Zijun Yi¹, Dan Xie^2,*

The International Conference on Computational & Experimental Engineering and Sciences, Vol.30, No.2, pp. 1-1, 2024, DOI:10.32604/icces.2024.012704

Abstract Hypersonic aircraft face complex aerodynamic forces and severe aerothermal issues. While aerodynamic and aerothermal empirical solutions exhibit high computational efficiency, they lack precision. Numerical approaches equipped with accuracy but come with high computational costs. To address the contradiction between precision and efficiency, some research on hypersonic unsteady aerodynamic and aerothermal Reduced Order Models (ROMs) was conducted in this study, using Kriging surrogate method.
Meanwhile, hypersonic aircraft typically feature numerous thin-wall structures. The strong coupling of aerodynamic, aerothermal, and elasticity will inevitably lead to aerothermoelastic effects. This study centered on the Thermal Protection System (TPS) panel… More >

Liang Yang^1,2, Jie Zhang¹, Jinfeng Xia¹, Siwen Zhang¹, Yang Yang³, Zhigang Chu^2,*

Sound & Vibration, Vol.58, pp. 171-183, 2024, DOI:10.32604/sv.2024.056968 - 21 October 2024

Abstract Helmholtz resonators are widely used to control low frequency noise propagating in pipes. In this paper, the elastic bottom plate of Helmholtz resonator is simplified as a single degree of freedom (SDOF) vibration system with acoustic excitation, and a one-dimensional lumped-parameter analytical model was developed to accurately characterize the structure-acoustic coupling and sound transmission loss (STL) of a Helmholtz resonator with an elastic bottom plate. The effect of dynamical parameters of elastic bottom plate on STL is analyzed by utilizing the model. A design criterion to circumvent the effect of wall elasticity of Helmholtz resonators More >

Winston Wai Shing Ma¹, Lei Zhang^2,3, Junhao Ding¹, Shuo Qu¹, Xu Song^1,*, Michael Yu Wang^4,*

The International Conference on Computational & Experimental Engineering and Sciences, Vol.29, No.2, pp. 1-1, 2024, DOI:10.32604/icces.2024.011319

Abstract Elastically isotropic open-cell lattice metamaterials exhibit identical elastic properties along arbitrary directions, and are ideal candidates for applications with unknown primary loading directions. Their open-cell properties are preferred for additive manufacturing processes and multifunctional applications requiring mass and heat transfer. This presentation focuses on the design, simulation, fabrication, and experimental tests of elastically isotropic open-cell lattice metamaterials with superior stiffness. First, a family of elastically isotropic truss lattices are analytically devised through combining elementary cubic lattices with contrary elastic anisotropy. The proposed stretching-dominated truss lattices can reach nearly 1/3 of the Hashin-Shtrikman upper bounds at… More >

Zhehan Ji¹, Tongqing Guo^1,*, Di Zhou¹, Zhiliang Lu¹, Binbin Lyu²

CMES-Computer Modeling in Engineering & Sciences, Vol.138, No.1, pp. 489-508, 2024, DOI:10.32604/cmes.2023.029088 - 22 September 2023

Abstract The reduced weight and improved efficiency of modern aeronautical structures result in a decreasing separation of frequency ranges of rigid and elastic modes. Particularly, a high-aspect-ratio flexible flying wing is prone to body freedom flutter (BFF), which is a result of coupling of the rigid body short-period mode with 1^st wing bending mode. Accurate prediction of the BFF characteristics is helpful to reflect the attitude changes of the vehicle intuitively and design the active flutter suppression control law. Instead of using the rigid body mode, this work simulates the rigid body motion of the model by… More >

Yang Liu^1,*, Luis Dorfmann²

The International Conference on Computational & Experimental Engineering and Sciences, Vol.27, No.4, pp. 1-1, 2023, DOI:10.32604/icces.2023.09499

Abstract In this talk, we present some analytical results concerning localized instabilities in stretched soft cylinders with residual-stress effect. Within the framework of finite elasticity, a bifurcation analysis is carried out based on the incremental theory. It is found that with the residual stress effect taken into consideration additional singularities of the incremental equations appear. To overcome this difficulty we apply the Stroh formulism and an expansion methodology and derive a bifurcation condition. Then we consider three loading scenarios and perform a detailed analysis of the bifurcation behaviors. It turns out that the zero mode, giving More >

