Power subsystem of GÖKTÜRK 2 flight model

The purpose of a power subsystem is to ensure reliable delivery of electrical power compatible with all loads under all foreseeable operational states and environments, during all mission phases, and over the intended design life of the loads and of the space vehicle and the power subsystem is unarguably the most critical subsystem on a satellite. Therefore, reliability, efficiency, autonomy, redundancy and size features become critical issues in design and implementation of a satellite power system. Moreover, these parameters associated with the power subsystem usually determine the lifetime of a satellite. This paper describes the design details with redundancy concept, autonomous operation, and sizing of GÖKTÜRK-2 power system flight model. The technical description of the subsystem and each module including the qualification level tests is also presented. For the battery charge regulators, the parallel operation, synchronization, electro-magnetic radiation reduction techniques, an effective MPPT algorithm will be presented in detail. Newly developed Electronic Separation Switch Module for the safe electrical separation from launch vehicle is also introduced here. Moreover, the power production-consumption analysis for different scenarios and early orbit data will also be presented roughly.