Investigations on nonlinear aerothermoelastic behaviors of multilayered composite panels subject to frictional boundaries and random acoustic loads in supersonic flow

• Published in: Thin-walled structures Vol. 158; p. 107180
• Main Authors: Zhang, Junxian, Qu, Yegao, Xie, Fangtao, Peng, Zhike, Zhang, Wenming, Meng, Guang
• Format: Journal Article
• Language: English
• Published: Elsevier Ltd 01.01.2021
• Subjects: Acoustic load; Composite laminated panel; Frictional boundary; Non-uniform temperature field; Nonlinear and random vibration; Nonlinear and random vibration; Acoustic load; Composite laminated panel; Frictional boundary; Non-uniform temperature field
• ISSN: 0263-8231; 1879-3223
• DOI: 10.1016/j.tws.2020.107180

This paper is focused on the nonlinear aerothermoelastic analysis of composite laminated panels having non-smooth frictional boundaries and simultaneously subject to combined supersonic aerodynamic, thermal and random acoustic loads. The Reddy's third-order shear deformation plate theory with zig-zag effects is employed to formulate the structural model of the panels. The von Karman strain relationships are considered in order to take into account the geometrical nonlinearities of the panels. The aerodynamic loads and the random acoustic loads acting on the panel are characterized by the quasi-steady first-order piston theory and the Gaussian band-limited white noise, respectively. A four-node finite element is developed to establish the aerothermoelastic models of the panels, and the non-smooth frictional boundaries of the panels are represented by a number of macro-slip friction models. The effects of the aerodynamic forces, acoustic loads, thermal forces and the spatial location of the frictional boundaries on the nonlinear aerothermoelastic responses (including the stable limit-cycle oscillations, chaotic and random vibration responses) of composite laminated panels are examined. The effects of non-uniform distribution of the temperature on the aerothermoelastic behaviors of composite laminated panels are discussed. •Numerical model of composite panels with friction boundaries in multi-fields is established.The numerical model of composite panel with friction boundaries in multi-fields is established.•Physical insight into nonlinear dynamic responses of composite panels in multi-fields is provided.•Effects of normal loads and friction coefficients of boundaries on flutter of composite panels are analyzed.•Effects of non-uniform distributed temperature on flutter of composite panels are discussed.