R. Steininger, G.N. Barakos, M.A. Woodgate

Helicopters vibration is a well-documented area with the main rotor identified as a key source. A proposed mitigation is based on active rotor blade twist. This promises a reduction in noise and vibration, specially via avoidance of BVI effects, and has some potential for power reduction. For the development and certification of such devices, there is a need to accurately simulate the twist actuators, and rotor structure within a high-fidelity CFD framework. Two structural modelling approaches for rotors in forward flight are compared in this work. A conventional, one-dimensional, beam model is typical, where the static and dynamic twist is applied via rigid rotations on the blade. The second approach uses a medium-fidelity structural model made of 3D elements, where the active twist piezoelectric actuators are modelled via a thermal analogy method. This work presents a comparison of the two approaches.

49th European Rotorcraft Forum 2023, Bückeburg, 2023

Conference Paper

englisch

21,0 x 29,7 cm, 13 Seiten

DGLR-Bericht, 2023, 2023-01, 49th European Rotorcraft Forum 2023 - Proceedings; S.1-13; 2023; Deutsche Gesellschaft für Luft- und Raumfahrt - Lilienthal-Oberth e.V., Bonn

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2023