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http://dx.doi.org/10.9766/KIMST.2020.23.6.533

Nonlinear Vibration Analyses of Stiffened Composite Panels under Combined Thermal and Random Acoustic Loads  

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)
Publication Information
Journal of the Korea Institute of Military Science and Technology / v.23, no.6, 2020 , pp. 533-541 More about this Journal
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
Stiffened Composite Panel; Snap-through; Thermal Load; Random Acoustic Load; Nonlinear Vibration Response;
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