अमूर्त

Fully Regulated 28V Bus Using Bidirectional Battery Charge/Discharge Regulator for Satellite Applications

Anusha. R, Usha.P

The main source of power in a Satellite is the Solar Array. Spacecraft which uses Photovoltaic cells is usually equipped with Rechargeable batteries that receive a charge from Main bus when Solar panels are in sunlit condition. During eclipse, the Shunt regulator remains off and Battery serves the Spacecraft load, which lowers the battery voltage. All these create a varying DC as the Spacecraft Bus Voltage. A Battery Charge and Discharge Control are required to maintain battery voltage within acceptable limits and extract maximum life out of the Battery. Typically, separate hardware circuits are used for the Battery Charge Regulator (BCR) and Battery Discharge Regulator (BDR). This paper discusses a Battery management scheme using a BCR/BDR Bidirectional converter.