S.H. Hong, D.K. Kim, S.N. Jung

This study investigates the optimal vibration reduction using the IBC (Individual Blade Control) actuation concept for a coaxial lift-offset (L.O.) rotorcraft in high-speed cruise flight. The rotorcraft vibration analysis model consists of a three-bladed coaxial rotor and a one-dimensional (1D) finite element (FE) fuselage stick model. A 1D FE stick model of the fuselage is constructed based on the natural frequency data of XH-59A and several other conventional helicopters. A total of 14 free vibrating modes are used to describe the airframe motions, after conducting a convergence study on the vibration behavior of the vehicle. The rotor-body vibration analysis is carried out using either one-way or two-way coupled method, and the results are validated with XH-59A flight test data. The two-way coupled predictions show relatively good correlations with the flight test data. The active vibration reduction gains obtained at the rotor hub and the pilot-seat via various actuation scenarios are examined. The IBC actuation is demonstrated to be very effective in reducing the vibration levels at both the locations of the vehicle. A multi-harmonic IBC actuation schedule enables to suppress the overall vehicle vibration by 80.6%, as compared to the baseline uncontrolled case.

49th European Rotorcraft Forum 2023, Bückeburg, 2023

Conference Paper

englisch

21,0 x 29,7 cm, 12 Seiten

DGLR-Bericht, 2023, 2023-01, 49th European Rotorcraft Forum 2023 - Proceedings; S.1-12; 2023; Deutsche Gesellschaft für Luft- und Raumfahrt - Lilienthal-Oberth e.V., Bonn

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2023