Mathematical modelling of a gas turbine engine based hybrid propulsion system for regional airplanes

Abstract

The work is a study of light multi-purpose aircraft hybrid propulsion advantages. A comparison of propulsion system dynamics and the integrated flight performance in the cases of turbo-prop and a hybrid turbo-prop propulsion usage has been carried out. Required battery parameters are calculated for usage of hybrid mode during a flight mission and for emergency landing on the hybrid propulsion electrical component. The calculation results showed that a hybrid propulsion system may have a longer operating life, lower fuel consumption during non-cruising flight modes, and the possibility of landing in case of gas turbine failure.