Assessment of a hybrid propulsion system for short-mid range application with a low-order code

The increase in air traffic expected the next years must be accompanied by innovation to ensure lowest possible environmental impact. Hybrid electric-thermal propulsion systems are currently being investigated and could represent a breakthrough for sustainability sector. However, transition electric remains challenging due current level of energy density related storage systems, additional components associated with power conversion control not mention cost all equipment. purpose this study is carry out preliminary assessment hybrid system short-mid range aircraft. This investigates series configuration, where turboshaft, high temperature superconducting (HTS) motor, batteries converters interact provide necessary flight. A zero-dimensional procedure developed estimate mass efficiency powertrain selected flight mission. Thermal engines modeled low-order code coupled through python routine. comparison terms weight emissions reported designed conventional one. analysis shows that two similar but, presence batteries, even considering higher technology than one, leads significant second part focuses on pollutant emissions, showing can reduce CO 2 58% NOx 68% compared system. Despite excellent premise, reduction payload aircraft causes per passenger only NOx. For reason, further technological improvement needed make advantageous both emissions.