Turkish First Indigenous 100V Satellite Power Subsystem

The electrical power subsystem (EPS) is unarguably one of the most critical subsystems on a spacecraft. The purpose of an EPS is to ensure reliable delivery of electrical power compatible with all loads during all mission phases. In this paper, an EPS with fully regulated power bus for a GEO satellite is presented. Presented EPS includes 2 deployable and rotatable solar array wings (SAW). Each SAW is rotating by dedicated Solar Array Drive Mechanism which is controlled by a Solar Array Drive Electronics. For energy storage, two serial Li-Ion Battery Blocks are used. To regulate power from solar array and battery, a Power Conditioning Unit (PCU) is used. PCU regulates up to 7.5kW output power during eclipse and 10.5kW during sunlight. Power Distribution Unit transfers the regulated power to satellite loads through current protected power lines. Moreover, pyro drive electronics which is responsible for actuating electro-initiated devices is part of the EPS and presented in this paper.