Abstract
This paper describes the implementation of a reliable maximum power point tracking design as an analog circuit for use on a satellite relying on solar power generation within low Earth orbit. The environment in which such a spacecraft system would function is evaluated. A specific maximum power point tracking algorithm is selected with regards to environmental constraints. A further increase in reliability was achieved by only using carefully selected analog components that are suitable for use within a space environment. The system was prototyped, and its power conversion performance was characterized using a custom-built measurement setup. The system successfully tracked the maximum power point through all the performed measurements. The results from the measurements suggest that the prototyped system has a nominal regulator efficiency of 88% and a nominal tracking accuracy of 96%.
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