Abstract: A spacecraft for the distribution of electrical energy to client craft at points situated in free space, in orbit and/or on a celestial body includes a main structure equipped with an electric thruster, with a chemical thruster and with a solar generator, a first fuel container for fuel intended for the electric thruster, and a second fuel container for fuel intended for the chemical thruster. The spacecraft is able to be modulated such that the main structure can be coupled/decoupled alternatively to/from the first container or the second container, the first container and the second container are able to be coupled/decoupled to/from one another, and the solar generator can be deployed or retracted.

Abstract: A method of deploying a constellation of satellites includes using a single launch vehicle to deploy a plurality of satellites at an initial altitude on a same initial orbit, controlling said satellites such that an altitude of some of the satellites is modified while their inclination relative to an equatorial plane and a type of trajectory, of the some of the satellites, remains identical so that each satellite reaches a drift altitude selected from a drift set, with orbits of various satellites shifting relative to one another, and controlling the satellites to be moved sequentially in order to reach a same final altitude, said sequential movement being performed in such a manner that the satellites describe final orbits having trajectories with a same angle of inclination relative to the equatorial plane, a same apogee and perigee, and the same final altitude but presenting distinct longitudes for ascending nodes.

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 method of deploying a constellation of satellites, the method comprising the following steps: using a single launcher to deploy (10) a plurality of satellites at an initial altitude on an initial orbit; controlling said satellites (20) in such a manner that each satellite reaches a drift altitude selected from a drift set, with the orbits of the various satellites shifting (30) relative to one another at the respective drift altitudes under the effect of the gravitational potential of the Earth; and controlling (40) the satellites in such a manner as to be moved sequentially in order to reach the same final altitude, said sequential movement being performed in such a manner that the satellites describe final orbits that are angularly offset relative to one another.

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: A Hall effect thruster including: a discharge channel with an open downstream end; a cathode situated outside the discharge channel; an injector system configured to inject atoms of gas into the discharge channel, the injector system situated at an upstream end of the discharge channel and also forming a cathode; a heater device configured to heat the cathode; a measurement mechanism measuring temperature of the heater device, and a regulator circuit regulating the temperature such that the heater device heats so long as its temperature is less than a threshold temperature from which the thruster is capable of starting, and ceases to heat shortly after the threshold temperature has been reached.

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: The invention relates to the field of Hall effect thrusters. The invention provides a Hall effect thruster having a discharge channel of annular shape extending along an axis, the discharge channel being defined by an outer wall of annular shape and an inner wall of annular shape situated inside the space defined by the outer wall, a cathode situated outside the discharge channel, and an injector system situated at the upstream end of the discharge channel and also forming an anode, the downstream end of the discharge channel being open, wherein the thruster includes a heat sink device comprising a heat sink in contact with the inner wall and of thermal conductivity that is greater than the thermal conductivity of the inner wall, the heat sink being a sleeve and the heat sink device being suitable for discharging heat from the inner wall to the outside of the thruster so as to reduce the temperature difference between the inner wall and the outer wall.

Abstract: A Hall effect plasma thruster including an annular discharge channel around a main axis presenting an open downstream end and defined between an inner wall and an outer wall, at least one cathode, a magnetic circuit for creating a magnetic field in the channel, a pipe for feeding ionizable gas to the channel, an anode, and a manifold placed in the upstream end of the channel. The manifold is connected to the pipe and enables the ionizable gas to flow into the ionization zone of the channel in concentric manner around the main axis. The anode acts as a manifold, and the manifold includes a directional mechanism that gives rise at an outlet from the manifold to swirling motion of the gas around the main axis.

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.

Abstract: A Hall effect thruster including: a discharge channel with an open downstream end; a cathode situated outside the discharge channel; an injector system configured to inject atoms of gas into the discharge channel, the injector system situated at an upstream end of the discharge channel and also forming a cathode; a heater device configured to heat the cathode; a measurement mechanism measuring temperature of the heater device, and a regulator circuit regulating the temperature such that the heater device heats so long as its temperature is less than a threshold temperature from which the thruster is capable of starting, and ceases to heat shortly after the threshold temperature has been reached.

Abstract: A Hall effect plasma thruster including an annular discharge channel around a main axis presenting an open downstream end and defined between an inner wall and an outer wall, at least one cathode, a magnetic circuit for creating a magnetic field in the channel, a pipe for feeding ionizable gas to the channel, an anode, and a manifold placed in the upstream end of the channel. The manifold is connected to the pipe and enables the ionizable gas to flow into the ionization zone of the channel in concentric manner around the main axis. The anode acts as a manifold, and the manifold includes a directional mechanism that gives rise at an outlet from the manifold to swirling motion of the gas around the main axis.

Abstract: The invention relates to the field of Hall effect thrusters. The invention provides a Hall effect thruster having a discharge channel of annular shape extending along an axis, the discharge channel being defined by an outer wall of annular shape and an inner wall of annular shape situated inside the space defined by the outer wall, a cathode situated outside the discharge channel, and an injector system situated at the upstream end of the discharge channel and also forming an anode, the downstream end of the discharge channel being open, wherein the thruster includes a heat sink device comprising a heat sink in contact with the inner wall and of thermal conductivity that is greater than the thermal conductivity of the inner wall, the heat sink being a sleeve and the heat sink device being suitable for discharging heat from the inner wall to the outside of the thruster so as to reduce the temperature difference between the inner wall and the outer wall.