S.N. Jung, J.-S. Park, Y.H. You, Y.H. Yu, J.-W. Kim, S.-H. Park, D.-H. Kim

In the present work, the comprehensive structural dynamics (CSD) analysis codes including DYMORE and CAMRAD II are used to evaluate the accuracy of the aeroelastic analysis solution as well as to validate the higher harmonic control aeroacoustic rotor test (HART) II data obtained for the aerodynamic and structural loads of the model-scale B0-105 helicopter in descending flight condition. A total of 16 finite elements along with 17 aerodynamic panels are used for the CAM RAD II analysis, whereas in the DYMORE analysis, 10 finite elements with 31 equally-spaced aerodynamic panels are utilized. To improve the prediction capability of DYMORE analysis, the finite state dynamic inflow model is upgraded with a free vortex wake model comprised of near shed wake and trailed tip vortices. The predicted results on structural dynamics analysis, aerodynamic loads, blade motions, and structural loads are correlated with the HART II measurement data for the baseline (BL), minimum noise (MN), and minimum vibration (MV) cases. It is found that an improvement of solution, especially for BVI (Blade Vortex Interaction) airloads, is achieved with the free wake method employed in the DYMORE analysis. Overall, fair to good correlation is achieved for the test cases considered in this study.

35th European Rotorcraft Forum 2009,

Conference Paper

englisch

21,0 x 29,7 cm, 13 Seiten

DGLR-Bericht, 2009, 2009-03, 35th European Rotorcraft Forum 2009 - Conference Proceedings; S.1-13; 2009; Deutsche Gesellschaft für Luft- und Raumfahrt - Lilienthal-Oberth e.V., Bonn

NA

in getr. Zählung;

bo 105 helicopter, aeroelastics, rotorcrafts

Bestellbar

2009