Simulative and experimental study of plasma distribution of Electric Propulsion Thruster
- Paper number
IAC-14,C2,P,35,x21705
- Author
Dr. Qin Xiaogang, China
- Coauthor
Mr. Yifeng Chen, China Aerospace Science and Technology Corporation (CASC), China
- Coauthor
Dr. Shengsheng Yang, Lanzhou Institute of Physics, China
- Year
2014
- Abstract
The increasing of satellite on orbit life makes the Electric Propulsion Thruster more and more attractively. Electric Propulsion Thruster emits a plasma plume with both fast beam ions and slow charge exchange particles, and the plasma impacts the charging environment and surface potential. In this paper, a PIC (particle-in-cell) model is applied to investigate the plasma distribution of Electric Propulsion Thruster, and a LP probe is used to measure the density and temperature of the electron in the plasma. The results indicate that the plasma density of Electric Propulsion Thruster is in the range of 1E8m-3 to 1E15m-3, and the simulative result agree with the experiment well.
- Abstract document
- Manuscript document
(absent)