The satellite solar generator structure comprises a plurality of solar panels
(PR, PS) each having a plane surface, the panels being disposed in superposition
in said structure (ST), the structure including at least one rod (TI) holding said
panels (PR, PS) pressed against one another, two successive panels being in contact
via bearing points (AL) disposed at the peripheries of the panels. In this structure,
spacers (CA) are distributed over the surfaces of the panels (PR, PS) and are disposed
between pairs of successive panels in order to improve contact between two successive
panels so that the structure presents better mechanical strength during the satellite
launch stage. With this arrangement, a fraction of the forces is taken up by the
spacers instead of being taken up by the panels, thus making it possible to optimize
the solar generator, for example by reducing the weight of the panels constituting it.
