Performance analysis of a hybrid-electric retrofit of a RUAG Dornier Do 228NG

摘要

The research in this paper provides an analysis of the payload-range capabilities of a retrofitted CS-23, 19-passenger class aircraft, specifically the RUAG Do 228NG. The aircraft is retrofitted with a serial-hybrid electric propulsion system having current technology-level components. The analysis in this paper finds the design points of the propulsion system (battery mass and generator size) with regard to specific operational requirements by performing mission simulations with different flight profiles (operating scenarios). With the requirement of pure electric take-off and initial climb, it was found that two operational parameters, the top-of-climb altitude and the generator-activation altitude, are significant drivers for the battery mass. The generator size is mainly driven by the design's speed. The mission performance results show that operational decisions affect the sizing of a retrofitted serial-hybrid propulsion system. The results suggest that once a system is sized, the airplane cannot easily be operated under different conditions. The calculated payload-range chart shows that the retrofit cannot match the payload-range capabilities of the baseline aircraft, showing a range reduced by 37% at a payload of 50% (1020 kg).