An electrical power system for a spacecraft or other vehicle or structure
comprising a structural member containing an integrated solid-state power
source is disclosed. The power source includes a solar cell system and an
energy storage system that are combined into a single unit or package,
and in certain embodiments, are configured into the shape of a flexible
aerobot balloon or a rigid nanosat surface panel. The power components of
a preferred lightweight power unit, include thinly layered photovoltaic
cells, a rechargeable lithium solid polymer electrolyte battery, a
capacitor, electronics and thermal management capability.