Modeling, analysis and verification of a partial shunt system

Spacecraft power system modeling, analysis and verification techniques using the electronic circuit simulation programs such as SPICE and SABER are presented. Partial shunt control system dynamics including the loop gain and bus impedance are derived. A typical partial shunt system is modeled and the loop gain of the system is simulated using an electronic circuit simulator. To confirm the circuit model simulation results prior to expensive hardware testing, they should be compared with the results simulated from a transfer function model derived from circuit equations. The spacecraft test results finally verify the modeling and analysis