Stability Analysis of Power Transfer Using Droop Control in Electric Aircraft Propulsion Systems

Traditional commercial aircraft use a 115Vac to 230Vac electrical system architecture for power generation and distribution with some localised DC conversion system. Moving to a hybrid electrical propulsion system architecture enables the option of executing a high-voltage DC distribution system. The thesis proposed here investigates the optimisation of a parallel hybrid configuration such that it allows greater benefits to be achieved at an aircraft level. The scope of this work will involve modelling an HVDC aircraft electrical system and evaluating electrical system optimisations that can be performed to reduce overall weight of the system and increase aircraft efficiencies. The thesis will be specially focused on the optimisation of the droop control laws to improve the dynamic and steady-state performance of paralleled power sources (active rectifiers, batteries, DC-DC converters) and also the performance of mechanically paralleled electrical drives. This work scope will be linked to existing propulsion system projects such that real world solution can be investigated.