To provide a propulsion device for a spacecraft controlling a temperature of pipes to a predetermined value by the less number of temperature sensors.

A fuel tank 1 and a plurality of thrusters 8 for burning the fuel are connected by fuel pipes 2 through a valve 7 every at the thrusters 8. A plurality of heaters 4 are auxiliarily provided on the fuel pipes 2. A heater control system having a power source 6, a heater control circuit 5 and a temperature sensor 3 and controlling an energization to the heater 4 is provided and dummy pipes 9 having approximately the same thermal characteristic as the fuel pipes 2 and letting no fuel run at the inside is provided. The temperature sensor is auxiliarily provided on the dummy pipes 9, and the heater control circuit 5 commonly and collectively controls a power from the power source 6 fed to the respective heaters 4 by a temperature measurement signal of this temperature sensor 3.