C. Lee, K. Kong, S.-H. Kang, M. Hwang, S. Shin

When the helicopter rotor collides, the relevant impact load on the blade will be transmitted to the fuselage though its hub. In this paper, collision analysis of the rotor blades under hard impact is conducted by both experimental and numerical approach. To obtain reliable test results, the collision of the rotating blades will be simulated by drop and whirl tower tests. UH-60A main rotor blade is selected and designed for each experiment. For the drop situation, the maximum indentation during the crash impact is evaluated experimentally and numerically using ANSYS LS-DYNA. In addition, the behavior of the rotor blade and the tendency of an impact force in terms of time and displacement under 2 drop tests are compared. Finally, the rotor blade and hub design of Mach-scaled UH-60 rotor blade is conducted for the whirl tower tests. In the future, the whirl tower test will be conducted for hover of both 4-blade and one-blade-out condition at Seoul National University Rotor Test Stand (SNURTS). The loads acting on the hub are measured and correlated against those predicted numerically.

49th European Rotorcraft Forum 2023, Bückeburg, 2023

Conference Paper

englisch

21,0 x 29,7 cm, 9 Seiten

DGLR-Bericht, 2023, 2023-01, 49th European Rotorcraft Forum 2023 - Proceedings; S.1-9; 2023; Deutsche Gesellschaft für Luft- und Raumfahrt - Lilienthal-Oberth e.V., Bonn

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2023