Identification of Nonlinearities in Joints of a Wing Structure

Nonlinear structural identification is essential in engineering. As new materials are being used and structures become slender and lighter, nonlinear behaviour of structures becomes more important. There have been many studies into the development and application of system identification methods fo...

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Main Authors: M. S. M., Sani, H., Ouyang
Format: Conference or Workshop Item
Language:English
Published: EDP Sciences 2016
Subjects:
Online Access:http://umpir.ump.edu.my/id/eprint/15350/1/matecconf_csndd2016_03006_wing.pdf
http://umpir.ump.edu.my/id/eprint/15350/
http://dx.doi.org/10.1051/matecconf/20168303006
http://dx.doi.org/10.1051/matecconf/20168303006
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spelling my.ump.umpir.153502018-01-22T07:57:44Z http://umpir.ump.edu.my/id/eprint/15350/ Identification of Nonlinearities in Joints of a Wing Structure M. S. M., Sani H., Ouyang TJ Mechanical engineering and machinery Nonlinear structural identification is essential in engineering. As new materials are being used and structures become slender and lighter, nonlinear behaviour of structures becomes more important. There have been many studies into the development and application of system identification methods for structural nonlinearity based on changes in natural frequencies, mode shapes and damping ratios. A great challenge is to identify nonlinearity in large structural systems. Much work has been undertaken in the development of nonlinear system identification methods (e.g. Hilbert Transform, NARMAX, and Proper Orthogonal Decomposition), however, it is arguable that most of these methods are cumbersome when applied to realistic large structures that contain mostly linear modes with some local nonlinearity (e.g. aircraft engine pylon attachment to a wing). In this paper, a multi-shaker force appropriation method is developed to determine the underlying linear and nonlinear structural properties through the use of the measurement and generation of restoring force surfaces. One undamped mode is excited in each multi-shaker test. Essentially, this technique is a derivative of the restoring surface method and involves a non-linear curve fitting performed in modal space. A reduced finite element model is established and its effectiveness in revealing the nonlinear characteristics of the system is discussed. The method is demonstrated through both numerical simulations and experiments on a simple jointed laboratory structure with seeded faults, which represents an engine pylon structure that consists of a rectangular wing with two stores suspended underneath. EDP Sciences 2016-11 Conference or Workshop Item PeerReviewed application/pdf en cc_by http://umpir.ump.edu.my/id/eprint/15350/1/matecconf_csndd2016_03006_wing.pdf M. S. M., Sani and H., Ouyang (2016) Identification of Nonlinearities in Joints of a Wing Structure. In: MATEC Web of Conferences: International Conference on Structural Nonlinear Dynamics and Diagnosis (CSNDD 2016) , 23–25 May 2016 , Marrakech, Morocco. pp. 1-4., 83 (03006). ISSN 2261-236X http://dx.doi.org/10.1051/matecconf/20168303006 http://dx.doi.org/10.1051/matecconf/20168303006
institution Universiti Malaysia Pahang
building UMP Library
collection Institutional Repository
continent Asia
country Malaysia
content_provider Universiti Malaysia Pahang
content_source UMP Institutional Repository
url_provider http://umpir.ump.edu.my/
language English
topic TJ Mechanical engineering and machinery
spellingShingle TJ Mechanical engineering and machinery
M. S. M., Sani
H., Ouyang
Identification of Nonlinearities in Joints of a Wing Structure
description Nonlinear structural identification is essential in engineering. As new materials are being used and structures become slender and lighter, nonlinear behaviour of structures becomes more important. There have been many studies into the development and application of system identification methods for structural nonlinearity based on changes in natural frequencies, mode shapes and damping ratios. A great challenge is to identify nonlinearity in large structural systems. Much work has been undertaken in the development of nonlinear system identification methods (e.g. Hilbert Transform, NARMAX, and Proper Orthogonal Decomposition), however, it is arguable that most of these methods are cumbersome when applied to realistic large structures that contain mostly linear modes with some local nonlinearity (e.g. aircraft engine pylon attachment to a wing). In this paper, a multi-shaker force appropriation method is developed to determine the underlying linear and nonlinear structural properties through the use of the measurement and generation of restoring force surfaces. One undamped mode is excited in each multi-shaker test. Essentially, this technique is a derivative of the restoring surface method and involves a non-linear curve fitting performed in modal space. A reduced finite element model is established and its effectiveness in revealing the nonlinear characteristics of the system is discussed. The method is demonstrated through both numerical simulations and experiments on a simple jointed laboratory structure with seeded faults, which represents an engine pylon structure that consists of a rectangular wing with two stores suspended underneath.
format Conference or Workshop Item
author M. S. M., Sani
H., Ouyang
author_facet M. S. M., Sani
H., Ouyang
author_sort M. S. M., Sani
title Identification of Nonlinearities in Joints of a Wing Structure
title_short Identification of Nonlinearities in Joints of a Wing Structure
title_full Identification of Nonlinearities in Joints of a Wing Structure
title_fullStr Identification of Nonlinearities in Joints of a Wing Structure
title_full_unstemmed Identification of Nonlinearities in Joints of a Wing Structure
title_sort identification of nonlinearities in joints of a wing structure
publisher EDP Sciences
publishDate 2016
url http://umpir.ump.edu.my/id/eprint/15350/1/matecconf_csndd2016_03006_wing.pdf
http://umpir.ump.edu.my/id/eprint/15350/
http://dx.doi.org/10.1051/matecconf/20168303006
http://dx.doi.org/10.1051/matecconf/20168303006
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