The invention relates to a space cold gas thruster operating with a solid propellant. The cold gas thruster of the invention comprises a tank (1) suitable for containing a solid propellant and a tank (1) heating device suitable for sublimating said solid propellant and forming gaseous propellant, the tank (1) having an aperture (7) for transferring said gaseous propellant outside said tank (1), such as a nozzle (7). The invention also relates to a process for determining the amount of remaining propellant in the propellant tank (1) of a cold gas thruster of the invention.
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