Abstract: The attitude of a satellite carrying terrestrial and solar sensors and spin-stabilized about an axis V--V is determined and controlled prior to its transfer from an elliptical transfer orbit to a circular geostationary orbit by means of an apogee motor firing. The attitude is defined relative to an inertial X-Y-Z frame of reference the Z axis of which is directed towards geographical North, by a declination .alpha. between the axis V--V and the X-Y plane and by a right ascension .beta. between the projection of the axis V--V onto the X-Y plane and the X axis. After injection of the satellite by a launch vehicle into the transfer orbit at its perigee, with an initial attitude approximating the predetermined final attitude for the apogee motor firing, the right ascension .beta. of the satellite is modified to confer on it an intermediate attitude such that the earth is in the field of view of the terrestrial sensors for a position of the satellite in the transfer orbit offset at least 10.degree.