for helium, 26.5 mN for nitrogen and 24.8mN for argon; while the specific im-pulse 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 ra-dial direction. The axial velocity changes a little near the axes, about 1 700 m/s for argon propellant, while it velocity increases a-long the axial direction and decreases along the radial direction far away from the axes;and the radial velocity increase along the ra-dial direction but it rapidly decreases near flow region boundary.