In this study, a parallel hybrid system using an electric motor and an internal combustion engine is designed for a light utility helicopter. Energy and exergy analyses were performed and evaluated for take-off phase of a Robinson R22 Beta II Light Utility Helicopter at various altitudes for different hybridization factors. The maximum energy efficiency and exergy efficiency were found to be as 16.03% and 11.86% respectively at sea level and hybridization factor was 0%. The lowest energy efficiency and exergy efficiency were 13.71% and 10.15 respectively while hybridization factor was 6% at 3000 m altitude. The highest loss exergy and exergy destructions were calculated to be 30.30 kW and 552.75 kW respectively where hybridization factor was 0% at sea level. Furthermore, the lowest loss exergy and exergy destruction value was 24.66 kW and 440.89 kW at 3000 m altitude and hybridization factor was 6%, respectively. (C) 2019 Elsevier Ltd. All rights reserved.