Multiple mode cathode-compensator developing for the stationary plasma thruster

Aeronautical and Space-Rocket Engineering

Thermal engines, electric propulsion and power plants for flying vehicles


Аuthors

Katashova M. I.1*, Parakhin G. A.1**, Rumyantsev А. V.2***

1. Experimental Design Bureau “Fakel”, 181, Moskovsky av, Kaliningrad, 236001, Russia
2. Immanuel Kant Baltic Federal University, IKBFU, 14, A. Nevskogo str., Kaliningrad, 236041, Russia

*e-mail: katashova@fakel-russia.com
**e-mail: info@fakel-russia.com
***e-mail: albert37@list.ru

Abstract

There is a need today in creating a highly efficient multi-mode stationary plasma thruster capable of both inter-orbital transfer and spacecraft position keeping in a set point. A multi-mode cathode-compensator capable of operating at a discharge current up to 15 A is needed for this purpose. The cathode operates on the principle of a gas-electric source of electrons based on a hollow cathode, and it is the most thermally and energy intensive element of the thruster. The K-3/15 cathode structure was designed and studied experimentally on the possibility of flame operation in at least two modes within the discharge current ranges fr om 3 to 5 A and from to 15 A at the experimental design bureau “Fakel” base. The main purpose of the К-3/15 tests was verifying the cathode operability at various start-up powers, propellant flow rates and discharge currents to determine optimal start-up modes. In the process of stand-alone testing, it was determined that the optimal start-up mode for the cathode is a start lies within (160±5) sec at the heating power of 130-139 W and at the cathode flow rate from 30 to 0.60 mg/s. A special attention was paid to determining the current-voltage and voltage-flow rate characteristics in the discharge current range from 3 to 15 A at propellant flow rates to the cathode in the range from 0.30 to 0.60 mg/s. A comparative analysis of the main characteristics of the КН-3В cathode and К-3/15 cathode was performed as well. It was revealed, that compared to the KH-3B cathode the cathode K-3/14 current effectiveness value would manifest itself at the high-current modes (above 10 A), wh ere this parameter value was three times lower. It was determined that the K-3/15 cathode ensured the multi-mode operation with respect to the discharge current and had much higher resource parametrics compared to the KH-3B cathode. It is being forecasted, that parameter changing of the thermo­emitter from mono-crystal lanthanum hexaboride will allow three times increase of the flame operation.

Keywords:

cathode-compensator, stationary plasma thruster, spacecraft, discharge current, power

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