Conical plume model calibration of the stationary plasma thruster by the thruster integral parameters

Aeronautical and Space-Rocket Engineering

Thermal engines, electric propulsion and power plants for flying vehicles


DOI: 10.34759/vst-2019-4-144-155

Аuthors

Nadiradze A. B.1*, Frolova Y. L.2**, Zuyev Y. V.2***

1. ,
2. Moscow Aviation Institute (National Research University), 4, Volokolamskoe shosse, Moscow, А-80, GSP-3, 125993, Russia

*e-mail: nadiradze@mai.ru
**e-mail: ylfrolova@yandex.ru
***e-mail: yuri_zuev@bk.ru

Abstract

The article presents the analysis of possible reasons for divergence of parameters measured under laboratory conditions and realized in space, based on application of multi-fractional conical model of the stationary plasma thruster jet. Three possible methods for the jet model calibration by the thruster integral parameters, such as discharge current, flow-rate and engine thrust were considered. The study of measuring conditions impact on the jet integral parameters was conducted. The need for calibration is stipulated by the fact that jet measured parameters may incorporate essential errors associated with the effect of experiment conditions and vacuum chamber walls. Calibration coefficients, linking measured and integral parameters of the jet, such as total ion current, flow-rate by ions and the jet axial impulse, are being introduced to minimize errors. Inasmuch as the jet integral parameters are being measured with high precision, the thruster jet model accuracy may be significantly increased after calibration.

The calibration methods regarded in the article allow obtain concurrence either by current density or by the flow-rate, or by the thrust (axial pulse). Jet calibration by the ion current and ions flow-rate gives the undervalued thrust value. Calibration by the thrust gives the jet parameters estimation for the worst case (overvalued parameters by the ion current and flow rate) necessary for analyzing the jet impact on a spacecraft. However, it is impossible to obtain the exact concurrence for parameters due to the effect of jet «disintegration» caused by interaction between the accelerated ions and neutral particles. Besides, the particles of residual atmosphere in vacuum chamber may affect the processes of jet formation in the acceleration channel of the thruster. To obtain more accurate jet model, it is necessary to account for the above-mentioned factors, and to use more complicate correction methods.

Keywords:

electric propulsion thruster, plasma plume, conical model, model calibration, probe measurements, residual gas pressure

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