Stochastic dynamic response of delaminated flexbeam like structures
Stochastic dynamic response of delaminated flexbeam like structures
In this work, the free vibration characteristics of flexbeam like structures, typically used in helicopter main or tail rotor blades, are investigated. The tapering effect in these laminated composite structures is introduced by terminating plies, which act as potential delamination sites. Delamination and uncertainties in material properties at various scales influence their dynamic behavior. The variational asymptotic method (VAM) is used as a mathematical framework to develop a model of a tapered composite beam with delamination. Subsequently, the modal characteristics are obtained by coupling the VAM model with the reduced 1D finite element beam model. Stochastic natural frequencies are investigated by combining the source uncertainties in the delaminated structure. Following a detailed validation study, the model capability is demonstrated on flexbeams typically used in helicopter rotor blades.
Composite Structures, Energy Density, Finite Element Formulation, Helicopter Blade, Laminated Composites, Mechanical Properties, Mechanical and Structural Vibrations, Reduced Order Modelling, Rotor Blades, Variational Asymptotic Method
2985-3004
Patil, Priyanka
1f53b814-f4c7-4a9d-9a18-977de9276192
Naskar, Susmita
5f787953-b062-4774-a28b-473bd19254b1
Vinoda, M.T.
db286ef8-97b8-418d-8fd1-5feb33a857a6
Harursampath, Dineshkumar
9856b449-140f-4b10-9e74-259e7f86f9e7
Guruprasad, P.J.
f115e048-9780-44cd-bccf-2eede99f1c51
July 2025
Patil, Priyanka
1f53b814-f4c7-4a9d-9a18-977de9276192
Naskar, Susmita
5f787953-b062-4774-a28b-473bd19254b1
Vinoda, M.T.
db286ef8-97b8-418d-8fd1-5feb33a857a6
Harursampath, Dineshkumar
9856b449-140f-4b10-9e74-259e7f86f9e7
Guruprasad, P.J.
f115e048-9780-44cd-bccf-2eede99f1c51
Patil, Priyanka, Naskar, Susmita, Vinoda, M.T., Harursampath, Dineshkumar and Guruprasad, P.J.
(2025)
Stochastic dynamic response of delaminated flexbeam like structures.
AIAA Journal, 63 (7), .
(doi:10.2514/1.J064711).
Abstract
In this work, the free vibration characteristics of flexbeam like structures, typically used in helicopter main or tail rotor blades, are investigated. The tapering effect in these laminated composite structures is introduced by terminating plies, which act as potential delamination sites. Delamination and uncertainties in material properties at various scales influence their dynamic behavior. The variational asymptotic method (VAM) is used as a mathematical framework to develop a model of a tapered composite beam with delamination. Subsequently, the modal characteristics are obtained by coupling the VAM model with the reduced 1D finite element beam model. Stochastic natural frequencies are investigated by combining the source uncertainties in the delaminated structure. Following a detailed validation study, the model capability is demonstrated on flexbeams typically used in helicopter rotor blades.
Text
8Dec_paper_clean_without highlights
- Accepted Manuscript
More information
Accepted/In Press date: 11 December 2024
e-pub ahead of print date: 22 January 2025
Published date: July 2025
Keywords:
Composite Structures, Energy Density, Finite Element Formulation, Helicopter Blade, Laminated Composites, Mechanical Properties, Mechanical and Structural Vibrations, Reduced Order Modelling, Rotor Blades, Variational Asymptotic Method
Identifiers
Local EPrints ID: 497219
URI: http://eprints.soton.ac.uk/id/eprint/497219
ISSN: 0001-1452
PURE UUID: 3822ced1-115f-45ff-974f-d5cad4fd1c8e
Catalogue record
Date deposited: 16 Jan 2025 17:30
Last modified: 11 Mar 2026 05:01
Export record
Altmetrics
Contributors
Author:
Priyanka Patil
Author:
M.T. Vinoda
Author:
Dineshkumar Harursampath
Author:
P.J. Guruprasad
Download statistics
Downloads from ePrints over the past year. Other digital versions may also be available to download e.g. from the publisher's website.
View more statistics
