Methodology of development and test of the electrical rocket propulsion system for telecommunication spacecraft Yamal-200 (to the 15th anniversary of operation in space)

Abstract

The article summarizes the results of a 15-year operation of the Yamal-202 telecommunication spacecraft in geostationary orbit. The review of using electrical rocket engines in spacecraft in domestic and foreign projects is made. The questions of methodology for developing and testing the electrical rocket propulsion system for the Yamal-200 spacecraft are considered including features of the RSC Energia stand base, specific features of the equipment and methodology for filling tanks with working fluid such as xenon. Special attention is paid to the preliminary joint test of the power supply and control equipment with thruster modules in order to justify the long-term operation of electrical rocket engines. In the analysis of the 15-year operation of the electrical rocket propulsion system the initial operation phase of the spacecraft is shown with the cruise mode of electrical rocket thruster modules for installation at operating points 49 and 90 EL with the corresponding operating time of all thruster modules. The final data on the operating time of thruster modules KA-201 for 10.5 and KA-202 – for 15 years of operation is presented that gives significant statistics on the use of engines СПД-70. The estimate of the remaining mass of the working fluid and the capability of further operation of the electrical rocket propulsion system is made. Key words: geostationary orbit, electrical rocket engine, thruster module, united propulsion system, predelivery checkout tests, filling with working fluid.