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The Power return point of PCE is connected to a common point called SGRP. All the return points on the primary side of the power converter will be floating on the converter side. The ground pin of the EMI filter of the converter is connected to the respective package chassis. The load returns are connected to the corresponding supply returns. The RF signals use ground return through Chassis.

The critical paths are analyzed and some redundant component/ units are added to improve the reliability.
The battery is charged during AIT operation of the spacecraft and at launch pad using ground (constant voltage) charger operated in CV/CC mode-Taper charge mode.

For all ground testing, a Battery simulator (BS) is used instead of the battery even when the battery is present. Hence an auxiliary bus is formed as a common bus for either battery or BS, to test the UTP/LTP and ETP logic.

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