alexa Impact Analysis of Composite Repair Patches of Different Shapes at Low Velocities for Aircraft Composite Structures
ISSN: 2168-9792

Journal of Aeronautics & Aerospace Engineering
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Research Article

Impact Analysis of Composite Repair Patches of Different Shapes at Low Velocities for Aircraft Composite Structures

Gangadharan S1*, Baliga SV2, Sonawane NH2, Sathyanarayan P2 and Shruti Kamdar3

1Department of Mechanical Engineering, Embry-Riddle Aeronautical University, 600 South Clyde Morris Blvd, Daytona Beach, Florida 32114, USA

2Department of Aerospace Engineering, Embry-Riddle Aeronautical University, 600 South Clyde Morris Blvd, Daytona Beach, Florida 32114, USA

3Department of Design Engineering, EGA, Honda Engineering North America, 640 Colemans Crossing Blvd, Marysville, OH 43040, USA

*Corresponding Author:
Gangadharan S
Professor, Department of Mechanical Engineering
Embry-Riddle Aeronautical University
600 South Clyde Morris Blvd, Daytona Beach, FL 32114,USA
Tel: +1 386-226-6100
E-mail: [email protected]

Received Date: July 25, 2016; Accepted Date: October 26, 2016; Published Date: October 31, 2016

Citation: Gangadharan S, Baliga SV, Sonawane NH, Sathyanarayan P, Kamdar S (2016) Impact Analysis of Composite Repair Patches of Different Shapes at Low Velocities for Aircraft Composite Structures. J Aeronaut Aerospace Eng 5: 173. doi: 10.4172/2168-9792.1000173

Copyright: © 2016 Gangadharan S, et al. This is an open-access article distributed under the terms of the Creative Commons Attribution License, which permits unrestricted use, distribution, and reproduction in any medium, provided the original author and source are credited.

 

Abstract

The area under crack for various aircraft composite structures can be effectively repaired using composite materials. Low velocity impact can cause barely visible damage to the interior structure of laminated composite. These impacts can cause delamination in composite materials. In this study, a finite element analysis was conducted using Abaqus/Explicit and the results of the analysis were compared to the experimental data from literature. E-glass/epoxy composite laminate was subjected to a low velocity impact test. To study the effect of patch repair, a composite patch was applied on a cracked laminate and a low velocity impact was then conducted on this model. The FEA results were validated with the experimental data and an approach to model an ideal composite patch shape was conducted. Different patch shapes like square, rectangle, circle and ellipse were designed and analysed on the crack by keeping the surface area of the patch common. All these patches were compared and an ideal patch shape was found for the model based on stress concentration on the patch. Finally, a parametric study was performed considering the change in impactor speed and impactor material on impact damage. The effectiveness of finite element analysis of low velocity impact on aircraft composite structures is demonstrated.

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