Analysis and design of hybrid electric regional turboprop aircraft

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The potential environmental benefits of hybrid electric regional turboprop aircraft in terms of fuel consumption are investigated. Lithium–air batteries are used as energy source in combination with conventional fuel. A validated design and analysis framework is extended with sizing and analysis modules for hybrid electric propulsion system components. In addition, a modified Bre´guet range equation, suitable for hybrid electric aircraft, is introduced. The results quantify the limits in range and performance for this type of aircraft as a function of battery technology level. A typical design for 70 passengers with a design range of 1528 km, based on batteries with a specific energy of 1000 Wh/kg, providing 34% of the shaft power throughout the mission, yields a reduction in emissions by 28%.
Original languageEnglish
Number of pages11
JournalCEAS Aeronautical Journal
Publication statusE-pub ahead of print - 2017


  • Hybrid electric propulsion
  • Range equation
  • Aircraft design
  • Mission analysis


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