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Soutenance de thèse de Jérôme THAUVIN

par Isabelle Clarysse - publié le

Jérome Thauvin,


soutiendra publiquement ses travaux de thèse intitulés :
"Exploring the design space for a hybrid-electric regional aircraft with multidisciplinary design optimisation methods"

le lundi 22 octobre 2018 à 10 h, EINSEEIHT, salle C002.


Mirko HORNUNG, Professeur, Université technique de Munich TUM - Rapporteur
Stéphane BRISSET, Maître de Conférences, Ecole Centrale Lille-L2EP - Rapporteur
Delphine RIU, Professeur, INP de Grenoble-G2ELAB - Examinateur
Xavier ROBOAM, Directeur de Recherche, ENSEEIHT-LAPLACE - Directeur de thèse
Marc BUDINGER, Maître de Conférences, INSA Toulouse-ICA - Directeur de thèse
Bruno SARENI, Professeur, ENSEEIHT-LAPLACE - Codirecteur de thèse
Guillaume BARRAUD, Ingénieur, Airbus Operations SAS - Encadrant
Jean HERMETZ, Directeur de département, ONERA-DCPS - Invité


Hybrid-electric propulsion offers the opportunity to integrate new technology bricks providing additional degrees of freedom to improve overall aircraft performance, limit the use of non-renewable fossil resources and reduce the aircraft environmental footprint. Today, hybrid-electric technology has mainly been applied to ground-based transports, cars, buses and trains, but also ships. The feasibility in the air industry has to be established and the improvement in aircraft performance has still to be demonstrated. This thesis aims to evaluate the energy savings enabled by electric power in the case of a 70-seat regional aircraft.

Evaluating hybrid-electric aircraft performance is even more challenging that the sizing of the different components, the energy management strategies and the mission profiles one can imagine are many and varied. In addition, the overall aircraft design process and the evaluation tools need to be adapted accordingly. The Airbus in-house Multidisciplinary Design Optimisation platform named XMDO, which includes most of the required modifications, is eventually selected and further developed during the thesis.
A reference aircraft equipped with a conventional propulsion system is first optimised with XMDO. Then, different hybrid-electric configurations are optimised under the same aircraft design requirements as the reference. For the electrical components, two levels of technology are defined regarding the service entry date of the aircraft. The optimisation results for a turboelectric and a partial-turboelectric are used to better understand the potential aerodynamic improvements. Optimisations for a parallel-hybrid, including different battery recharge scenarios, highlight the best energy management strategies when batteries are used as secondary energy sources. All the results are finally compared to the reference in terms of fuel and energy efficiencies, for the two electrical technology levels.