Dynamic characterisation of a damaged composite structure with stiffeners employing fibre bragg gratings

T.H. Ooijevaar, J. Botsis (Editor), Th. Gmür (Editor), F.P. Grooteman, J. Cugnoni (Editor), Laurent Warnet, Richard Loendersloot, Remko Akkerman, Andries de Boer

Research output: Contribution to conferencePaper

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Abstract

One of the key issues in composite structures for aircraft applications is the early detection and localisation of damage. Often service induced damage does not involve visible plastic deformation, but internal matrix related damage, like transverse cracks and delaminations. Their detection imposes costly maintenance techniques. Vibration based damage identification methods are promising as an alternative for the time consuming and costly Non-Destructive Testing methods currently available. These methods also offer the potential to be used in a real-time health monitoring system. The measured change of the dynamic properties is employed to identify damage such as delaminations. Earlier performed research [1] showed that the Modal Strain Energy Damage Index algorithm [2] is a suitable method to identify impact induced damage in a fibre reinforced composite plate structure with stiffeners using laser vibrometer measurements. The damage identification algorithm requires the computation of the second derivative of the displacement mode shapes. The goal is to extent this research by applying fibre Bragg gratings since they can be valuable. Firstly, optical fibre sensors are suitable for integration, which is required in a Structural Health Monitoring environment. Secondly, measured strain mode shapes could be advantageous with respect to the numerical errors induced by the computation of second derivatives of the displacement mode shapes. Before applying the damage identification algorithm, it is a challenge to accurately extract the dynamic properties. The dynamic properties of a damaged composite T-shaped stiffener section, shown in figure 1, are investigated in this work using fibre Bragg gratings.
Original languageEnglish
Pages155-156
Publication statusPublished - 2011

Fingerprint

Fiber Bragg gratings
Composite structures
Delamination
Derivatives
Structural health monitoring
Composite materials
Fiber optic sensors
Strain energy
Nondestructive examination
Plastic deformation
Aircraft
Health
Cracks
Fibers
Lasers
Monitoring

Keywords

  • Mode shape
  • Structural Health Monitoring
  • IR-79159
  • Modal strain energy
  • dynamic characterisation
  • Fibre reinforced composite
  • Fibre Bragg Grating
  • METIS-282569

Cite this

Ooijevaar, T. H., Botsis, J. (Ed.), Gmür, T. (Ed.), Grooteman, F. P., Cugnoni, J. (Ed.), Warnet, L., ... de Boer, A. (2011). Dynamic characterisation of a damaged composite structure with stiffeners employing fibre bragg gratings. 155-156.
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Dynamic characterisation of a damaged composite structure with stiffeners employing fibre bragg gratings. / Ooijevaar, T.H.; Botsis, J. (Editor); Gmür, Th. (Editor); Grooteman, F.P.; Cugnoni, J. (Editor); Warnet, Laurent; Loendersloot, Richard; Akkerman, Remko; de Boer, Andries.

2011. 155-156.

Research output: Contribution to conferencePaper

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T1 - Dynamic characterisation of a damaged composite structure with stiffeners employing fibre bragg gratings

AU - Ooijevaar, T.H.

AU - Grooteman, F.P.

AU - Warnet, Laurent

AU - Loendersloot, Richard

AU - Akkerman, Remko

AU - de Boer, Andries

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A2 - Gmür, Th.

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AB - One of the key issues in composite structures for aircraft applications is the early detection and localisation of damage. Often service induced damage does not involve visible plastic deformation, but internal matrix related damage, like transverse cracks and delaminations. Their detection imposes costly maintenance techniques. Vibration based damage identification methods are promising as an alternative for the time consuming and costly Non-Destructive Testing methods currently available. These methods also offer the potential to be used in a real-time health monitoring system. The measured change of the dynamic properties is employed to identify damage such as delaminations. Earlier performed research [1] showed that the Modal Strain Energy Damage Index algorithm [2] is a suitable method to identify impact induced damage in a fibre reinforced composite plate structure with stiffeners using laser vibrometer measurements. The damage identification algorithm requires the computation of the second derivative of the displacement mode shapes. The goal is to extent this research by applying fibre Bragg gratings since they can be valuable. Firstly, optical fibre sensors are suitable for integration, which is required in a Structural Health Monitoring environment. Secondly, measured strain mode shapes could be advantageous with respect to the numerical errors induced by the computation of second derivatives of the displacement mode shapes. Before applying the damage identification algorithm, it is a challenge to accurately extract the dynamic properties. The dynamic properties of a damaged composite T-shaped stiffener section, shown in figure 1, are investigated in this work using fibre Bragg gratings.

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KW - IR-79159

KW - Modal strain energy

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ER -

Ooijevaar TH, Botsis J, (ed.), Gmür T, (ed.), Grooteman FP, Cugnoni J, (ed.), Warnet L et al. Dynamic characterisation of a damaged composite structure with stiffeners employing fibre bragg gratings. 2011.