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Performance Analysis of Hybrid-Electric Propulsion Systems for Regional Commuter Aircraft
Aeronautics Institute of Technology (ITA), São Paulo, São José dos Campos, Brazil.
Aeronautics Institute of Technology (ITA), São Paulo, São José dos Campos, Brazil.
Embraer S.A., light Mechanics Department, São Paulo, São José dos Campos, Brazil.
Texas A&M University, Department of Aerospace Engineering, College Station, TX, United States.
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2026 (English)In: IEEE Transactions on Aerospace and Electronic Systems, ISSN 0018-9251, E-ISSN 1557-9603Article in journal (Refereed) Published
Abstract [en]

Aviation plays a fundamental and valuable role in the modern world, yet it faces significant challenges, including high fuel costs and substantial environmental pollution. These issues have prompted the aviation industry to establish emission standards and develop less-polluting propulsion systems, such as those utilizing synthetic fuels, fuel cells, and electrification. Among these, electrification holds promise as a potential solution for reducing emissions in commuter aircraft, despite the mass limitations posed by batteries. In this study, a methodology was developed and implemented within in-house software to simulate the performance of a commuter aircraft with a hybrid-electric propulsion system. The analysis focused on key metrics like fuel economy and climb time to cruise altitude. The EMB-120 Brasilia was chosen as the base aircraft for this research. Its long-standing use by the Brazilian Air Force (FAB), the authors' extensive familiarity with its performance, and the availability of experimental data for lift and drag coefficients made it an ideal model for our simulations. To evaluate the performance of the hybrid propulsion system and compare it with the standard case, a gas turbine was utilized as the primary engine. Mathematical models were developed for the PW118 gas turbine, which powers the real aircraft that was considered the standard case, and for the PT6A-68C, which was suggested as a substitute for the hybrid system. To evaluate the aircraft's performance, a standard mission was simulated on a short-range route of 926 km (500 NM), flying at an altitude of 7,620 m (25,000 ft), a common mission that is used by Brazilian Air Force. For hybrid simulations, battery packs were tested with specific energies ranging from 0.125 kWh/kg to 0.750 kWh/kg, in multiples of the initial value. Batteries with 0.250 kWh/kg were considered the current state-of-the-art, while the 0.750 kWh/kg packs represent an extreme upper bound associated with far-future technological developments. The results demonstrated significant performance gains depending on the chosen battery technology and the power split, the hybrid system achieved fuel savings of up to 18% to 19% and reduced climb time by 17% to 25%. © 1965-2011 IEEE.

Place, publisher, year, edition, pages
Institute of Electrical and Electronics Engineers (IEEE) , 2026.
Keywords [en]
Aircraft Performance, Gas Turbine, Hybrid-Electric Propulsion, Propulsion, Aircraft power systems, Aircraft propulsion, Battery management systems, Battery Pack, Electric propulsion, Electrification, Fighter aircraft, Fuel cells, Fuel economy, Hybrid electric aircraft, Hybrid systems, Synthetic fuels, Vehicle performance, Aviation industry, Brazilian Air Force, Emission standard, Environmental pollutions, Fuel cost, Hybrid-electric propulsion systems, Performance, Performances analysis, Gas turbines
National Category
Vehicle and Aerospace Engineering
Identifiers
URN: urn:nbn:se:mdh:diva-77170DOI: 10.1109/TAES.2026.3695492Scopus ID: 2-s2.0-105039570886OAI: oai:DiVA.org:mdh-77170DiVA, id: diva2:2065607
Available from: 2026-06-03 Created: 2026-06-03 Last updated: 2026-06-03Bibliographically approved

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Kyprianidis, Konstantinos

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