Mathematical analysis of the energy and environmental effects of hybrid (piston prop-electric) light utility helicopter

The gradual decrease in the amount of fossil fuels on earth and the negative environmental effects of fossil fuel usage have brought the importance of zero emission transportation vehicles to the agenda. Various studies have discussed production and secure application of Zero Emission Aircrafts in the past. With current technology, existing battery and fuel cell systems have problems such as additional weight, cost, range, charging times. In this context, hybrid propulsion systems have gained importance in the transition stage to electrical and fuel cell vehicles. In this study, energy consumption and environmental effects were analyzed for parallel hybrid light utility helicopter with piston engine and electric motor. Fuel consumption, CO2 production, impact on human health and ecosystem quality were examined and evaluated for different altitudes and different hybridization factors for during take-off where the maximum power is needed. The calculations were made for various altitudes up to 3000 m above mean sea level. Fuel consumption and CO2 production decreased by 3.91% in the case of hybridization factor 6%, at an altitude of 3000 m. At the same altitude and same hybridization factor, impact on human health and ecosystem quality were determined to be less, drop of 3.27% and 2.92% respectively.