Abstract
The P ower Tools Suite (PTS) is being used to calculate various Electric Power System (EPS) sizing studies and also to provide detailed transient analysis for various given orbital satellite missions. Greater accuracy is now being demanded in these EPS simulati ons to not only reduce the satellite weight, but to also accurately predict the battery, solar array, load, and radiator power responses immediately after liftoff, during ascent, during the mission phase, and at end -of -life. The PTS code provides detailed subsystem models to accurately calculate all of the EPS system parameters, and predict future EPS mission behavior. Improvements recently made to the tools suite include several user -defined solar array and battery models, additional solar array wings, a s well as constant power and constant current load subsystems. Iterative numerical techniques are used during each time -step of the calculation to insure accurate and stabilized EPS currents and voltages, even at and near the maximum power point of the so lar array. The presentation will include descriptions of the various EPS subsystem models, and comparisons of PTS model results to data and various proposed missions.
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