Validation of Comprehensive Helicopter Aeroelastic Analysis with Experimental Data

Defence Science Journal

Ranjan Ganguli¹  Shrinivas R. Bhat¹ 

[1] Indian Institute of Science, Bangalore

关键词: Helicopter;    vibration;    validation;    aeroelastic analysis;    finite element model;    rotor blade;    aerodynamic models;    free-wake models;    unsteady aerodynamics;    quasi-steady aerodynamics;   

DOI  :  

学科分类：社会科学、人文和艺术（综合）

来源: Defence Scientific Information & Documentation Centre

【 摘 要 】

The experimental data for a Cbladed soft-inplane hingeless main rotor is used to validate a comprehensive aeroelastic analysis. A finite element model has been developed for the rotor blade which predicts rotating frequencies quite well, across a range of rotation speeds. The helicopter is trimmed and the predicted trim-control angles are found to be In the range of measured values for a variety of flight speeds. Power predictions over a range of forward speeds also compare well. Finally, the aeroelastlc analysis is used to study the Importance of aerodynamic models on the vibration predict~onU. nsteady aerodynamics and free-wake models have been investigated.

【 授权许可】

Unknown