Thin-walled structures of composite material have been widely applied to advanced flight vehicles in recent years. These structures will suffer severe complex loading conditions, a combination of mechanical, aerodynamic, thermal and acoustic loads, which may lead to nonlinear response of the structures. Thin-walled structures subjected to simultaneous effects of thermal and acoustic loads tend to exhibit snap-through response. This paper presents a nonlinear finite element model to study response calculation and characteristic analysis of thin-walled structures under the combined effects of thermal and acoustic loads. The nonlinear large deflection equations of composite panel under thermal acoustic loadings are established and the influence of nonlinear recovery-stress to structure vibration is discussed. Then the effect of geometry nonlinearity caused by thermal and acoustics loadings on dynamic response of panels is analyzed. The results show that temperature will change the deflection and stress response of the panel and cause frequency shifting and broaden the PSD plot. At high noise pressure levels, deflection of the panel will change accordingly, but stress response won’t change because the acoustic pressure completely exceeds the thermal items and constrains the shape-recovery stresses.
BAO Dong-dong, SHA Yun-dong, JIANG Na-na
. Analysis of nonlinear dynamic response of composite thin-walled structure under thermo-acoustic loadings[J]. Journal of Shenyang Aerospace University, 2013
, 30(1)
: 39
-42
.
DOI: 10.3969/j.issn.2095-1248.2013.01.009
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