Journal of the Korea Institute of Military Science and Technology (한국군사과학기술학회지)

The Korea Institute of Military Science and Technology (한국군사과학기술학회)
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Nonlinear Vibration Analyses of Stiffened Composite Panels under Combined Thermal and Random Acoustic Loads

열-랜덤 음향 하중을 받는 보강된 복합재 패널의 비선형 진동 해석

  • Choi, In-Jun (Department of Aerospace Engineering, Chungnam National University) ;
  • Lee, Hong-Beom (L-SAM Anti Air Missile Systems R&D Team 2, LIG Nex1 Co. Ltd.) ;
  • Park, Jae-Sang (Department of Aerospace Engineering, Chungnam National University) ;
  • Kim, In-Gul (Department of Aerospace Engineering, Chungnam National University)
  • 최인준 (충남대학교 항공우주공학과) ;
  • 이홍범 (LIG넥스원(주) L-SAM체계단 2팀) ;
  • 박재상 (충남대학교 항공우주공학과) ;
  • 김인걸 (충남대학교 항공우주공학과)
  • Received : 2020.08.29
  • Accepted : 2020.11.13
  • Published : 2020.12.05
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Abstract

This study using ABAQUS investigates the nonlinear vibration responses when thermal and random acoustic loads are applied simultaneously to the stiffened composite panels. The nonlinear vibration analyses are performed with changing the number of stiffeners, and layup condition of the skin panel. The panel and stiffeners both are modeled using shell elements. Thermal load (ΔT) is assumed to have the temperature gradient through the thickness direction of the stiffened composite panel. The random acoustic load is represented as stationary white-Gaussian random pressure with zero mean and uniform magnitude over the panels. The thermal postbuckling analysis is conducted using RIKS method, and the nonlinear dynamic analysis is performed using Hilber-HughesTaylor time integration method. When ΔT = 25.18 ℃ and SPL = 105 dB are applied to the stiffened composite panel, the effect of the number of stiffener is investigated, and the snap-through responses are observed for composite panels without stiffeners and with 1 and 3 stiffeners. For investigation of the effect of layup condition of the skin panel, when ΔT = 38.53 ℃ and SPL = 110 dB are applied to the stiffened composite panel, the snap-through responses are shown when the fiber angle of the skin panel is 0°, 30°, and 60°.

Keywords

References

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