Manufacturing options for secondary aircraft CFRP sandwich components
Manufacturing options for secondary aircraft CFRP sandwich components
The objective of this research is to reduce the cost of carbon fibre sandwich component manufacture for use in aircraft secondary structure. The current paper describes the design of generic components to be representative of secondary structure components and the design of a full-scale pressure load test rig to provide validation for structural analysis being carried out using Finite Element analysis (FEA). For comparison to the FEA model, optical techniques will be used to measure stress/strain during the mechanical tests. The current paper has described the results of a feasibility study of three such optical techniques; namely Thermoelastic Stress Analysis (TSA), Pulse Phase Thermography (PPT) and Digital Image Correlation (DIC). These feasibility tests showed TSA and DIC can offer useable results for measurements of carbon fibre sandwich structure.
aircraft, cfrp, sandwich, structure
Crump, D.A.
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Dulieu-Barton, J.M.
9e35bebb-2185-4d16-a1bc-bb8f20e06632
Savage, J.
eb3584a2-0c3a-4cf7-af84-894babf15610
2007
Crump, D.A.
ab7e71bf-ab02-4fb6-9052-bf2374f7fb55
Dulieu-Barton, J.M.
9e35bebb-2185-4d16-a1bc-bb8f20e06632
Savage, J.
eb3584a2-0c3a-4cf7-af84-894babf15610
Crump, D.A., Dulieu-Barton, J.M. and Savage, J.
(2007)
Manufacturing options for secondary aircraft CFRP sandwich components.
Sixteenth International Conference on Composite Materials (ICCM 16), Ky�to-shi, Japan.
07 - 12 Jul 2007.
8 pp
.
Record type:
Conference or Workshop Item
(Paper)
Abstract
The objective of this research is to reduce the cost of carbon fibre sandwich component manufacture for use in aircraft secondary structure. The current paper describes the design of generic components to be representative of secondary structure components and the design of a full-scale pressure load test rig to provide validation for structural analysis being carried out using Finite Element analysis (FEA). For comparison to the FEA model, optical techniques will be used to measure stress/strain during the mechanical tests. The current paper has described the results of a feasibility study of three such optical techniques; namely Thermoelastic Stress Analysis (TSA), Pulse Phase Thermography (PPT) and Digital Image Correlation (DIC). These feasibility tests showed TSA and DIC can offer useable results for measurements of carbon fibre sandwich structure.
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Published date: 2007
Venue - Dates:
Sixteenth International Conference on Composite Materials (ICCM 16), Ky�to-shi, Japan, 2007-07-07 - 2007-07-12
Keywords:
aircraft, cfrp, sandwich, structure
Organisations:
Fluid Structure Interactions Group
Identifiers
Local EPrints ID: 49039
URI: http://eprints.soton.ac.uk/id/eprint/49039
PURE UUID: fc25106a-434f-477c-b018-aae2db6b6837
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Date deposited: 22 Oct 2007
Last modified: 08 Jan 2022 07:03
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Contributors
Author:
D.A. Crump
Author:
J. Savage
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