Abstract: A space propulsion module for fitting to spacecraft is provided. The space propulsion module includes a solid propellant chemical thruster including a main body, and at least one electric thruster. The at least one electric thruster is mounted on main body of the solid propellant chemical thruster.

Abstract: A combustion chamber including a diverging portion. The combustion chamber extends along a longitudinal axis and includes a fluid injection system from which there extends in a downstream direction a wall presenting a throat and a diverging portion situated downstream from the throat. The chamber further includes a tubular element surrounding the wall at least in part and configured to take up most of forces generated during operation of the chamber on the downstream end of the wall to transfer the forces to a structure situated upstream from the chamber.

Abstract: The invention relates to the field of propulsion nozzles, and in particular to a device (105) for connecting together first and second segments (103a, 103b) of a propulsion nozzle that are made of thermally dissimilar materials. The device (105) comprises at least one pin (106) and an eccentric bushing (107). The pin (106) presents both a first axisymmetric surface (106a) that is to be housed in a radial orifice (108) of the first nozzle segment (103a) and also a second axisymmetric surface (106b) that is eccentric relative to said first axisymmetric surface (106a).

Abstract: A space propulsion module in particular for fitting to spacecraft such as satellites, probes, or indeed the upper stages of rockets. According to the invention, the space propulsion module comprises a solid propellant chemical thruster (10) having a main body (11), and at least one electric thruster (30), said at least one electric thruster (30) being mounted on said main body (11) of the solid propellant chemical thruster (10).

Abstract: The invention relates to the field of injectors, and in particular to an injector element (201) having at least one first helical channel (204) and at least one second helical channel (205), each of said helical channels (204, 205) following a respective helix (204a, 205a) centered on a central axis (X) of the injector element (201). The helix (205a) of the at least one second helical channel (205) is situated inside the helix (204a) of the at least one first helical channel (204).

Abstract: A heat exchanger for operating at an outlet of a hot fuel cell feeding the heat exchanger with oxidizer gas and with fuel gas, the heat exchanger including: a first flow circuit for oxidizer gas; a second flow circuit for fuel gas; a pre-mixer chamber fed both with oxidizer gas and with fuel gas from at least the second circuit; a combustion chamber fed with the gaseous mixture from the pre-mixer chamber and with oxidizer gas from the first circuit; and a flow circuit for flue gas, receiving the flue gas coming from the combustion chamber. The first flow circuit for oxidizer gas, the second flow circuit for fuel gas, the combustion chamber, and the flow circuit for flue gas are immersed in a common cooling fluid.

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.

Abstract: A combustion chamber including a diverging portion. The combustion chamber extends along a longitudinal axis and includes a fluid injection system from which there extends in a downstream direction a wall presenting a throat and a diverging portion situated downstream from the throat. The chamber further includes a tubular element surrounding the wall at least in part and configured to take up most of forces generated during operation of the chamber on the downstream end of the wall to transfer the forces to a structure situated upstream from the chamber.

Abstract: A heat exchanger for operating at an outlet of a hot fuel cell feeding the heat exchanger with oxidizer gas and with fuel gas, the heat exchanger including: a first flow circuit for oxidizer gas; a second flow circuit for fuel gas; a pre-mixer chamber fed both with oxidizer gas and with fuel gas from at least the second circuit; a combustion chamber fed with the gaseous mixture from the pre-mixer chamber and with oxidizer gas from the first circuit; and a flow circuit for flue gas, receiving the flue gas coming from the combustion chamber. The first flow circuit for oxidizer gas, the second flow circuit for fuel gas, the combustion chamber, and the flow circuit for flue gas are immersed in a common cooling fluid.

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 a heat exchanger for a hot fuel cell. The heat exchanger includes a first flow circuit for receiving a cool air stream and a second flow circuit for receiving a hot fluid coming from the cell, the first and second flow circuits having common surfaces for heat exchange. In accordance with the present invention, each of the first and second flow circuits comprises a plurality of concentric annular ducts that are interconnected. The two walls of each duct are mechanically decoupled from each other, thereby enabling them to expand independently of one another and avoiding mechanical stresses within the heat exchanger.

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: The invention relates to a heat exchanger for a hot fuel cell. The heat exchanger includes a first flow circuit for receiving a cool air stream and a second flow circuit for receiving a hot fluid coming from the cell, the first and second flow circuits having common surfaces for heat exchange. In accordance with the present invention, each of the first and second flow circuits comprises a plurality of concentric annular ducts that are interconnected. The two walls of each duct are mechanically decoupled from each other, thereby enabling them to expand independently of one another and avoiding mechanical stresses within the heat exchanger.

Abstract: The sliding joint assembly for a first part and a second part having different expansion coefficients comprises a plurality of radially-acting spring blades connected firstly at first ends to the first part only in the vicinity of a contact interface, and secondly via second ends to the second part only in a zone that is axially remote from the contact interface, the contact interface constituting a sliding contact interface between the first and second parts while the second ends of the spring blades are connected to the second part by mechanical fasteners constituted by detachable screw-and-nut type assemblies provided with spring washers for damping forces exerted in the axial direction.