AN EXPERIMENTAL STUDY OF THE STRUCTURAL DAMPING OF THE FULL-SCALE HELICOPTER MAIN ROTOR BLADE FROM COMPOSITE LAMINATED MATERIALS

摘要

In this paper experimental results of structural vibratory testing for the light multipurpose helicopter main rotor blade of composite laminated materials are presented. This testing included determination of the natural oscillation modes and natural frequency of the structure in oscillations, as well as defining the blade structural damping. The measurement was performed for three different full-scale models with three different types of cores of the main rotor blade: 1-^sRohacell 71 - polyurethane foam, 2-^sNomex aramid honeycomb and 3-Nomex phenolic honeycomb, and the results are presented in this paper.