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The test facility for electric microthrusters at the European Space Research and Technology Centre is described. The microbalance which is used to directly measure thrust and propellant mass flow rate is able to resolve thrusts of 10−7 N. Within a working range of 5×10−5−5×10−4 N it is estimated that thrust measurements may be made to an accuracy of ±2%.
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Bailey et al. (1972) studied this question.
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