The purpose of this paper is to present the development and application of a numerical formulation for the structural dynamics and aeroelastic analysis of new generation helicopter and tiltrotor rotor blades. These are characterized by a curvilinear elastic axis, typically with the presence of tip sweep and anhedral angles.

    Design/methodology/approach

    The structural dynamics model implemented is based on nonlinear, flap-lag-torsion, rotating beam equations that are valid for slender, homogeneous, isotropic, non-uniform, twisted blades undergoing moderate displacements. A second-order approximation scheme for strain-displacement is adopted. Aerodynamic contributions for aeroelastic applications are derived from sectional theories, with inclusion of wake inflow models to take into account three-dimensional effects. The numerical integration is obtained through implementation within the COMSOL Multiphysics Finite-Element-Method (FEM) software code, considering the elastic axis of arbitrary curvilinear shape.

    Findings

    The computational tool developed is validated by comparisons with results available in the literature. These demonstrate the capability of the tool to accurately predict structural dynamics and aeroelastic behavior of curved-axis rotor blades. In particular, the influence of sweep and anhedral angles at the blade tip is successfully captured.

    Research limitations/implications

    The numerical tool developed is limited to the analysis of isotropic blades, with a simple sectional aerodynamic modeling for aeroelastic applications. However, the flexibility of the process through which the proposed tool has been developed is such that a moderate effort is required for its extension to composite blades and more accurate aerodynamic loads predictions.

    Practical implications

    The proposed computational solver is a reliable tool for preliminary design and optimal design processes of helicopter and tiltrotor rotor blades.

    Originality/value

    Computational tools for rotors with advanced-geometry blades are not commonly available. Therefore, the presentation of a successful way to implement structural dynamics/aeroelastic mathematical formulations for rotor blades with curvilinear elastic axis in highly flexible, multiphysics, FEM-based, commercial software may be of interest for designers and researchers.


    Access

    Check access

    Check availability in my library

    Order at Subito €


    Export, share and cite



    Title :

    Structural-aeroelastic finite element modeling for advanced-geometry rotor blades


    Contributors:

    Published in:

    Publication date :

    2012-10-12


    Size :

    9 pages




    Type of media :

    Article (Journal)


    Type of material :

    Electronic Resource


    Language :

    English





    Aeroelastic Stability of Rotor Blades Using a Parallel Adaptive Finite Element Solver

    Bauchau, O. A. / Bottasso, C. L. / Dindar, M. et al. | British Library Conference Proceedings | 1995


    Aeroelastic Stability of Rotor Blades Using a Parallel Adaptive Finite Element Solver

    Bauchau, O. A. / Bottasso, C. L. / Dindar, M. et al. | British Library Conference Proceedings | 1995


    Aeroelastic Analysis of Helicopter Rotor Blades

    Landmann, Björn / Wagner, Siegfried | AIAA | 2004


    Aeroelastic response characteristics of rotor blades

    NAGARAJA, K. / PIERCE, G. | AIAA | 1980