Analysis of Future Generic InnoSat Power Architecture

Sammanfattning

Compact satellites and lower launch costs have worked to expand the commercial satellite development market. To lower costs and increase competitiveness satellite manufactures are working to streamline their processes and designs. One way to achieve this is standardizing designs and leveraging the economics of scale. In this spirit a desire exists to standardize the power system of the Innosat small satellite platform developedand manufactured by OHB Sweden AB. This thesis creates a highly modular and parametric model of the electrical power system on a small satellite, specifically Innosat. With this model simulations for a wide range of configurations and mission profiles were carried out to determine if a generic one-size-fits-all configuration could be used, and what such a configuration should look like. Simulations are performed with both flight data from a selection of in-orbit satellites and with synthetic data. Real hardware values have been used whenever possible. Furthermore Maximum PowerPoint Tracking and Direct Energy Transfer/Sequential Switching Shunting Regulation was compared for the use in the Innosat platform. Simulations were conductedin Matlab and Simulink. In the end it is suggested that an eight-series, six parallel battery configuration be used with two solar array wings, and a maximum power point tracker as the charge and power regulator.