Radiator deployable for a satellite stabilized on three axes

A method for controlling a deployable photovoltaic generator of a three-axis stabilized satellite, the photovoltaic generator comprises an array of panels that are hinged to each other, and a supporting yoke to attach the photovoltaic generator to a structure of a body of the satellite, the panels are folded on top of one another in a first or launch position of the photovoltaic generator, the panels are completely deployed in a second or deployed position of the photovoltaic generator;

• wherein at least some of the panels are solar panels having a photovoltaic-collector side orientable towards solar radiation;
• wherein at least one panel consists of a thermal radiator to provide a radiator panel;
• wherein a radiative side of the thermal radiator is oriented oppositely to a side of the photovoltaic panels bearing photovoltaic collectors in the deployed position of the photovoltaic generator, the radiative side is referred to as a shady side, and an opposite side of the panel forming the thermal radiator is referred to as a sunny side;
• wherein the panel closest the supporting yoke is a panel forming the thermal radiator;
• and wherein each panel is mono-functional such that thermal-radiator and solar-generator functions are exclusive from each other in each panel of the photovoltaic generator;
• the satellite is equipped with a fluid-loop cooler, the satellite comprises a fluidic link between the radiator panel of the photovoltaic generator and the body of the satellite, and a coil of flexible piping comprising two tubes to transport a fluid between the body of the satellite and the radiator panel, one end of the coil of flexible piping is securely fastened to a circuit to remove heat from the body of the satellite, and other end of the coil of flexible piping is securely fastened to the radiator panel;
• the method comprises the steps of:
• stowing the array of panels of the photovoltaic generator in the launch position during launch, then deploying the panels in the deployed position once the satellite has acquired an orbital station, the radiator panel is arranged close to the body of the satellite;
• gradually deploying the flexible piping while maintaining the transport of fluids between the body of the satellite and the photovoltaic generator during a rotation of the photovoltaic generator about an axis relative to the body of the satellite;
• and
• at regular intervals, rotating the photovoltaic generator in a direction opposite to a solar-tracking direction, to return the coil of flexible piping to a neutral position, or to a position of maximum deployment in other direction.