Singh, Lokk and Dattaguru, B (2013) Delamination Tolerance in Composites under Fatigue Loading. In: JOURNAL OF THE INDIAN INSTITUTE OF SCIENCE, 93 (4). pp. 593-602.
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Delamination is one of the most commonly occurring defects in laminated composite structures. Under operating fatigue loads on the laminate this delamination could grow and totally delaminate certain number of layers from the base laminate. This will result in loss of both compressive residual strength and buckling margins available. In this paper, geometrically non-linear analysis and evaluation of Strain Energy Release Rates using MVCCI technique is presented. The problems of multiple delamination, effect of temperature exposure and delamination from pin loaded holes are addressed. Numerical results are presented to draw certain inferences of importance to design of high technology composite structures such as aircraft wing.
|Item Type:||Journal Article|
|Additional Information:||Copyright for this article belongs to the INDIAN INST SCIENCE, INDIA|
|Keywords:||Composite; Delamination; Fatigue|
|Department/Centre:||Division of Mechanical Sciences > Aerospace Engineering (Formerly, Aeronautical Engineering)|
|Date Deposited:||10 Mar 2014 06:29|
|Last Modified:||10 Mar 2014 06:30|
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