Abstract: Cryogenic propellant tank (1) for a spacecraft engine, comprising an external enclosure (10) defining an internal volume, characterized in that the internal volume of the tank comprises a primary volume (V1) and a secondary volume (V2) connected to the primary volume (V1) via a valve (20) configured to selectively allow a passage of fluid from the primary volume (V1) to the secondary volume (V2), or to isolate the secondary volume (V2) from the primary volume (V1), the primary volume (V1) having a primary orifice (11) adapted to be connected to a first pressurization source (41), the secondary volume (V2) having a supply orifice (4) adapted to be connected to a supply line of a spacecraft engine (30), and a secondary orifice (12) adapted to be connected to a second pressurization source (42).

Abstract: Cryogenic propellant tank (1) for a spacecraft engine, comprising an external enclosure (10) defining an internal volume, characterized in that the internal volume of the tank comprises a primary volume (V1) and a secondary volume (V2) connected to the primary volume (V1) via a valve (20) configured to selectively allow a passage of fluid from the primary volume (V1) to the secondary volume (V2), or to isolate the secondary volume (V2) from the primary volume (V1), the primary volume (V1) having a primary orifice (11) adapted to be connected to a first pressurization source (41), the secondary volume (V2) having a supply orifice (4) adapted to be connected to a supply line of a spacecraft engine (30), and a secondary orifice (12) adapted to be connected to a second pressurization source (42).

Abstract: The invention relates to a device and a method for feeding a propulsion chamber of a rocket engine with at least with a first propellant. The device comprises at least a first tank for containing the first propellant, a first feed circuit connected to the first tank, and a first electric pump within the first tank in order to pump the first propellant through the first feed circuit. In the method, the first propellant is pumped through the first feed circuit from the first tank by at least the first electric pump that is immersed in the first propellant within the first tank.

Abstract: The invention relates to a device and a method for feeding a propulsion chamber 5 of a rocket engine 1 with at least with a first propellant. The device comprises at least a first tank 2 for containing said first propellant, a first feed circuit 4 connected to the first tank 2, and a first electric pump 10 within said first tank 2 in order to pump said first propellant through the first feed circuit 4. In the method, the first propellant is pumped through the first feed circuit 4 from the first tank 2 by at least said first electric pump 10 that is immersed in the first propellant within the first tank 2.

Abstract: Pump (1) comprising a rotary shaft (30), a bearing housing (80) that is fixed relative to the rotary shaft, at least one rolling bearing (70) the inner ring (71) of which is connected to the said rotary shaft and the outer ring (76) of which is able to slide in this housing along the axis of rotation of the rotary shaft. The bearing housing (80) comprises a shoulder (81) situated on one side of this bearing and able rigidly to prevent translational movement of the outer ring (76) along the axis of rotation, and a deformable elastic device (100) fixed to the housing on the other side of the bearing (70) so that the bearing lies between the shoulder and the elastic device.

Abstract: The invention relates to a centrifugal pump.

Abstract: Pump (1) comprising a rotary shaft (30), a bearing housing (80) that is fixed relative to the rotary shaft, at least one rolling bearing (70) the inner ring (71) of which is connected to the said rotary shaft and the outer ring (76) of which is able to slide in this housing along the axis of rotation of the rotary shaft. The bearing housing (80) comprises a shoulder (81) situated on one side of this bearing and able rigidly to prevent translational movement of the outer ring (76) along the axis of rotation, and a deformable elastic device (100) fixed to the housing on the other side of the bearing (70) so that the bearing lies between the shoulder and the elastic device.

Abstract: A tubular structure comprising reinforcing fibers impregnated with a thermosetting polymer and a sheet of matrix material filled with an additive suitable for improving tribological and heat conductivity characteristics of the tubular structure. The reinforcing fibers alternate with the matrix material. The tubular structure is formed by winding the reinforcing fiber fabric and the matrix sheet material, wherein the fabric and the matrix sheet material have first and second ends and the first ends are located in the interior of the winding and the second ends are radially outwardly displaced from the first ends.

Abstract: A method of manufacturing a composite material in the form of an annular tube by winding on a mandrel both a reinforcing fiber fabric and a sheet of matrix material, comprising the following steps: 1) preheating the mandrel to a predetermined temperature; 2) fixing the reinforcing fiber fabric and the sheet of matrix material to the mandrel; 3) causing the mandrel to rotate at a nominal speed to wind the fabric and the sheet simultaneously, the fabric and the sheet being subjected to a nominal tension; 4) actuating heating means for heating the material and cooling means for cooling the mandrel; 5) when the tube reaches the desired diameter, stopping both the heating means and the rotation of the mandrel; 6) after a determined duration that is sufficient for bringing the temperature of the mandrel to the predetermined preheating temperature, stopping the cooling means; and 7) dismounting the mandrel.

Abstract: A method of manufacturing a composite material in the form of an annular tube by winding on a mandrel both a reinforcing fiber fabric and a sheet of matrix material, comprising the following steps: 1) preheating the mandrel to a predetermined temperature; 2) fixing the reinforcing fiber fabric and the sheet of matrix material to the mandrel; 3) causing the mandrel to rotate at a nominal speed to wind the fabric and the sheet simultaneously, the fabric and the sheet being subjected to a nominal tension; 4) actuating heating means for heating the material and cooling means for cooling the mandrel; 5) when the tube reaches the desired diameter, stopping both the heating means and the rotation of the mandrel; 6) after a determined duration that is sufficient for; bringing the temperature of the mandrel to the predetermined preheating temperature, stopping the cooling means; and 7) dismounting the mandrel.