Tank for a spacecraft engine

A cryogenic propellant tank for a spacecraft engine, comprising an outer enclosure defining an inner volume,

• characterized in that the inner volume of the tank includes a primary volume and a secondary volume connected to the primary volume by a valve configured to selectively (i) allow passing of fluid from the primary volume towards the secondary volume, or (ii) isolate the secondary volume from the primary volume,
• the primary volume having a primary orifice configured to be connected to a first pressurization source,
• the secondary volume having a supply orifice configured to be connected to a supply line of a spacecraft engine, and a secondary orifice configured to be connected to a second pressurization source, and
• the cryogenic propellant tank further comprising an inner wall arranged inside the outer enclosure, said inner wall separating the inner volume of the outer enclosure so as to define the primary volume and the secondary volume.