Abstract
A couple of 5 cm mercury electronbombardment ion engine systems will be tested on board the engineering test satellite (ETS-III) of Japan, scheduled to be launched in 1982. To ascertain their reliability, the ion thrusters were to be subjected to a series of development tests in each phase of EM, PM and FM (engineering, prototype and flight models). Measurements on ion beam divergence and thrust were particularly planned because the measured quantities are important for ion thruster application to the satellite. Thermal-vacuum and electromagnetic compatibility tests are necessary for an on-board device. A special method must be considered and established for these tests because ion thruster is a peculiar device. In this paper, these tests conducted as research by using preliminary engineering model ion thrusters are described, with a brief summary of the data obtained.
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