Abstract: A satellite comprises at least one first communication module, a repeater module, one or more antennas, at least one propulsion module and an avionics module, the repeater module comprising: a north first panel when the satellite is in an orbital position, an east second panel, a south third panel and a west fourth panel arranged respectively opposite the north first panel and the east second panel, the north panel and the south panel having widths XmcR in the east-west direction, the east panel and the west panel having a width or YmcR in the north-south direction; characterized in that: the value of the ratio XmcR/YmcR for the repeater module lies within the interval [0.84; 1.12], and the repeater module consists of a number of floors, and the value of Xmck varies as a function of the floor k and of its position in the repeater module.

Abstract: A satellite comprises at least one first communication module, a repeater module, one or more antennas, at least one propulsion module and an avionics module, the repeater module comprising: a north first panel when the satellite is in an orbital position, an east second panel, a south third panel and a west fourth panel arranged respectively opposite the north first panel and the east second panel, the north panel and the south panel having widths XmcR in the east-west direction, the east panel and the west panel having a width or YmcR in the north-south direction; characterized in that: the value of the ratio XmcR/YmcR for the repeater module lies within the interval [0.84; 1.12], and the repeater module consists of a number of floors, and the value of Xmck varies as a function of the floor k and of its position in the repeater module.

Abstract: The invention relates to a thermal control device intended to dissipate the heat generated by a payload on a spacecraft, comprising a number of surfaces and including means for circulating a refrigerant. An evaporation zone (Z1) comprises means for circulating the refrigerant, a compression zone (Z2), a condensation zone (Z3) comprising at least one radiating panel, linked to a part of the means for circulating the refrigerant, including several branches and comprising means to allow or inhibit the circulation of the refrigerant within these branches so as to vary the area of the heat exchange surface in the condensation zone, a pressure reduction zone (Z4) comprising means for circulating the refrigerant. Such a device is particularly well adapted to thermal problems encountered in telecommunications satellites.

Abstract: The invention relates to a craft comprising an energy storage system of the RFCS (regenerative fuel cell system) type and a system for pressurizing the propellants used for propulsion. The craft also comprises a plurality of means (31 to 38) for coupling the tanks of the fuel cell to the propellant-pressurizing tanks of the propulsion system of the craft when the tanks of the propellant-pressurizing system are no longer used. The invention also relates to the method of coupling the tanks of the propellant-pressurizing means to the energy storage system. The invention applies particularly to telecommunication satellites and more generally to spacecraft.

Abstract: The invention relates to a thermal management device intended to collect the heat dissipated by a group of dissipative equipment of a spacecraft in an evaporation zone before discharging this heat to cold space via a condensation zone, situated in the region of the radiators. The evaporation zone and the condensation zone each consist of at least one heat-exchange part comprising a network of a plurality of compact heat-exchange elements distributed over their respective heat-exchange surface and connected in series and/or in parallel by the tubes of the thermal fluid circulation means. A device such as this is particularly intended for telecommunications satellites.

Abstract: The invention relates to a craft comprising an energy storage system of the RFCS (regenerative fuel cell system) type and a system for pressurizing the propellants used for propulsion. The craft also comprises a plurality of means (31 to 38) for coupling the tanks of the fuel cell to the propellant-pressurizing tanks of the propulsion system of the craft when the tanks of the propellant-pressurizing system are no longer used. The invention also relates to the method of coupling the tanks of the propellant-pressurizing means to the energy storage system. The invention applies particularly to telecommunication satellites and more generally to spacecraft.

Abstract: The invention relates to a thermal control device intended to dissipate the heat generated by a payload on a spacecraft, comprising a number of surfaces and including means for circulating a refrigerant. An evaporation zone (Z1) comprises means for circulating the refrigerant, a compression zone (Z2), a condensation zone (Z3) comprising at lEast one radiating panel, linked to a part of the means for circulating the refrigerant, including several branches and comprising means to allow or inhibit the circulation of the refrigerant within these branches so as to vary the area of the heat exchange surface in the condensation zone, a pressure reduction zone (Z4) comprising means for circulating the refrigerant. Such a device is particularly well adapted to thermal problems encountered in telecommunications satellites.