Possibility-Based Sizing Method for Hybrid Electric Aircraft
At the early stage of aircraft design, the sizing process plays a critical role in determining key parameters such as mass, geometry, and propulsion system characteristics based on design requirements. However, existing sizing methods, relying on historical data, assumptions, and low-fidelity models...
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| Format: | Article |
| Language: | English |
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IEEE
2025-01-01
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| Series: | IEEE Access |
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| Online Access: | https://ieeexplore.ieee.org/document/10845774/ |
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| author | Zin Win Thu Maxim Tyan Yong-Hyeon Choi Mohammad Irfan Alam Jae-Woo Lee |
| author_facet | Zin Win Thu Maxim Tyan Yong-Hyeon Choi Mohammad Irfan Alam Jae-Woo Lee |
| author_sort | Zin Win Thu |
| collection | DOAJ |
| description | At the early stage of aircraft design, the sizing process plays a critical role in determining key parameters such as mass, geometry, and propulsion system characteristics based on design requirements. However, existing sizing methods, relying on historical data, assumptions, and low-fidelity models, often fail to address uncertainties, leading to costly design modifications, particularly for electric aircraft, where technological uncertainties pose significant challenges. It is crucial to account for uncertainties at the sizing stage to ensure reliable outcomes, highlighting the need for a method that efficiently integrates uncertainty into the process. We propose a possibility-based sizing approach, which accounts for design uncertainties into sizing process, yields possible feasible design outcomes and identifies critical parameters for refinement in later stages. We verified our approach with two case studies meeting CS23 certification. The results demonstrate design feasibility through trade-offs between conservative and optimistic designs, with possibility indices from 0.75 to 1, identifying maximum and stall speeds as key limiting factors. Sensitivity analysis shows that aerodynamic design, airframe, and propulsion efficiencies significantly impact maximum takeoff mass. Propulsion system integration achieves a relative mass reduction of 0.05, outperforming hydrogen fuel cells (0.025) and battery systems (0.009). The study highlights that power density is more critical than battery energy density in high-power segments, providing valuable insights for sizing and key parameters in future hybrid electric aircraft development. |
| format | Article |
| id | doaj-art-7eaaa18028b44d3c947508fdbb61b2be |
| institution | Kabale University |
| issn | 2169-3536 |
| language | English |
| publishDate | 2025-01-01 |
| publisher | IEEE |
| record_format | Article |
| series | IEEE Access |
| spelling | doaj-art-7eaaa18028b44d3c947508fdbb61b2be2025-02-05T00:00:57ZengIEEEIEEE Access2169-35362025-01-0113209452095910.1109/ACCESS.2025.353169610845774Possibility-Based Sizing Method for Hybrid Electric AircraftZin Win Thu0https://orcid.org/0000-0003-2948-4873Maxim Tyan1https://orcid.org/0000-0001-5076-7689Yong-Hyeon Choi2Mohammad Irfan Alam3https://orcid.org/0000-0003-0296-3364Jae-Woo Lee4https://orcid.org/0000-0002-3109-798XDepartment of Aerospace Information Engineering, Konkuk University, Seoul, South KoreaKonkuk Aerospace Design-Airworthiness Institute (KADA), Konkuk University, Seoul, South KoreaDepartment of Aerospace Information Engineering, Konkuk University, Seoul, South KoreaKonkuk Aerospace Design-Airworthiness Institute (KADA), Konkuk University, Seoul, South KoreaDepartment of Aerospace Information Engineering, Konkuk University, Seoul, South KoreaAt the early stage of aircraft design, the sizing process plays a critical role in determining key parameters such as mass, geometry, and propulsion system characteristics based on design requirements. However, existing sizing methods, relying on historical data, assumptions, and low-fidelity models, often fail to address uncertainties, leading to costly design modifications, particularly for electric aircraft, where technological uncertainties pose significant challenges. It is crucial to account for uncertainties at the sizing stage to ensure reliable outcomes, highlighting the need for a method that efficiently integrates uncertainty into the process. We propose a possibility-based sizing approach, which accounts for design uncertainties into sizing process, yields possible feasible design outcomes and identifies critical parameters for refinement in later stages. We verified our approach with two case studies meeting CS23 certification. The results demonstrate design feasibility through trade-offs between conservative and optimistic designs, with possibility indices from 0.75 to 1, identifying maximum and stall speeds as key limiting factors. Sensitivity analysis shows that aerodynamic design, airframe, and propulsion efficiencies significantly impact maximum takeoff mass. Propulsion system integration achieves a relative mass reduction of 0.05, outperforming hydrogen fuel cells (0.025) and battery systems (0.009). The study highlights that power density is more critical than battery energy density in high-power segments, providing valuable insights for sizing and key parameters in future hybrid electric aircraft development.https://ieeexplore.ieee.org/document/10845774/Hybrid electric aircraftsizingdesign under uncertaintypossibility-based design optimizationbattery and hydrogen fuel cell |
| spellingShingle | Zin Win Thu Maxim Tyan Yong-Hyeon Choi Mohammad Irfan Alam Jae-Woo Lee Possibility-Based Sizing Method for Hybrid Electric Aircraft IEEE Access Hybrid electric aircraft sizing design under uncertainty possibility-based design optimization battery and hydrogen fuel cell |
| title | Possibility-Based Sizing Method for Hybrid Electric Aircraft |
| title_full | Possibility-Based Sizing Method for Hybrid Electric Aircraft |
| title_fullStr | Possibility-Based Sizing Method for Hybrid Electric Aircraft |
| title_full_unstemmed | Possibility-Based Sizing Method for Hybrid Electric Aircraft |
| title_short | Possibility-Based Sizing Method for Hybrid Electric Aircraft |
| title_sort | possibility based sizing method for hybrid electric aircraft |
| topic | Hybrid electric aircraft sizing design under uncertainty possibility-based design optimization battery and hydrogen fuel cell |
| url | https://ieeexplore.ieee.org/document/10845774/ |
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