Nuo Ma¹, Qingyang Liu¹, Junhui Meng^1,2,*

The International Conference on Computational & Experimental Engineering and Sciences, Vol.30, No.1, pp. 1-2, 2024, DOI:10.32604/icces.2024.011195

Abstract Due to its flexibility and foldable ability, the inflatable wing is widely employed to loitering munitions and aerostats [1-3]. Meanwhile, as a typical flexible thin-walled structure, the wrinkling and buckling behaviors of the inflatable wing induced in flight will limit its load-bearing capacity [4,5]. Therefore, a wrinkling-resistant structural configuration is the key to improving performance of the inflatable wing. Among various schemes, the swept baffled structure is considered to have the potential to retard wrinkling because of the designable axis of twist [6,7]. However, owing to the flexible large deformation of inflatable wing under aerodynamic… More >

Zhicheng Ou¹, Xiaohu Yao¹, Xiaoqing Zhang^1,2, Xuejun Fan³

CMC-Computers, Materials & Continua, Vol.44, No.3, pp. 205-222, 2014, DOI:10.3970/cmc.2014.044.205

Abstract The buckling of a thin film on a compressible compliant substrate in large deformation is studied. A finite-deformation theory is developed to model the film and the substrate under different original strain-free configurations. The neo-Hookean constitutive relation is applied to describe the substrate. Through the perturbation analysis, the analytical solution for this highly nonlinear system is obtained. The buckling wave number, amplitude and critical condition are obtained. Comparing with the traditional linear model, the buckling amplitude decreases. The wave number increases and relates to the prestrain. With the increment of Poisson’s ratio of the substrate, More >

Fei Jia¹, Xiu-Peng Zheng^1,2, Yan-Ping Cao^1,3, Xi-Qiao Feng¹

CMC-Computers, Materials & Continua, Vol.18, No.2, pp. 105-120, 2010, DOI:10.3970/cmc.2010.018.105

Abstract Recently, a novel technique based on the wrinkling of a bilayer composite film resting on a compliant substrate was proposed to measure the elastic moduli of thin films. In this paper, this technique is studied via theoretical analysis and finite element simulations. We find that under an applied compressive strain, the composite system may exhibit various buckling modes, depending upon the applied compressive strain, geometric and material parameters of the system. The physical mechanisms underlying the occurrence of the two most typical buckling modes are analyzed from the viewpoint of energy. When the intermediate layer More >

Jin-Ho Roh¹, In Lee²

CMES-Computer Modeling in Engineering & Sciences, Vol.26, No.1, pp. 13-30, 2008, DOI:10.3970/cmes.2008.026.013

Abstract A methodology to maintain the configuration of inflated membrane structures using shape memory alloy (SMA) film actuator is numerically investigated. The two- dimensional incremental formulation of the SMA constitutive model is developed. New parameters related to the thermodynamic energy equation are introduced to describe more general behaviors of the SMA film. With numerical algorithm of wrinkling and SMAs, the interactions between the inflated membrane structure and the SMA film are investigated by using a finite element program. The effectiveness of SMA film to control the configuration of an inflated membrane structure is examined. To demonstrate More >

D. H. Pahr¹, F.G. Rammerstorfer¹

CMES-Computer Modeling in Engineering & Sciences, Vol.12, No.3, pp. 229-242, 2006, DOI:10.3970/cmes.2006.012.229

Abstract Sandwich structures are efficient lightweight materials. Due to there design they exhibit very special failure modes such as global buckling, shear crimping, facesheet wrinkling, facesheet dimpling, and face/core yielding. The core of the sandwich is usually made of foams or cellular materials, e.g., honeycombs. Especially in the case of honeycomb cores the correlation between analytical buckling predictions and experiments might be poor (Ley, Lin, and Uy (1999)). The reason for this lies in the fact that analytical formulae typically assume a homogeneous core (continuous support of the facesheets). This work highlights problems of honeycomb core… More >

K. Woo¹, H. Igawa², C.H. Jenkins³

CMES-Computer Modeling in Engineering & Sciences, Vol.6, No.4, pp. 397-408, 2004, DOI:10.3970/cmes.2004.006.397

Abstract This paper presents the development and evaluation of a wrinkling analysis procedure for anisotropic membranes. The procedure is based on a penalty-parameter modified material model and a non-linear root finding to simulate the uni-axial stress state. The procedure was implemented in the ABAQUS finite element code as a user subroutine, and then applied to annular and square membranes. The wrinkle problems were also solved by shell element post-buckling analysis and the results were compared. The effect of anisotropy and unsymmetric loading on the wrinkling behavior was investigated. More >