20th International Conference on Composite Materials (ICCM20) X-ray CT videos

20th International Conference on Composite Materials (ICCM20) X-ray CT videos

Videos linked to X-ray CT images in paper entitled "X-RAY COMPUTED TOMOGRAPHY OF DAMAGE FORMATION UNDER IN-SITU LOADING" presented at ICCM20, July 2015. X-RAY COMPUTED TOMOGRAPHY OF DAMAGE FORMATION UNDER IN-SITU LOADING A. Sandhu1, L. Glen1, M. Doughty1, A. T. Rhead1 1Department of Mechanical Engineering, University of Bath Claverton Down, Bath, BA2 7AY, UK Email: atr21@bath.ac.uk, web page: http://www.bath.ac.uk/mech-eng Keywords: In-situ loading, X-ray CT, Damage, Impact ABSTRACT Use of X-ray Computed Tomography (XRCT) to investigate damage morphology has previously been constrained to post-test analysis of unloaded coupons. As delaminations and intra-ply cracks close when load is removed, a limit is placed on the information available for identifying mechanisms causing resin and fibre fracture. Here, a newly developed loading stage, for in-situ XRCT imaging of laminates under quasi-static impact loading, is employed to visualise the mechanisms that drive the formation of damage morphologies. Multiple X-ray CT scans taken at increasing indenter displacements reveal the evolution of damage morphology. Various laminates subject to out-of-plane, near-edge or on-edge impacts are assessed. For out-of-plane and on-edge impact, both a conventional and novel stacking sequence are considered. Favourable formation mechanisms that occur in laminates with novel sequences are highlighted. In particular, damage from out-of-plane impacts is seen to occur in two stages. The first stage is instantaneous, with multiple shear-driven intra-ply cracks and inter-ply delaminations occurring at plies with dissimilar interfaces. In the second stage, shear-driven cracking gives way to peeling of layers. This peeling is focussed at certain weaker interfaces and is driven by an intact core of material pushing through the laminate. The latter process is clearly demonstrated by testing of a laminate with stacking sequence [04/904]s. Results indicate that stacking sequence can be used to force the development of favourable damage morphologies that protect load carrying plies and prevent the near surface delaminations which enable sublaminate buckling driven failures.

Subjects:
Mechanical engineering

Cite this dataset as:
Rhead, A., 2015. 20th International Conference on Composite Materials (ICCM20) X-ray CT videos. University of Bath. https://doi.org/10.15125/BATH-00093.

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Data

Near_edge_impact.mp4
video/mp4 (250MB)

Nearedgeunblocked.mp4
video/mp4 (239MB)

Onedgeimpactblockedmp4.mp4
video/mp4 (252MB)

OPDTall.mp4
video/mp4 (252MB)

OPnonDT.mp4
video/mp4 (250MB)

With_impactor_wide_angl3D.mpg
video/mpeg (284MB)

With_impactor_Zoom3D.mpg
video/mpeg (604MB)

With_impactor_Zoom.mpg
video/mpeg (514MB)

With_impactor_wide_angle.mpg
video/mpeg (505MB)

Creators

Andrew Rhead
University of Bath

Documentation

Data collection method:

Paper published at 20th International Conference on Composites Materials (ICCM20), Copenhagen, Denmark, 2015. X-RAY COMPUTED TOMOGRAPHY OF DAMAGE FORMATION UNDER IN-SITU LOADING A. Sandhu1, L. Glen1, M. Doughty1, A. T. Rhead1 1Department of Mechanical Engineering, University of Bath Claverton Down, Bath, BA2 7AY, UK Email: atr21@bath.ac.uk, web page: http://www.bath.ac.uk/mech-eng Keywords: In-situ loading, X-ray CT, Damage, Impact ABSTRACT Use of X-ray Computed Tomography (XRCT) to investigate damage morphology has previously been constrained to post-test analysis of unloaded coupons. As delaminations and intra-ply cracks close when load is removed, a limit is placed on the information available for identifying mechanisms causing resin and fibre fracture. Here, a newly developed loading stage, for in-situ XRCT imaging of laminates under quasi-static impact loading, is employed to visualise the mechanisms that drive the formation of damage morphologies. Multiple X-ray CT scans taken at increasing indenter displacements reveal the evolution of damage morphology. Various laminates subject to out-of-plane, near-edge or on-edge impacts are assessed. For out-of-plane and on-edge impact, both a conventional and novel stacking sequence are considered. Favourable formation mechanisms that occur in laminates with novel sequences are highlighted. In particular, damage from out-of-plane impacts is seen to occur in two stages. The first stage is instantaneous, with multiple shear-driven intra-ply cracks and inter-ply delaminations occurring at plies with dissimilar interfaces. In the second stage, shear-driven cracking gives way to peeling of layers. This peeling is focussed at certain weaker interfaces and is driven by an intact core of material pushing through the laminate. The latter process is clearly demonstrated by testing of a laminate with stacking sequence [04/904]s. Results indicate that stacking sequence can be used to force the development of favourable damage morphologies that protect load carrying plies and prevent the near surface delaminations which enable sublaminate buckling driven failures.

Funders

Publication details

Publication date: 20 July 2015
by: University of Bath

Version: 1

DOI: https://doi.org/10.15125/BATH-00093

URL for this record: https://researchdata.bath.ac.uk/id/eprint/93

Contact information

Please contact the Research Data Service in the first instance for all matters concerning this item.

Contact person: Andrew Rhead

Departments:

Faculty of Engineering & Design
Mechanical Engineering