EPSRC Reference: |
GR/L51348/01 |
Title: |
INVESTIGATION OF MATRIX CRACKING AND DELAMINATION IN COMPOSITE PLATES WITH A HOLE UNDER BIAXIAL LOADING |
Principal Investigator: |
Soutis, Professor C |
Other Investigators: |
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Researcher Co-Investigators: |
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Project Partners: |
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Department: |
Aeronautics |
Organisation: |
Imperial College London |
Scheme: |
Standard Research (Pre-FEC) |
Starts: |
27 February 1998 |
Ends: |
26 February 2001 |
Value (£): |
182,665
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EPSRC Research Topic Classifications: |
Materials Characterisation |
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EPSRC Industrial Sector Classifications: |
Aerospace, Defence and Marine |
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Related Grants: |
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Panel History: |
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Summary on Grant Application Form |
The fracture process of composite laminates subjected to quasi-static or fatigue tensile loading is known to involve a sequential accumulation of damage, in the form of matrix cracking, 0* splitting and delamination prior to catastrophic failure. A better understanding of damage growth with increasing applied loads will provide analytical models to predict the stiffness properties as a function of damage and also to predict the failure strength of the notched composite laminates. In previous work by Soutis and co-workers the Equivalent Constraint MODEL (ECM) was developed to predict matrix cracking multiplication in multi-directional laminates and its effect on laminate stiffness properties. The analysis was also extended to predict delaminations growing from the tips of transverse ply cracks for balanced symmetric laminates subjected to uniaxial tensile loading. We are now proposing to develop the model further and consider plates with open holes loaded in biaxial tension. Failure under biaxial loading has been poorly understood and physically-based failure criteria, at present, are not available.
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Key Findings |
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Potential use in non-academic contexts |
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Impacts |
Description |
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Summary |
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Date Materialised |
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Sectors submitted by the Researcher |
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Project URL: |
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Further Information: |
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Organisation Website: |
http://www.imperial.ac.uk |