Formulation for flutter and vibration analysis of a hingeless helicopter blade in hover: part II. Results of flutter stability and vibration analysis of a hingeless helicopter blade in hover

Abstract

Purpose

This study aims to carry out flutter stability and vibration analysis of a uniform hingeless rotor blade in hovering flight conditions.

Design/methodology/approach

The perturbation equations are obtained using the governing differential equations of motion derived in Part I (Aircraft Engineering and Aerospace Technology, Vol. 79 No. 2, 2007). The differential transform method (DTM) is applied to the perturbation equations of motion and the transformed equations are coded in the computer package Mathematica.

Findings

The effects of the built‐in pretwist angle and the rotational speed ratio on the natural frequencies are investigated and the results are compared with the results in literature.

Originality/value

This study, in carrying out an analysis of flutter stability and vibration of a uniform hingless rotor blade, is in good agreement with previous studies in the literature.

Citation

Ozdemir Ozgumus, O. and Kaya, M.O. (2007), "Formulation for flutter and vibration analysis of a hingeless helicopter blade in hover: part II. Results of flutter stability and vibration analysis of a hingeless helicopter blade in hover", Aircraft Engineering and Aerospace Technology, Vol. 79 No. 3, pp. 231-237. https://doi.org/10.1108/00022660710743822