A design chain for preliminary design of hybrid-electric and full-electric aircraft allowed to explore different possible innovative concepts aiming to find out the best configuration with respect to top-level requirements. The aim of this work was to opportunely describe how it was possible to obtain a high-fidelity estimation of mass and stiffness properties for main wing components (spars, ribs, skin and stringers). The configuration under consideration hereinafter is a full-electric configuration of a commuter 19 passengers, which provides for 8 electric motors distributed along the wingspan, with two tip electric motors as a primary propulsive system. The design starting point was the estimation of flight loads, which come out from V-n diagram. Afterwards, in order to refine the first level weight estimation (based on analytic method) a dedicated high-fidelity structural analysis was performed, which allowed a higher-fidelity strength assessment as well. This approach allowed to verify the structural efficiency of the wing within the aircraft flight envelope and to optimize the structure components.
A Design Chain for Distributed Electric Propulsion with Increased Fidelity Structural Strength Assessment and Mass Estimation / Ongut, A. E.; Cusati, V.; Memmolo, V.; Nicolosi, F.; Orefice, F.; Qiao, D.; Lemmens, Y.. - (2022), pp. 1-15. (Intervento presentato al convegno AIAA Science and Technology Forum and Exposition, AIAA SciTech Forum 2022 tenutosi a usa nel 2022) [10.2514/6.2022-0169].
A Design Chain for Distributed Electric Propulsion with Increased Fidelity Structural Strength Assessment and Mass Estimation
Cusati V.;Memmolo V.;Nicolosi F.;
2022
Abstract
A design chain for preliminary design of hybrid-electric and full-electric aircraft allowed to explore different possible innovative concepts aiming to find out the best configuration with respect to top-level requirements. The aim of this work was to opportunely describe how it was possible to obtain a high-fidelity estimation of mass and stiffness properties for main wing components (spars, ribs, skin and stringers). The configuration under consideration hereinafter is a full-electric configuration of a commuter 19 passengers, which provides for 8 electric motors distributed along the wingspan, with two tip electric motors as a primary propulsive system. The design starting point was the estimation of flight loads, which come out from V-n diagram. Afterwards, in order to refine the first level weight estimation (based on analytic method) a dedicated high-fidelity structural analysis was performed, which allowed a higher-fidelity strength assessment as well. This approach allowed to verify the structural efficiency of the wing within the aircraft flight envelope and to optimize the structure components.I documenti in IRIS sono protetti da copyright e tutti i diritti sono riservati, salvo diversa indicazione.
