A software power model for a spin-stabilized LEO spacecraft utilizing V/T charge control

Abstract

A software power model has been developed which characterizes the performance of the electrical power subsystem of a spin-stabilized LEO spacecraft which uses an eight-level V/T controller to perform the charge control function. The model accurately simulates the operational performance of the solar array and power control unit, the charge/discharge characteristics of the batteries, and the time-varying nature of various electrical loads. The end result is a prediction of battery state-of-charge as a function of time for a specified period of operations. This allows mission planners to perform operational trades relating to payload usage, and enables more efficient payload tasking without endangering vehicle health.