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Volume 40 Issue 9
Sep.  2014
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Journal of Beijing University of Aeronautics and Astronautics  > 2014  >  40(9): 1299-1304.
Xu Rongzhang, Guan Zhidong, Liu Lu, et al. Effect of buckling mode on performance of post-buckled composite stringer-stiffened panels with debond[J]. Journal of Beijing University of Aeronautics and Astronautics, 2014, 40(9): 1299-1304. doi: 10.13700/j.bh.1001-5965.2013.0605(in Chinese)
Citation: Xu Rongzhang, Guan Zhidong, Liu Lu, et al. Effect of buckling mode on performance of post-buckled composite stringer-stiffened panels with debond[J]. Journal of Beijing University of Aeronautics and Astronautics, 2014, 40(9): 1299-1304. doi: 10.13700/j.bh.1001-5965.2013.0605(in Chinese)
shu

Effect of buckling mode on performance of post-buckled composite stringer-stiffened panels with debond

doi: 10.13700/j.bh.1001-5965.2013.0605
  • 1.

    School of Aeronautic Science and Engineering, Beijing University of Aeronautics and Astronautics, Beijing 100191, China

  • 2. The First Aircraft Design and Research Institute of China Aviation Industry, Xi'an 710089, China

  • Received Date: 22 Oct 2013
  • Publish Date: 20 Sep 2014
    Abstract
  • Because of the proximity of first and second buckling load, some specific stringer-stiffened panels will exhibit different buckling modes under uniaxial compression load, which causes their post-buckling behavior strikingly different. Test and numerical calculation was conducted to study this phenomenon. Moiré interferometry and ultrasonic scan were used to monitor the buckling mode and debond. Based on the software of ABAQUS, a finite element was developed. Virtual crack closure technology (VCCT) was used to simulate the interfaces with artificial debond. The initial geometric imperfection was led into model to process the nonlinear post-buckling analysis. By comparing the strain energy release rates of the crack front, the performance of debond propagation in two different modes was determined. The calculated results are coordinated with the tested results very well. The results indicate that the different damaging propagates under two buckling modes will generate that strength of panels with three half waves buckling mode exceeds the panels with two half waves buckling mode.

     

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