IVANA PAJIC-LIJAKOVIC^*, MILAN MILIVOJEVIC

BIOCELL, Vol.47, No.11, pp. 2321-2334, 2023, DOI:10.32604/biocell.2023.043796 - 27 November 2023

Abstract The biointerface dynamics influence any cancer spreading through the epithelium since it is documented in the early stages some malignancies (like epithelial cancer). The altered rearrangement of epithelial cells has an impact on the development of cancer. Therefore, it is necessary to comprehend the underlying biological and physical mechanisms of this biointerface dynamics for early suppression of cancer. While the biological mechanisms include cell signaling and gene expression, the physical mechanisms are several physical parameters such as the epithelial-cancer interfacial tension, epithelial surface tension, and compressive stress accumulated within the epithelium. Although the segregation of… More > Graphic Abstract

Dan Xie^1,*, Shihao Zhang¹, Zijun Yi¹

The International Conference on Computational & Experimental Engineering and Sciences, Vol.26, No.1, pp. 1-1, 2023, DOI:10.32604/icces.2023.010490

Abstract Considering the high cost of numerical simulation for aeroelastic coupling analysis, it is difficult to directly apply it to engineering. In this paper, the typical swept trapezoidal wing of hypersonic aircraft [1] is simplified to a cantilever trapezoidal plate [2]. Based on semi-analytical method [3], including von Karman plate theory to consider the structural geometric nonlinearity, third-order piston theory to calculate quasi steady aerodynamic force, and Rayleigh-Ritz method to characterize the displacement as a mode superposition form, the aeroelastic equation of the swept trapezoidal wing is established, and the fourthorder Runge Kutta numerical integration is More >

Junzhe Cui¹, Dechun Zhang¹, Peng Li^1,*, Yiren Yang¹

The International Conference on Computational & Experimental Engineering and Sciences, Vol.26, No.1, pp. 1-1, 2023, DOI:10.32604/icces.2023.010401

Abstract This study investigates the static instability of a cracked plate in subsonic airflow. The plate model is an inverted cantilever plate, where its leading edge is free and the trailing edge the clamped. A mathematical model of the crack is developed using the Dirac function, while Theodorsen aerodynamic mode is applied for the fluid force. To account for angle discontinuity caused by cracks, Fourier expansion is employed to transform the form corresponding to the angle into a continuous model. The critical divergent dynamic pressure and mode of an inverted cantilever plate with a crack are More >

Salvatore Brischetto^*, Roberto Torre, Domenico Cesare

CMES-Computer Modeling in Engineering & Sciences, Vol.136, No.3, pp. 2551-2594, 2023, DOI:10.32604/cmes.2023.026312 - 09 March 2023

Abstract This new work aims to develop a full coupled thermomechanical method including both the temperature profile and displacements as primary unknowns of the model. This generic full coupled 3D exact shell model permits the thermal stress investigation of laminated isotropic, composite and sandwich structures. Cylindrical and spherical panels, cylinders and plates are analyzed in orthogonal mixed curved reference coordinates. The 3D equilibrium relations and the 3D Fourier heat conduction equation for spherical shells are coupled and they trivially can be simplified in those for plates and cylindrical panels. The exponential matrix methodology is used to… More >

Changrong Zhang, Hongtao Guo, Li Yu, Binbin Lv, Hongya Xia^*

CMES-Computer Modeling in Engineering & Sciences, Vol.136, No.2, pp. 1743-1758, 2023, DOI:10.32604/cmes.2023.025528 - 06 February 2023

Abstract This study presents a high-speed geometrically nonlinear flutter analysis calculation method based on the high-precision computational fluid dynamics/computational structural dynamics methods. In the proposed method, the aerodynamic simulation was conducted based on computational fluid dynamics, and the structural model was established using the nonlinear finite element model and tangential stiffness matrix. First, the equilibrium position was obtained using the nonlinear static aeroelastic iteration. Second, the structural modal under a steady aerodynamic load was extracted. Finally, the generalized displacement time curve was obtained by coupling the unsteady aerodynamics and linearized structure motion equations. Moreover, if the… More > Graphic Abstract