Study on Plasma Characteristics in a Pulsed Plasma Thruster by Optical Emission Spectroscopy
ZHANG Hua1, WU Jian-jun1*, HE Zhen1, LI Shi-liang2, ZHANG Yu1
1. College of Aerospace Science and Engineering, National University of Defense Technology, Changsha 410073, China 2. College of Basic Education, National University of Defense Technology, Changsha 410073, China
Abstract：The pulsed plasma thruster(PPT) is suited for various applications, e. g., attitude control, station keeping and formation flying due to its significant advantage with regard to the related savings of wet system mass，small volume and high specific impulse. In order to elaborate the mechanism of PPT operation process, the optical emission spectrum was conducted on a breech-fed PPT with tongue electrodes. The results show that plasma plume mainly consists of C, F, C+, F+ and C2+, besides Cu+ and Cu2+ were detected in plasma which were produced by electrodes ablation. The plasma distribution is asymmetric in the discharge channel, the maximum of plasma density of plasma appears at the central axis of discharge channel and the plasma density nearby the anode is much higher than that nearby the cathode. The composition of plasma is not symmetric and not uniform. The distribution of F+ and neutral particle concentrate close to the anode. The electron temperature is about 6.67 eV derived from the optical emission spectra by Boltzmann linear fitting. Evolution of plasma emission spectrum was derived at the fourth measurement point, the results show that there is much difference between different discharge stages for the composition of plume and the proportion of each component.
Key words：Pulsed plasma thruster;Plume;Optical emission spectrum;Plasma composition;Plasma temperature
张 华1，吴建军1*，何 振1，李是良2，张 宇1. 脉冲等离子体推力器等离子体羽流的光谱研究[J]. 光谱学与光谱分析, 2016, 36(06): 1867-1871.
ZHANG Hua1, WU Jian-jun1*, HE Zhen1, LI Shi-liang2, ZHANG Yu1. Study on Plasma Characteristics in a Pulsed Plasma Thruster by Optical Emission Spectroscopy. SPECTROSCOPY AND SPECTRAL ANALYSIS, 2016, 36(06): 1867-1871.
[1] Sackheim R L. J. Propul. Power, 2006, 22: 1310. [2] ZHANG Hua, WU Jian-jun, ZHANG Dai-xian, et al(张 华，吴建军，张代贤，等). Acta Phys. Sin. (物理学报), 2013, 62: 210202. [3] Burton R L, Turchi P J. J. Propul. Power, 1998, 14: 716. [4] Schonherr T, Komurasaki K, Herdrich G. World Acad. Sci. Eng. Technol., 2011, 50: 557. [5] Markusic T E, Choueiri E Y, Berkery J W. Phys. Plasmas, 2004, 11: 4847. [6] Vondra R J, Thomassen K, Solbes A. J. Spacecraft, 1970, 7: 1402. [7] Koizumi H, Noji R, Komurasaki K, et al. Phys. Plasmas, 2007, 14: 033506. [8] Keidar M, Boyd I D, Antonsen E, et al. J. Propul. Power, 2004, 20: 961. [9] Schonherr T, Nees F, Arakawa Y, et al. Phys. Plasmas, 2013, 20: 033503. [10] Zhang R, Zhang D, Zhang F, et al. Applied Surface Science, 2013, 270: 352.
