Multidisciplinary Design Optimization Framework with Coupled Derivative Computation for Hybrid Aircraft

Autor: Joaquim R. R. A. Martins, Alessandro Sgueglia, Nathalie Bartoli, John T. Hwang, John P. Jasa, Peter Schmollgruber, Justin S. Gray, Joseph Morlier, Emmanuel Benard
Přispěvatelé: Centre National de la Recherche Scientifique - CNRS (FRANCE), Ecole nationale supérieure des Mines d'Albi-Carmaux - IMT Mines Albi (FRANCE), Institut National des Sciences Appliquées de Toulouse - INSA (FRANCE), Institut Supérieur de l'Aéronautique et de l'Espace - ISAE-SUPAERO (FRANCE), National Aeronautics and Space Administration - NASA (USA), Office National d'Etudes et Recherches Aérospatiales - ONERA (FRANCE), Université Toulouse III - Paul Sabatier - UT3 (FRANCE), University of California - UC San Diego (USA), University of Michigan - U-M (USA), NASA Glenn Research Center (Clevaland, USA), ONERA / DTIS, Université de Toulouse [Toulouse], ONERA-PRES Université de Toulouse, Institut Supérieur de l'Aéronautique et de l'Espace (ISAE-SUPAERO), University of Michigan [Ann Arbor], University of Michigan System, University of California [San Diego] (UC San Diego), University of California, NASA Glenn Research Center, NASA
Jazyk: angličtina
Rok vydání: 2020
Předmět:
Zdroj: Journal of Aircraft
Journal of Aircraft, American Institute of Aeronautics and Astronautics, 2020, pp.1-15. ⟨10.2514/1.C035509⟩
ISSN: 0021-8669
DOI: 10.2514/1.C035509⟩
Popis: International audience; Hybrid-electric aircraft are a potential way to reduce the environmental footprint of aviation. Research aimed at this subject has been pursued over the last decade; nevertheless, at this stage, a full overall aircraft design procedure is still an open issue. This work proposes to enrich the procedure for the conceptual design of hybrid aircraft found in literature through the definition of a multidisciplinary design optimization (MDO) framework aimed at handling design problems for such kinds of aircraft. The MDO technique has been chosen because the hybrid aircraft design problem shows more interaction between disciplines than a conventional configuration, and the classical approach based on multidisciplinary design analysis may neglect relevant features. The procedure has been tested on the case study of a single-aisle aircraft featuring hybrid propulsion with distributed electric ducted fans. The analysis considers three configurations (with 16, 32, and 48 electric motors) compared with a conventional baseline at the same 2035 technological horizon. To demonstrate the framework’s capability, these configurations are optimized with respect to fuel and energy consumption. It is shown that the hybrid-electric concept consumes less fuel/energy when it flies on short range due to the partial mission electrification. When one increases the design range, penalties in weight introduced by hybrid propulsion overcome the advantages of electrified mission segment: the range for which hybrid aircraft have the same performance of the reference conventional aircraft is named the “breakdown range.” Starting from this range, the concept is no longer advantageous compared to conventional aircraft. Furthermore, a tradeoff between aerodynamic and propulsive efficiency is detected, and the optimal configuration is the one that balances these two effects. Finally, multiobjective optimization is performed to establish a tradeoff between airframe weight and energy consumption.
Databáze: OpenAIRE
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