Abstract: A solar generator for spacecraft or satellites, including a solar panel, a detector layer, a first evaluation means and a second evaluation means. The solar panel includes a plurality of solar cells. The detector layer includes first conductors substantially in parallel in a first plane and second conductors substantially in parallel in a second plane. The second plane is substantially in parallel to the first plane such that the first conductors are at an angle to the second conductors. The first evaluation means is for detecting a failure of one or more of the plurality of solar cells. The second evaluation means is for testing electrical status of the first conductors and the second conductors to determine whether the failure detected by the first evaluation means was caused by a space object damaging or severing one or more of the first conductors and the second conductors.