The invention refers to an electrically powered propulsion system for use in a spacecraft (1) that comprises a first center of gravity (3) at a first time of operation and a second center of gravity (4) at a second time of operation, wherein the second center of gravity (4) is different from the first center of gravity (3). The electrically powered propulsion system for use in a spacecraft (1) comprises a thruster realignment mechanism (30) and at least two thrusters (10, 20) coupled to the thruster realignment mechanism (30), each of the at least two thrusters (10, 20) having an individual thrust vector (11, 21). The thruster realignment mechanism (30) is adapted such that, in a first position, the individual thrust vectors (11, 21) of the at least two thrusters (10, 20) pass through the first center of gravity (3) and such that, in a second position, the individual thrust vectors (11, 21) of the at least two thrusters (10, 20) pass through the second center of gravity (4). The thruster realignment mechanism (30) holds the first position in case all of the at least two thrusters (10, 20) are without any failure. The thruster realignment mechanism (30) realigns the thrusters (10, 20) to the second position in case that one of the at least two thrusters (10, 20) has a failure and/or a predetermined time criterion is fulfilled.