Journal of Aerospace System Engineering (항공우주시스템공학회지)

The Society for Aerospace System Engineering (항공우주시스템공학회)
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Buckling Characteristics of Skin-Stringer Composite Stiffened Panel

  • Noh, Ji-Sub (School of Mechanical and Aerospace Engineering, Gyeongsang National University) ;
  • Ghim, Yeong-Taek (Songwol Technology Co., Ltd.) ;
  • Shin, Joon-Hyung (School of Mechanical and Aerospace Engineering, Gyeongsang National University) ;
  • Kwon, Bo-Seong (School of Mechanical and Aerospace Engineering, Gyeongsang National University) ;
  • Byun, Joon-Hyung (Composite Research Division, Korea Institute of Materials Science) ;
  • Nam, Young-Woo (School of Mechanical and Aerospace Engineering, Gyeongsang National University) ;
  • Kweon, Jin-Hwe (School of Mechanical and Aerospace Engineering, Gyeongsang National University)
  • Received : 2020.01.21
  • Accepted : 2020.09.21
  • Published : 2020.12.31
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Abstract

Skin-stringer structures are widely used in aircrafts due to their advantage of minimizing structural weight while maintaining load carrying capacity. However, buckling load can cause serious damage to these structures. Therefore, the buckling characteristics of skin-stringer structures should be carefully considered during the design phase to ensure structural soundness. In this study, finite element method was applied to predict the buckling characteristics of stiffened panels. In terms of the failure mode, finite element analysis showed a symmetrical buckling mode, whereas an asymmetrical mode was determined by experimentation. The numerical results were obtained and compared to the experimental data, showing a difference of 9.3% with regard to the buckling loads.

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References

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