Stability analysis of aircraft electrical power system with active front rectifier system in generation channel

The presence of constant power loads in novel aircraft electrical power systems may cause overall system instability if a power limit range is exceeded. This paper deals with stability analysis of the proposed aircraft power system in order to determine the power limit range and possible differences when varying system parameters such as DC bus capacitance, electrical frequency, and controller parameters. The non-linear mathematical model of the system is derived and linearized. The system is also modelled in SimPower Simulink environment as comparison with the Simulink non-linear mathematical model. Results are verified in time-domain simulations for both models. Eigenvalue theorem is applied on the linearized model to investigate stability margins and their dependence on system parameter changes.