Electrical thruster functional test at system level on flight model of a spacecraft

In the framework of the system environmental tests on ESA's spacecraft SMART-1, there are plans to run the Electric Propulsion System for a short-duration end-to-end test in the Large Space Simulator (LSS) after the Thermal Vacuum and Thermal Balance tests. The test would involve the spacecraft and the payload Flight Models and should take place in spring 2002. The problems to be tackled are essentially related to the xenon ion-beam sputtering effects and related potential contamination of both chamber and spacecraft. Different methods of protection against the associated contamination risks have to be evaluated. The points to be addressed among others are: identification of contamination risks for the chamber and the spacecraft; adequacy of the pumping system; and identification of safety hazards. The paper presents the results of the feasibility investigation conducted at ESTEC in view of the SMART-1, Bepi-Colombo and Solar orbiter future test campaigns.