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In general, solar array is used for primary power source of satellite. For solar array design, required power and voltage are considered to perform the mission successfully. Also, solar cell degradation and string failure at EOL (End of Life) are considered for its design. In this paper, solar array design that is reflected design consideration for Korea LEO (low earth orbit) satellite is introduced. For verification of design results, we perform the related analysis and test for key requirements. The test results show that design is suitable for usage of space application.