Abstract: A method for transferring a spacecraft (10), such as an artificial satellite, from an initial elliptical orbit (30) to a final geostationary orbit (50), the spacecraft taking at least one intermediate elliptical orbit (40) propelled by electric propulsion means (12, 13), the method includes: when the spacecraft is in an intermediate orbit, a nominal thrust step (410) in which the propulsion means generate nominal thrust while the spacecraft is on at least part of a first orbital arc (41) passing through the apogee A of the intermediate orbit, and a minimum thrust step (420), in which the propulsion means are partly stopped or slowed while the spacecraft is on at least part (43) of a second orbital arc (42) passing through the perigee P of the intermediate orbit, the two orbital arcs being complementary.

Abstract: An electrical power supply system for a satellite with continuously controlled DC-voltage is suitable for recharging batteries without requiring any specific charge module. To this purpose, at least one solar generator section, so-called charge section, is connected directly to a battery output terminal (B). Simultaneously, at least one battery discharge module is dedicated to the control of a residual current that is not used for recharging the batteries. A first regulator is added to the system in order to control said residual current on the basis of a current produced by the charge section and a charge target for the batteries. Optionally, a second regulator may also be added, in order to directly control the current produced by the charge section when equipment that is electrically powered has a low consumption.

Abstract: The invention relates to control of a battery, permitting a reduction in the number of components of the battery. The battery comprises several modules (2a, . . . , 2n), each module comprising a charge limiting circuit (4). When a module is detected as defective, the charge limiting circuit (4) carries out a command for the discharge of said defective module, by formation of a short-circuit path. The battery can subsequently be used without functional hindrance by the defective module.

Abstract: An electrical power supply system for a satellite with continuously controlled DC-voltage is suitable for recharging batteries without requiring any specific charge module. To this purpose, at least one solar generator section, so-called charge section, is connected directly to a battery output terminal (B). Simultaneously, at least one battery discharge module is dedicated to the control of a residual current that is not used for recharging the batteries. A first regulator is added to the system in order to control said residual current on the basis of a current produced by the charge section and a charge target for the batteries. Optionally, a second regulator may also be added, in order to directly control the current produced by the charge section when equipment that is electrically powered has a low consumption.

Abstract: The invention relates to control of a battery, permitting a reduction in the number of components of the battery. The battery comprises several modules (2a, . . . , 2n), each module comprising a charge limiting circuit (4). When a module is detected as defective, the charge limiting circuit (4) carries out a command for the discharge of said defective module, by formation of a short-circuit path. The battery can subsequently be used without functional hindrance by the defective module.