Propulsion system with stationary plasma thrusters aboard small spacecraft

Аuthors

Tkachuk A. V.^1*, Kozubski K. N.^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: antonchik_2004@mail.ru
**e-mail: fakel@gazinter.net
***e-mail: albert37@list.ru

Abstract

This article is devoted to the decryption of the Correction Propulsion System (CPS) named «ЭОЛ- 2010» developed on the base of the low power stationary plasma thrusters (SPT). This device is dedicated to power the low mass spacecraft keeping its working orbit parameters during active lifetime and de-orbiting after expiration. The CPS relevance is dedicated by increasing of the micro-satellites application in the various fields of science.
This CPS is designed as a monoblock structure, which adapted to install on the unified spacecraft chassis. CPS includes the propellant storage unit, propellant flow control unit, and the thruster unit. The design with both single and two thrusters modifications are described. The working mode of the thrusters was choosing with adjustable power level in the range from 150 to 210 Watts, taking into account solar cell illumination change or its degradation. The propellant storage unit tank contains 4.1 kg of xenon at a pressure of 10 MPa. The total system thrust impulse is 44 kN under full propellant utilization. The CPS dry mass is 8 kg.
The calculations presented in the article demonstrate the application possibility of micro-thrusters correcting propulsion system usage for orbital transfer and adjustments in low orbits (up to 600 km) the spacecraft mass up to 100 kg, taking into account its aerodynamic drag. It is shown that spacecraft lifetime increases 5 to 10 times with such CPS using.
The results of firing test of the thrusters aboard the CPS module with the flow rate characteristics controlled by the weight method are described. The possibility of using the CPS module as test stand equipment for testing of SPT modifications and elements of a Propellant Storage and Power Supply System is shown herein.

Keywords:

stationary plasma thruster, correction propulsion system, micro-spacecraft, active lifetime, test stand equipment.

References

Kvasnikov L.A., Latyshev L.A., Ponomarev-Stepnoi N.N., Sevruk D.D., Tikhonov V.B. Teoriya i raschet energosilovykh ustanovok kosmicheskikh letatelnykh apparatov (Theory and design of the electric-power and -propulsion systems of flying vehicles), Moscow, MAI, 2001, p. 480.