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Damage assessment across hybrid laminates using an array of embedded fibre optic sensors

Damage assessment across hybrid laminates using an array of embedded fibre optic sensors
Damage assessment across hybrid laminates using an array of embedded fibre optic sensors
Hybrid laminates typically consist of alternate layers of fibre-reinforced polymer and aluminium alloy. Developed primarily for fatigue critical aerospace applications, the hybrid laminates are orthotropic materials with lower density and hgher strength compared to the aluminium alloy monolith. One of the damage mechanisms of particular interest is that of fatigue crack growth, which for hybrid laminates is a relatively complex process that includes a combination of delamination and fibre bridging. To facilitate the development of a unified model for both crack and damage growth processes, a remote sensing system, reliant upon fibre optic sensor technology, has been utilised to monitor strain within the composite layer. The fibre optic system, with capacity for sub microstrain resolution, combines time domain multiplexing with line switching to monitor continuously an array of Bragg grating sensors. Herein are detailed the findings from a study performed using an array of 40 sensors distributed across a small area of a test piece containing a fatigue crack initiated at a through-thickness fastener hole. Together with details of system operation, sensor measurements of the strain profiles associated with the developing delamination zone are reported.
281-288
The International Society for Optical Engineering
Austin, T.S.P.
97c7f52a-2535-4fde-b3dc-2150e81ca30f
Singh, M.M.
2fd46335-d898-4bfc-945a-75f3c8e575fd
Gregson, P.J.
ddc3b65d-18fb-4c11-9fa1-feb7e9cbe9fe
Dakin, J.P.
490d5873-c444-423b-8d83-c49f118dc4b5
Powell, P.M.
2fda759a-bb1b-4451-9713-e36535feb341
Austin, T.S.P.
97c7f52a-2535-4fde-b3dc-2150e81ca30f
Singh, M.M.
2fd46335-d898-4bfc-945a-75f3c8e575fd
Gregson, P.J.
ddc3b65d-18fb-4c11-9fa1-feb7e9cbe9fe
Dakin, J.P.
490d5873-c444-423b-8d83-c49f118dc4b5
Powell, P.M.
2fda759a-bb1b-4451-9713-e36535feb341

Austin, T.S.P., Singh, M.M., Gregson, P.J., Dakin, J.P. and Powell, P.M. (1999) Damage assessment across hybrid laminates using an array of embedded fibre optic sensors. In Smart Structures and Materials 1999: Smart Systems for Bridges, Structures, and Highways. vol. 3671, The International Society for Optical Engineering. pp. 281-288 . (doi:10.1117/12.348677).

Record type: Conference or Workshop Item (Paper)

Abstract

Hybrid laminates typically consist of alternate layers of fibre-reinforced polymer and aluminium alloy. Developed primarily for fatigue critical aerospace applications, the hybrid laminates are orthotropic materials with lower density and hgher strength compared to the aluminium alloy monolith. One of the damage mechanisms of particular interest is that of fatigue crack growth, which for hybrid laminates is a relatively complex process that includes a combination of delamination and fibre bridging. To facilitate the development of a unified model for both crack and damage growth processes, a remote sensing system, reliant upon fibre optic sensor technology, has been utilised to monitor strain within the composite layer. The fibre optic system, with capacity for sub microstrain resolution, combines time domain multiplexing with line switching to monitor continuously an array of Bragg grating sensors. Herein are detailed the findings from a study performed using an array of 40 sensors distributed across a small area of a test piece containing a fatigue crack initiated at a through-thickness fastener hole. Together with details of system operation, sensor measurements of the strain profiles associated with the developing delamination zone are reported.

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More information

Published date: 1999
Venue - Dates: Smart Structures and Materials 1999: Smart Systems for Bridges, Structures, and Highways, Newport Beach, United States, 1999-03-01 - 1999-03-02

Identifiers

Local EPrints ID: 76559
URI: http://eprints.soton.ac.uk/id/eprint/76559
PURE UUID: c10149f8-06a9-4083-9d47-0138c7098e81

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Date deposited: 11 Mar 2010
Last modified: 29 Jan 2020 13:25

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