| 摘要 |
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.
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