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Free vibration analysis of a rotating double tapered beam with flexible root via differential quadrature method

Mustafa Tolga Tolga Yavuz (Faculty of Aeronautics and Astronautics Engineering, Istanbul Technical University, Istanbul, Turkey)
İbrahim Özkol (Faculty of Aeronautics and Astronautics Engineering, Istanbul Technical University, Istanbul, Turkey)

Aircraft Engineering and Aerospace Technology

ISSN: 0002-2667

Article publication date: 28 June 2021

Issue publication date: 5 August 2021

77

Abstract

Purpose

This study aims to develop the governing differential equation and to analyze the free vibration of a rotating non-uniform beam having a flexible root and setting angle for variations in operating conditions and structural design parameters.

Design/methodology/approach

Hamiltonian principle is used to derive the flapwise bending motion of the structure, and the governing differential equations are solved numerically by using differential quadrature with satisfactory accuracy and computation time.

Findings

The results obtained by using the differential quadrature method (DQM) are compared to results of previous studies in the open literature to show the power of the used method. Important results affecting the dynamics characteristics of a rotating beam are tabulated and illustrated in concerned figures to show the effect of investigated design parameters and operating conditions.

Originality/value

The principal novelty of this paper arises from the application of the DQM to a rotating non-uniform beam with flexible root and deriving new governing differential equation including various parameters such as rotary inertia, setting angle, taper ratios, root flexibility, hub radius and rotational speed. Also, the application of the used numerical method is expressed clearly step by step with the algorithm scheme.

Keywords

Citation

Yavuz, M.T.T. and Özkol, İ. (2021), "Free vibration analysis of a rotating double tapered beam with flexible root via differential quadrature method", Aircraft Engineering and Aerospace Technology, Vol. 93 No. 5, pp. 900-914. https://doi.org/10.1108/AEAT-01-2021-0014

Publisher

:

Emerald Publishing Limited

Copyright © 2021, Emerald Publishing Limited

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