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Investigation of influence of charging-discharging processes on functioning of spacecraft correction system with high-impulse stationary plasma truster

DOI 10.18127/j19998465-201812-12

Keywords:

R.E. Tikhomirov – Leading Engineer, JSC Academician M.F. Reshetnev «ISS» (Zheleznogorsk)
E-mail: tikhroman@gmail.com
D.A. Trofimchuk – Head of Group, JSC Academician M.F. Reshetnev «ISS» (Zheleznogorsk)
I.A. Maksimov – Dr.Sc.(Eng.), Head of Department, JSC Academician M.F. Reshetnev «ISS» (Zheleznogorsk)
E-mail: mia@iss-reshetnev.ru
S.G. Kochura – Ph.D.(Eng.), Associate Professor, Deputy General, JSC Academician M.F. Reshetnev «ISS» (Zheleznogorsk)
E-mail: kochura@iss-reshetnev.ru


The elements of construction of electric propulsion system of spacecraft (SC) correction can accumulate electrostatic charge due to interaction with the magnetospheric plasma. The impact of electrostatic discharges on the electrical circuit of the correction system can lead to failures of the transformation and control system (TCS).
The results of investigation of spacecraft charging influence on functioning of geostationary spacecraft correction system with high-impulse stationary plasma truster are described in this article. The authors developed the mathematical model of charging impact on the correction system with stationary plasma truster. Using this model the parameters of charging – discharging processes on ceramic isolator of SPT were obtained. For propose of model verification the experimental researching of charging parameters and investigation of discharge processes impact on TCS electric circuits was done. Obtained results are able to usage in spacecraft correction system designing.

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