Method of controlling the latitude argument of a satellite

摘要

The invention relates to a method (100) for controlling the orbit of a satellite comprising a body having two opposite faces substantially parallel to each other each comprising at least one heater. According to the invention, the method comprises: - a step (110) of determining an evolution of a free drift of a latitude argument of the satellite; - a step (120) of controlling the drift of the argument latitude of the satellite during which a thermal setpoint law is applied to at least one of the heaters, as a function of the solar elevation, to create a target thermal power gap between the two opposite faces, which thermal power gap is at the origin of a force having a tangential component to an orbit of the satellite intended to counterbalance the free drift of the latitude argument of the satellite and allow the latitude argument to remain within a predetermined angular window. The invention also relates to a computer program product and a satellite. Figure for the abstract: figure 7