The development of satellite propulsion systems naturally requires the accurate measurement of the thrust level. Whereas such a task is relatively easy for chemical thrusters where forces in the order of kN are produced, complexity raises with electrical thrusters that show very low thrust-to-mass ratios. Currently the thrust of electric devices is in the µN to hundreds mN range, which makes measurements difficult and complicated. Moreover, thrust measurements must be carried out inside a vacuum chamber in order to comply with the effective environment in which satellites, then thrusters, operate. This Master thesis presents the development of a pendulum-type Thrust Balance able to measure the low thrust produced by miniature electric thrusters.