Abstract: A system for regulating the flow rate of a propellant fluid for an electrical thruster of a space vehicle, the vehicle including a tank of propellant fluid and a flow rate regulator connected to the outlet of said tank; the flow rate regulator including a heater element controlled by a computer and adapted to heat the propellant fluid and to modify its physical properties so as to vary the flow rate of propellant fluid leaving the tank; said system being characterized in that the computer also includes a plurality of empirical calibration curves that have been determined empirically for defining the flow rate of propellant fluid as a function of the magnitude of heating and as a function of environmental parameters, such that said computer also performs a function of determining the flow rate of the propellant fluid.

Abstract: A system for regulating the flow rate of a propellant fluid for an electrical thruster of a space vehicle, the vehicle including a tank of propellant fluid and a flow rate regulator connected to the outlet of said tank; the flow rate regulator including a heater element controlled by a computer and adapted to heat the propellant fluid and to modify its physical properties so as to vary the flow rate of propellant fluid leaving the tank; said system being characterized in that the computer also includes a plurality of empirical calibration curves that have been determined empirically for defining the flow rate of propellant fluid as a function of the magnitude of heating and as a function of environmental parameters, such that said computer also performs a function of determining the flow rate of the propellant fluid.

Abstract: A turbomachine such as an aircraft turbojet including an electrical generator/starter that can be mounted and dismounted by axial translation in an upstream enclosure of the turbomachine between the low-pressure compressor and the high-pressure compressor, and couple to electrical cables which extend inside the structural arms of the intermediate casing of the turbomachine.

Abstract: An electric connector assembly includes a plug having primary contacts and a base having secondary contacts capable of interacting with the primary contacts. The connector assembly also includes a closure flap fixed to the base and capable of pivoting between a closed position in which it closes off an axis to the secondary contacts and an open position in which it frees an access to the secondary contacts to make it possible to connect the plug to the base, and an annular sleeve fixed to an electric cable connected to the plug and capable of being moved between two extreme positions, a bottom position in which it covers the closure flap when the plug and the base are connected and a top position in which it frees an access to the plug.

Abstract: A shielded and sealed electric harness having conductors housed in a tubular structure providing protection and shielding, the structure being constituted by a tubular inner textile braid, an intermediate metal tubular braid for electromagnetic shielding, and a corrugated outer sheath having its end adhesively bonded to a heat-shrink endpiece for fastening onto a portion of a connector of a branch joint.

Abstract: A turbomachine such as an aircraft turbojet including an electrical generator/starter that can be mounted and dismounted by axial translation in an upstream enclosure of the turbomachine between the low-pressure compressor and the high-pressure compressor, and couple to electrical cables which extend inside the structural arms of the intermediate casing of the turbomachine.

Abstract: Turbomachine such as an aircraft turbojet comprising an electrical generator/starter (26) that can be mounted and dismounted by axial translation in an upstream enclosure (18) of the turbomachine between the low-pressure compressor and the high-pressure compressor, and couple to electrical cables (34) which extend inside the structural arms (12) of the intermediate casing (10) of the turbomachine.

Abstract: The invention relates to an electric connector assembly comprising a plug (10) having primary contacts (20) and a base (12) having secondary contacts (24) capable of interacting with the primary contacts. The connector assembly also comprises a closure flap (30) fixed to the base and capable of pivoting between a closed position in which it closes off an axis to the secondary contacts (24) and an open position in which it frees an access to the secondary contacts to make it possible to connect the plug to the base, and an annular sleeve (40) fixed to an electric cable (14) connected to the plug (10) and capable of being moved between two extreme positions, a bottom position in which it covers the closure flap (30) when the plug and the base are connected and a top position in which it frees an access to the plug.

Abstract: A shielded and sealed electric harness comprises conductors housed in a tubular structure providing protection and shielding, the structure being constituted by a tubular inner textile braid, an intermediate metal tubular braid for electromagnetic shielding, and a corrugated outer sheath having its end adhesively bonded to a heat-shrink endpiece for fastening onto a portion of a connector of a branch joint.

Abstract: Turbomachine such as an aircraft turbojet comprising an electrical generator/starter (26) that can be mounted and dismounted by axial translation in an upstream enclosure (18) of the turbomachine between the low-pressure compressor and the high-pressure compressor, and couple to electrical cables (34) which extend inside the structural arms (12) of the intermediate casing (10) of the turbomachine.