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Virtual testing of aircraft structures

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Abstract

This paper will focus on the prediction of aircraft structural strength using virtual testing analysis methods. Virtual testing is a concept with several attributes and is to be understood as the simulation of aircraft structure using advanced nonlinear finite element analysis. It will involve the combination of analysis software, methods, people skills and experience to predict the actual aircraft structural strength with a high level of confidence. This is achieved through the creation and execution of a detailed nonlinear finite element analysis model of an aircraft structure, which represents as accurately as possible the actual physical behaviour when subjected to a wide range of loading scenarios. Creating a virtual representation of an aircraft structure presents the analysts with several significant challenges, including the creation of the complex finite element model that accurately represents the global aircraft structure, and then adding the significant detail in terms of material and construction required to make accurate failure predictions with confidence. An overview will be provided of the general principles used in the process of virtual testing of both metallic and composite aircraft structures. The paper will focus on the key challenges and enablers for future successful virtual testing demonstrations in an industrial context.

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Authors and Affiliations

  1. Airbus in the UK, Bristol, BS997AR, UK

    Morten G. Ostergaard & Andrew R. Ibbotson

  2. Airbus in France, 31060, Toulouse Cedex 9, France

    Olivier Le Roux

  3. Dassault Systèmes Simulia Limited, Warrington, WA3 7PB, UK

    Alan M. Prior

Authors
  1. Morten G. Ostergaard
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  2. Andrew R. Ibbotson
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  3. Olivier Le Roux
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  4. Alan M. Prior
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Correspondence to Morten G. Ostergaard.

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Ostergaard, M.G., Ibbotson, A.R., Roux, O.L. et al. Virtual testing of aircraft structures. CEAS Aeronaut J 1, 83–103 (2011). https://doi.org/10.1007/s13272-011-0004-x

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  • DOI: https://doi.org/10.1007/s13272-011-0004-x

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