Abstract: A space propulsion system includes an electrostatic thruster with a first electrical load; a resistojet; a propellant fluid feed circuit; and an electrical power supply circuit including a first power supply line and a first switch for selecting between connecting the first power supply line to the resistojet and connecting the first power supply line to the first electrical load of the electrostatic thruster. The propulsion system thus enables a space propulsion method to be applied that includes a switching step for selecting a first propulsion mode in which the resistojet is activated, or a second propulsion mode in which the electrostatic thruster is activated.

Abstract: A Hall effect thruster includes at least one tank of gas under high pressure, a pressure regulator module, a gas flow rate control device, an ionization channel, a cathode placed in a vicinity of an outlet from the ionization channel, an anode associated with the ionization channel, an electrical power supply unit, an electric filter, coils for creating a magnetic field around the ionization channel, and an additional electrical power supply unit for applying a pulsating voltage between the anode and the cathode.

Abstract: An electric thruster includes at least one electric engine, a feed system for the engine including a high-pressure tank of ionizable gas, a low-pressure buffer tank connected to the high-pressure tank by a valve, and a system of pipes for conveying the gas from the low-pressure buffer tank to an anode and to a cathode of the engine. The low-pressure buffer tank is in open connection with the engine. The thruster detects that a magnitude of the discharge current between the anode and the cathode is less than a threshold value and switches off the discharge voltage as a result of the detection. The thruster can be for use in a satellite.

Abstract: A Hall effect thruster includes at least one tank of gas under high pressure, a pressure regulator module, a gas flow rate control device, an ionization channel, a cathode placed in a vicinity of an outlet from the ionization channel, an anode associated with the ionization channel, an electrical power supply unit, an electric filter, coils for creating a magnetic field around the ionization channel, and an additional electrical power supply unit for applying a pulsating voltage between the anode and the cathode.

Abstract: An electric thruster includes at least one electric engine, a feed system for the engine including a high-pressure tank of ionizable gas, a low-pressure buffer tank connected to the high-pressure tank by a valve, and a system of pipes for conveying the gas from the low-pressure buffer tank to an anode and to a cathode of the engine. The low-pressure buffer tank is in open connection with the engine. The thruster detects that a magnitude of the discharge current between the anode and the cathode is less than a threshold value and switches off the discharge voltage as a result of the detection.