Stability Analysis and Control Design for Hybrid AC-DC More-Electric Aircraft Power Systems

摘要

This thesis studies the stability of a more-electric aircraft (MEA) power system with hybrid converters and loads, and proposes a control design method using state feedback. The MEA is aimed to replace the conventional nonelectric power in aircraft with electric power in order to reduce the size and weight of the aircraft power system. This thesis considers a model of the MEA power system consisting of the following components: converters with uncontrolled diodes and controlled rectifiers, ideal constant power loads (CPL), and non-ideal CPL driven by electromechanical actuators. The system has narrow stability range under the conventional two-loop PI control. To improve control performance, a full-state feedback control method is developed that can significantly increase the stability margin of the MEA power system.