Delamination monitoring of honeycomb composite for aircraft structure using fiber bragg gratings / Ramzyzan Ramly

Since two decades ago, non-metallic composites especially honeycomb core sandwich panel were widely used in the secondary non-controlling surfaces such as the horizontal and vertical stabilizer main boxes. One of the problems in honeycomb sandwich structure is detection of delamination between the c...

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Main Author:	Ramly, Ramzyzan
Format:	Thesis
Language:	English
Published:	2014
Subjects:	Honeycomb structure
Online Access:	http://ir.uitm.edu.my/id/eprint/16309/ http://ir.uitm.edu.my/id/eprint/16309/2/ABS_RAMZYZAN%20RAMLY%20TDRA%20VOL%207%20IGS%2015.pdf

id	uitm-16309
recordtype	eprints
spelling	uitm-163092018-09-28T08:07:10Z http://ir.uitm.edu.my/id/eprint/16309/ Delamination monitoring of honeycomb composite for aircraft structure using fiber bragg gratings / Ramzyzan Ramly Ramly, Ramzyzan Honeycomb structure Since two decades ago, non-metallic composites especially honeycomb core sandwich panel were widely used in the secondary non-controlling surfaces such as the horizontal and vertical stabilizer main boxes. One of the problems in honeycomb sandwich structure is detection of delamination between the core and the skin. In order to overcome this problem, most aircraft manufacturers equipped their aircrafts with Health Monitoring System (HMS) in place to monitor the status of the aircraft structural integrity. There are many types of HMS being adopted by the aircraft manufacturers. The type of HMS being studied in this research is the one using Fiber Bragg Grating (FBG) system, which utilize optical strain sensor using light wave as the means of signal detection. The objectives of this research are to detect the location of delamination in sandwich panel and to determine the extents or the relative size of the delamination using FBG. In this study, an FBG sensor array was embedded in the honeycomb core carbon fiber skin sandwich panel. The sandwich panel was fabricated in accordance to the aviation industry standards process as well as the materials used in fabrication. The FBG’s used in the research had two sensors with grating wavelengths of 1550 nm and 1555 nm spaced approximately 100 mm between the two. The grating had a length of 15 mm. The sandwich panel had a dimension of 300 mm by 200 mm by 20 mm. The core was made from Nomex® honeycomb while the skin was made from plain weave carbon fiber supplied by Hexcel®. There were five cases being studied with different sizes of delamination were pre-introduced at different locations, using a non-stick plastic used in the vacuum bagging process, laid between the carbon fiber skin and the honeycomb core. Finite Element Analysis simulation was conducted to monitor the axial displacement at the location of the FBG’s in the specimen. The simulation was validated by experiment. The specimens underwent a 3-point bending test. The loads were applied in the increment of 0.2 kN up to 2.2 kN. The whole panel failed at the load of 2.6 kN. The data was recorded using FBG Scanner. From the simulation and experiment, there was an agreement and similarities in terms of the patterns of the result. From the research, the use of FBG was a proven method where the relative location of delamination could be detected and relative size of the delamination could be determined. The findings could be used to help monitoring the aircraft structural integrity in the area of honeycomb sandwich panel. 2014 Thesis NonPeerReviewed text en http://ir.uitm.edu.my/id/eprint/16309/2/ABS_RAMZYZAN%20RAMLY%20TDRA%20VOL%207%20IGS%2015.pdf Ramly, Ramzyzan (2014) Delamination monitoring of honeycomb composite for aircraft structure using fiber bragg gratings / Ramzyzan Ramly. PhD thesis, Universiti Teknologi MARA.
repository_type	Digital Repository
institution_category	Local University
institution	Universiti Teknologi MARA
building	UiTM Institutional Repository
collection	Online Access
language	English
topic	Honeycomb structure
spellingShingle	Honeycomb structure Ramly, Ramzyzan Delamination monitoring of honeycomb composite for aircraft structure using fiber bragg gratings / Ramzyzan Ramly
description	Since two decades ago, non-metallic composites especially honeycomb core sandwich panel were widely used in the secondary non-controlling surfaces such as the horizontal and vertical stabilizer main boxes. One of the problems in honeycomb sandwich structure is detection of delamination between the core and the skin. In order to overcome this problem, most aircraft manufacturers equipped their aircrafts with Health Monitoring System (HMS) in place to monitor the status of the aircraft structural integrity. There are many types of HMS being adopted by the aircraft manufacturers. The type of HMS being studied in this research is the one using Fiber Bragg Grating (FBG) system, which utilize optical strain sensor using light wave as the means of signal detection. The objectives of this research are to detect the location of delamination in sandwich panel and to determine the extents or the relative size of the delamination using FBG. In this study, an FBG sensor array was embedded in the honeycomb core carbon fiber skin sandwich panel. The sandwich panel was fabricated in accordance to the aviation industry standards process as well as the materials used in fabrication. The FBG’s used in the research had two sensors with grating wavelengths of 1550 nm and 1555 nm spaced approximately 100 mm between the two. The grating had a length of 15 mm. The sandwich panel had a dimension of 300 mm by 200 mm by 20 mm. The core was made from Nomex® honeycomb while the skin was made from plain weave carbon fiber supplied by Hexcel®. There were five cases being studied with different sizes of delamination were pre-introduced at different locations, using a non-stick plastic used in the vacuum bagging process, laid between the carbon fiber skin and the honeycomb core. Finite Element Analysis simulation was conducted to monitor the axial displacement at the location of the FBG’s in the specimen. The simulation was validated by experiment. The specimens underwent a 3-point bending test. The loads were applied in the increment of 0.2 kN up to 2.2 kN. The whole panel failed at the load of 2.6 kN. The data was recorded using FBG Scanner. From the simulation and experiment, there was an agreement and similarities in terms of the patterns of the result. From the research, the use of FBG was a proven method where the relative location of delamination could be detected and relative size of the delamination could be determined. The findings could be used to help monitoring the aircraft structural integrity in the area of honeycomb sandwich panel.
format	Thesis
author	Ramly, Ramzyzan
author_facet	Ramly, Ramzyzan
author_sort	Ramly, Ramzyzan
title	Delamination monitoring of honeycomb composite for aircraft structure using fiber bragg gratings / Ramzyzan Ramly
title_short	Delamination monitoring of honeycomb composite for aircraft structure using fiber bragg gratings / Ramzyzan Ramly
title_full	Delamination monitoring of honeycomb composite for aircraft structure using fiber bragg gratings / Ramzyzan Ramly
title_fullStr	Delamination monitoring of honeycomb composite for aircraft structure using fiber bragg gratings / Ramzyzan Ramly
title_full_unstemmed	Delamination monitoring of honeycomb composite for aircraft structure using fiber bragg gratings / Ramzyzan Ramly
title_sort	delamination monitoring of honeycomb composite for aircraft structure using fiber bragg gratings / ramzyzan ramly
publishDate	2014
url	http://ir.uitm.edu.my/id/eprint/16309/ http://ir.uitm.edu.my/id/eprint/16309/2/ABS_RAMZYZAN%20RAMLY%20TDRA%20VOL%207%20IGS%2015.pdf
first_indexed	2023-09-18T22:55:47Z
last_indexed	2023-09-18T22:55:47Z
_version_	1777417843685457920

Delamination monitoring of honeycomb composite for aircraft structure using fiber bragg gratings / Ramzyzan Ramly

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