Abstract: Reduction of battery effectiveness due to memory effect and unequal cell voltages is minimized by a spacecraft power control system which reconditions the battery preferably just prior to eclipse seasons of a geo-stationary orbit by discharging each battery cell through a network of shunting resistors. Recharging is accomplished by a low power dissipation charging sequence. The load of the system, except for during the eclipse season, is receiving power continuously from the solar cells and during peak load requirements receives supplementary power from the battery cells. During the eclipse seasons, the system power is supplied solely by the battery cells.