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Finite Element Analysis of an Aircraft Wing Leading Edge Made of GLARE Material for Structural Integrity

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Abstract

The present paper characterizes the structure of 3D model of an aircraft wing leading edge of a passenger aircraft considering GLARE laminates as one of the candidate materials through finite element analysis. The investigation is carried out on different types of GLARE configurations and the results of finite element analysis are well compared analytically with benchmark tests to demonstrate the performance of the modeling technique adopted. The GLARE laminate materials are found suitable for their application in the wing leading edge with some reservation on GLARE 3/2 and GLARE 4/3 for Al alloy 2024-T3 thickness, between 0.2 and 0.4 mm. The finite element approach is able to predict the mechanical behavior of structural elements fast enough so that the results can be incorporated into normal design iteration processes.

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Authors and Affiliations

  1. Nitte Meenakshi Institute of Technology, Bangalore, India

    Balachandra P. Shetty & Sudheer Reddy

  2. Regional Center for Military Airworthiness, Bangalore, India

    R. K. Mishra

Authors
  1. Balachandra P. Shetty
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  2. Sudheer Reddy
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  3. R. K. Mishra
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Correspondence to R. K. Mishra.

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Shetty, B.P., Reddy, S. & Mishra, R.K. Finite Element Analysis of an Aircraft Wing Leading Edge Made of GLARE Material for Structural Integrity. J Fail. Anal. and Preven. 17, 948–954 (2017). https://doi.org/10.1007/s11668-017-0331-2

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  • DOI: https://doi.org/10.1007/s11668-017-0331-2

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