A. Tamer, A. Tatar

An important number of recent urban mobility aircraft have multiple propellers to generate the required levels of power for electric propulsion. The novel urban mobility designs are expected to exhibit more complex aeroelastic behaviour with their multiple propellers distributed over the aircraft structure because of the aeroelastic instabilities such as whirl flutter and wing flutter. While it is possible to use sophisticated numerical simulations to address the aeroelastic instabilities in distributed propulsion aircraft, they are difficult to use in early design stages due to a lack of data and their computational cost when experimenting over a wide range of parameters is required. On the other hand, aeroelastic problems cannot be oversimplified due to their multidisciplinary nature. Therefore, a minimum complexity model is required for the aeroelastic analysis of distributed propulsion aircraft by combining structural and aerodynamic models of the wing and multiple propellers, which is less complex than sophisticated tools yet good enough to capture the instabilities. For this purpose, the authors developed a minimum complexity model for the aeroelastic analysis of such aircraft. In the proposed aeroelastic model, the wing structure is built using a finite volume beam formulation. The unsteady aerodynamics of the wing is based on Wagner's function and formulated for wing sections. Finally, the classical Reed's model is used for the aeroelastic modelling of the propellers. The model is verified against results in the literature and its benefits are further demonstrated through sample analysis.

49th European Rotorcraft Forum 2023, Bückeburg, 2023

Conference Paper

englisch

21,0 x 29,7 cm, 8 Seiten

DGLR-Bericht, 2023, 2023-01, 49th European Rotorcraft Forum 2023 - Proceedings; S.1-8; 2023; Deutsche Gesellschaft für Luft- und Raumfahrt - Lilienthal-Oberth e.V., Bonn

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2023