Study on the operation process of pulsed plasma thrusters by a modified electromechanical model
- Paper number
IAC-13,C4,P,45.p1,x17060
- Author
Mr. Hua Zhang, College of Aerospace Science and Engineering, National University of Defense Technology, China
- Coauthor
Mr. Daixian Zhang, College of Aerospace Science and Engineering, National University of Defense Technology, China
- Coauthor
Dr. Rui Zhang, College of Aerospace and Materials Engineering, National University of Defense Technology, China
- Coauthor
Dr. Jianjun Wu, National University of Defense Technology, China
- Coauthor
Dr. Zhen He, College of Aerospace and Materials Engineering, National University of Defense Technology, China
- Year
2013
- Abstract
Pulsed plasma thrusters (PPTs) have been used widely in space flight mission due to their high specific impulses, low power requirements, and simple propellant management. Even with the more precise numerical simulation codes available, electromechanical models can still be used for a fast parameter variation and a quick first order design optimization of PPTs due to their simplicities. Unfortunately, the ablation process in these models is often subjected to considerable simplification. In fact, the ablation mass is always assumed to be constant or relies on empirical formulations. To gain greater insight into the ablation process, a modified electromechanical model is presented in this paper. A one-dimensional ablation model is developed that addresses the more detailed thermal and thermodynamic behavior of Teflon during simulated operation of a PPT. The operation process of a PPT is simulated by this analytic model and results of the numerical simulations are discussed. Effects of variations of electric parameters, configuration parameters and the late time ablation on PPTs’ performance are studied by numerical simulation using this modified electromechanical model.
- Abstract document
- Manuscript document
IAC-13,C4,P,45.p1,x17060.pdf (🔒 authorized access only).
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