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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