A model for macro-performances applied to low power coaxial pulsed plasma thrusters. (May 2020)

• Record Type: Journal Article
• Authors: Li, Hang; Wu, Zhiwen; Sun, Guorui; Zhu, Kangwu; Huang, Tiankun; Liu, Xiangyang; Ling, William Yeong Liang; Wang, Ningfei
• Is Part Of: Acta astronautica. Volume 170(2020)
• Page Start: 154
• Page End: 162
• Publication Date: 2020-05
• Subjects: Coaxial pulsed plasma thruster -- Model simulation -- Macro-performances estimation; Astronautics -- Periodicals; Outer space -- Exploration -- Periodicals; Astronautics; Periodicals; 629.405
• DOI: 10.1016/j.actaastro.2019.11.014
• Languages: English
• ISSNs: 0094-5765

Abstract

Abstract: Pulsed plasma thrusters (PPT), as an important developing direction of micro-satellite propulsion system, are attracting more and more attention. Low power coaxial PPT has great advantages in miniaturization because of its coaxial structure, which is beneficial for micro-satellite applications. Since there are few macro-performances estimation model in low power coaxial PPT, this paper establishes a model based on one-dimensional electromechanical PPT model and gas dynamic pressure forces model to describe macro-performances of low power coaxial PPT. In this model, the electromechanical model describes the plasma electromagnetic acceleration process, current and voltage changes of the main circuit during the discharge process, and the gas dynamic pressure forces model describes the expansion and acceleration of the neutral gas group in the discharge channel. To verify the model, we compared the voltage and current obtained from model simulation with the experimental results, and compared the impulse bit measured in the experiment with the impulse bit calculated by the model. The results show that the model established in this paper can well simulate the variation of voltage and current during the working process of low power coaxial PPT, and can preliminarily estimate the macro performances of the thruster. Highlights: Model based on the one-dimensional electromechanical PPT model and gas dynamic pressure forces model. The establishment of the model is described in detail. A series of experiments were carried out to verify the validity and feasibility. The simulation results show good agreement with the experimental results and the model can preliminarily estimate the macro performances of the thruster.