The present invention relates to a satellite on an equatorial orbit with improved solar means and which is more particularly used in satellite telecommunications.
The satellite according to the invention is of the "stabilized three axes" type. In such a satellite, the payload is placed on a main body rotating about an axis perpendicular to the plane of the orbit, i.e. in parallel to the North-South axis. The rotation speed is such that one of the faces of the satellite is constantly oriented towards the earth. The solar generator comprises two flat blades or fins covered with solar collectors.
A satellite of the present type and which is closest to that according to the invention is described in French Pat. No. 2 472 509 (corresponding to U.S. Pat. No. 4,374,579). It is illustrated in FIG. 1 and comprises:
a service module 21 equipped with a polar stellar sensor 25 positioned on the north face 211, a solar sensor 26 located on the solar face 212, whereby said sensors are arranged in such a way as to supply attitude control information along three axes for the stabilization of the satellite; PA1 solar panels 23 rigidly fixed to the service module in such a way that when they are opened out in orbital configuration, they extend in the orbital plane; PA1 a rotary interface device 24 fixed to the service module; PA1 a payload module 22 equipped with antennas and connected to the interface device, the latter being arranged in such a way as to permit the payload module 22 to be continuously pointed towards the earth.
Such a configuration has disadvantages with respect to the solar means used by it. Throughout the remainder of the description, "solar means" are understood to mean means having a function relating to the sun.