Structural Engineering and Mechanics

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Numerical vibration correlation technique analyses for composite cylinder under compression and internal pressure

  • Do-Young Kim (Rotorcraft Structural Design Team, Korea Aerospace Industries) ;
  • Chang-Hoon Sim (Department of Aerospace Engineering, Chungnam National University) ;
  • Jae-Sang Park (Department of Aerospace Engineering, Chungnam National University) ;
  • Joon-Tae Yoo (Launcher Structures and Materials Team, Korea Aerospace Research Institute) ;
  • Young-Ha Yoon (Launcher Structures and Materials Team, Korea Aerospace Research Institute) ;
  • Keejoo Lee (Small Launch Vehicle Research Division, Korea Aerospace Research Institute)
  • Received : 2023.04.03
  • Accepted : 2023.07.23
  • Published : 2023.09.10
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Abstract

This study conducts numerical analyses of a thin-walled composite cylinder under axial compression and internal pressure of 10 kPa. Numerical vibration correlation technique and nonlinear postbuckling analyses are conducted using the nonlinear finite element analysis program, ABAQUS. The single perturbation load approach and measured imperfection data are used to represent the geometric initial imperfection of thin-walled composite cylinder. The buckling knockdown factors are derived using present initial imperfection and analysis methods under axial compression without and with the internal pressure. Furthermore, the buckling knockdown factors are compared with the buckling test and computation time are calculated. In this study, derived buckling knockdown factors in present study have difference within 10% as compared with the buckling test. It is shown that nonlinear postbuckling analysis can derive relatively accurate buckling knockdown factor of present thin-walled cylinders, however, numerical vibration correlation technique derives reasonable buckling knockdown factors compared with buckling test. Therefore, this study shows that numerical vibration correlation technique can also be considered as an effective numerical method with 21~91% reduced computation time than nonlinear postbuckling analysis for the derivation of buckling knockdown factors of present composite cylinders.

Keywords

Acknowledgement

This work was supported by research on the Korea Space Launch Vehicle (KSLV-II) funded by the Ministry of Science and ICT (MSIT, Korea). The work was supported by the National Research Foundation of Korea (NRF) grant funded by the Korea government (MSIT) (NRF-2022M1A3B8076744).

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