Damage tolerance coupon sizing of composite stiffened panels under impact

Hamid Dalir

Research output: Chapter in Book/Report/Conference proceedingConference contribution

Abstract

The design of aircraft composite stiffened structures subjected to dynamic and impact loadings requires several experimental testing scenarios on the full-size structure. The present paper deals with investigating the feasibility of the use of sub-size test specimens under vertical and lateral impacts on the stiffener free flange based on finite element (FE) models. Simulations were performed on sub-size specimens carefully extracted from the full-size (26.4 × 48.4 × 2.4 in3) impact test panels. The main required specifications of an in-house falling weight impact tester were also determined, discussing the required fixture/jig configuration.

Original languageEnglish (US)
Title of host publicationProceedings of 2016 7th International Conference on Mechanical and Aerospace Engineering, ICMAE 2016
PublisherInstitute of Electrical and Electronics Engineers Inc.
Pages68-72
Number of pages5
ISBN (Electronic)9781467388290
DOIs
StatePublished - Aug 23 2016
Event7th International Conference on Mechanical and Aerospace Engineering, ICMAE 2016 - London, United Kingdom
Duration: Jul 18 2016Jul 20 2016

Other

Other7th International Conference on Mechanical and Aerospace Engineering, ICMAE 2016
CountryUnited Kingdom
CityLondon
Period7/18/167/20/16

Keywords

  • composite stiffened panel
  • finite element analysis
  • fixture/jig
  • impact testing

ASJC Scopus subject areas

  • Aerospace Engineering
  • Mechanical Engineering

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  • Cite this

    Dalir, H. (2016). Damage tolerance coupon sizing of composite stiffened panels under impact. In Proceedings of 2016 7th International Conference on Mechanical and Aerospace Engineering, ICMAE 2016 (pp. 68-72). [7549510] Institute of Electrical and Electronics Engineers Inc.. https://doi.org/10.1109/ICMAE.2016.7549510