Mechanisms for the Formation of Parasitic Propellant Consumption in an Ablative Pulsed Plasma Thruster
- Authors: Bogatyi A.V.1, D’yakonov G.A.1, Semenikhin S.A.1
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Affiliations:
- Research Institute of Applied Mechanics and Electrodynamics, Moscow Aviation Institute
- Issue: Vol 57, No 5 (2019)
- Pages: 310-316
- Section: Article
- URL: https://journals.rcsi.science/0010-9525/article/view/153501
- DOI: https://doi.org/10.1134/S0010952519050010
- ID: 153501
Cite item
Abstract
Results of spectroscopic studies of electric discharge stages in the channel of an ablative pulsed plasma thruster (APPT) are presented. The initial stage has been shown to affect further discharge development. Shock surface ionization of the propellant has been found to be the dominant mechanism for “parasitic” propellant consumption of an APPT. The results of experimental studies of the dependence of propulsion efficiency and consumption on the distance between operating surfaces of APPT propellant bars are given.
About the authors
A. V. Bogatyi
Research Institute of Applied Mechanics and Electrodynamics, Moscow Aviation Institute
Author for correspondence.
Email: riame@sokol.ru
Russian Federation, Moscow, 125993
G. A. D’yakonov
Research Institute of Applied Mechanics and Electrodynamics, Moscow Aviation Institute
Email: riame@sokol.ru
Russian Federation, Moscow, 125993
S. A. Semenikhin
Research Institute of Applied Mechanics and Electrodynamics, Moscow Aviation Institute
Email: riame@sokol.ru
Russian Federation, Moscow, 125993
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