The solar panel for space satellites has a plane surface including a plurality
of photovoltaic cells (CE) disposed side-by-side and substantially forming a grid,
the cells (CE) being electrically connected into at least one serpentine (SE1),
each serpentine made up of cells (CE) connected in series two-by-two forming parallel
cell segments (SG), two successive segments (SG) of a serpentine being electrically
connected at their ends, and each serpentine having positive terminals (+) and
negative terminals (-), the positive (+) and negative (-) terminals being distributed
along each serpentine (SE1) and over the surface of the panel so that the
positive terminals are far away from the negative terminals, to reduce the risk
of electrical arcing between two terminals. With this arrangement, the risk of
electrical arcing is reduced without increasing the fabrication cost of the panel.
