Satellites are notably used as radar systems. To this end they include a radar antenna taking the form of a plane panel in the operating configuration. This plane panel generally has dimensions such that it cannot be placed in the operating configuration under the nose cone of the launch vehicle for placing the satellite in orbit. Consequently, a radar antenna is generally formed of a so-called deployable structure. Such a structure comprises a set of antenna panels articulated to each other in such manner as to be able to assume a stowed configuration for launch, in which the panels are stacked on each other, and an operating configuration after the satellite is placed in orbit, in which the antenna panels are deployed and form a plane panel. To be more precise, in the stowed configuration, the antenna panels are stacked on either side of the body of the satellite on two opposite faces. The panels are articulated to a central antenna panel fixed to a third face of the body. Satellites also necessitate a source of electrical energy, generally provided by solar generators including solar panels. Missions being increasingly “costly” in energy terms, they necessitate increasingly large solar panels. Increasing the size of the solar panels gives rise to problems, however, both for the stowed configuration and for the operating configuration of the radar antenna. In fact, the body of the satellite forms a parallelepiped-shaped overall volume the two faces of which on which the antenna panels are stacked in the stowed configuration have a greater width than the third face to which the central antenna panel is fixed. Consequently, the volume available for stowing solar panels on the face opposite the third face is relatively limited. In the operating configuration, the solar panels are deployed and moved away from the body of the satellite. Consequently, there is a risk of the antenna panels and the solar panels shading each other. The solar panels are liable to interfere with the operation of the radar antenna.