Effect of Skin-core Delamination on the Interlaminar Stress Distribution in Sandwich Composites

Avnish Kumar Shukla; Ashutosh Kumar; Hukam Singh; Rakesh Kumar Shukla; Pawan Mishra

doi:https://doi.org/10.51976/ijari.511728

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Effect of Skin-core Delamination on the Interlaminar Stress Distribution in Sandwich Composites

Avnish Kumar Shukla, Ashutosh Kumar, Hukam Singh, Rakesh Kumar Shukla, Pawan Mishra

Vol 5 , Issue 1 , January - March 2017 | Pages: 174-180 | Research Paper

https://doi.org/10.51976/ijari.511728

Received: January 25, 2017 | Revised: February 20, 2017 | Accepted: February 28, 2017 | Published Online: March 15, 2017

Author Details ( * ) denotes Corresponding author

1. * Avnish Kumar Shukla, Department of Mechanical Engineering, Krishna Engineering College, Ghaziabad, Uttar Pradesh, India (jajivarghese@gmail.com)

2. Ashutosh Kumar, Department of Mechanical Engineering, Krishna Engineering College, Ghaziabad, Uttar Pradesh, India

3. Hukam Singh, Department of Mechanical Engineering, Krishna Engineering College, Ghaziabad, Uttar Pradesh, India

4. Rakesh Kumar Shukla, Department of Mechanical Engineering, Krishna Engineering College, Ghaziabad, Uttar Pradesh, India

5. Pawan Mishra, Department of Mechanical Engineering, Krishna Engineering College, Ghaziabad, Uttar Pradesh, India

Sandwich honeycomb panels are used in wing-fuselage fairings, rudder and elevator surfaces, and the leading and trailing edge of wing panels etc.It consists of thin facesheetswith high stiffness and a thick corewith high shear strength, between them. It is advantageous due to high strength to weight ratio.Interlaminar stresses are developed due to mismatch of elastic moduli and fibre orientation angle between the layers, which causes delamination. The possibility of delamination growth is more when even a small delamination is present in the sandwich panel. In this study, the effect of delamination between core and facesheet on interlaminar stresses is analysed. Ansys 14.0 software is used to perform the finite element analysis.A uniformtransverse load is applied on the top facesheet. The interlaminar stresses along the circumference of selected concentric rings, around the delamination are observed. The variation in interlaminar stresses, along three concentric rings, due to the presence of delamination of different sizes are presented.

Keywords

Interlaminar Stress; Sandwich Composites; Face Sheet; Core; Laminate; FEM; Flexural Stiffness; Fiber Orientation Angle

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