Formulation for flutter and vibration analysis of a hingeless helicopter blade in hover: Part I

Abstract

Purpose

This study aims to derive the kinetic and the potential energy expressions of a rotating uniform hingeless rotor blade and the aerodynamic loads that act on the blade element in hovering flight conditions.

Design/methodology/approach

The blade is modeled as an Euler‐Bernoulli beam. The governing partial differential equations of motion and the associated boundary conditions are derived using the Hamilton's principle.

Findings

The derivations of the energy expressions and the aerodynamic loads are made in a detailed way by including several explanatory tables. The resultant equations of motion are in good agreement with the literature. Additionally, in this work the hub radius effect is included in the equations of motion.

Originality/value

Arguably this study achieves a breakthrough in deriving the kinetic and the potential energy expressions of a rotating uniform hingeless rotor blade and the aerodynamic loads that act on the blade element in hovering flight conditions.

Citation

Ozdemir Ozgumus, O. and Kaya, M.O. (2007), "Formulation for flutter and vibration analysis of a hingeless helicopter blade in hover: Part I", Aircraft Engineering and Aerospace Technology, Vol. 79 No. 2, pp. 177-183. https://doi.org/10.1108/00022660710732734