Finite element based damage and failure analysis of honeycomb core sandwich composite structures for space applications

Venkatesan, Karthik Rajan; Rai, Ashwin; Chattopadhyay, Amares; Stoumbos, Tom; Inoyama, Daisaku

doi:10.2514/6.2020-0249

Cited by 3 publications

(3 citation statements)

References 19 publications

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“…[6][7][8][9][10][11] Sandwich composite structures are one of the most popular materials used in engineering applications such as transportation, marine industries, aerospace and aircraft industries, wind turbine industries, and so on due to their suitable physical properties and efficiency in supporting transverse loads. [12][13][14][15] To that end, the design and structural analysis of sandwich panels was done by Allen [16] and the results provided a classical theoretical analysis method that greatly increases the application of sandwich structures. Composite structures are sensitive to external localized loads such as low-velocity impact and the introduction of improper loads that are normal to face sheets.…”

Section: Introductionmentioning

confidence: 99%

Effect of graphene nanoparticles on the strength of sandwich structure inspired by dragonfly wings under low‐velocity impact

et al. 2021

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Dragonfly's wings are highly specialized flying organs that are well adapted to the flying behavior of each dragonfly, mainly consisting of veins and membrane. The effect of graphene nanoparticles on a novel foam-based sandwich panel structure inspired by microstructural features of dragonfly wings has been investigated under low-velocity impact. Composite and nanocomposite sandwich veins are made of E-glass/epoxy layers, in which different percentages of graphene nanoparticles are combined with its resin. Polyurethane foam was also used for its core. According to the performance of the samples made after testing and cutting the samples in transverse and longitudinal directions, the internal structure of the vein was examined. Sandwich panels with this type of structure under impact can prevent damage propagation in the vein.The sandwich structure with 0.3% nano indicated more stable behavior in energy absorption and impact resistance than other samples.

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Section: Introductionmentioning

confidence: 99%

Effect of graphene nanoparticles on the strength of sandwich structure inspired by dragonfly wings under low‐velocity impact

et al. 2021

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“…However, the proposed damage model is implemented for the out-of-plane shear load case only. A recent study on the thermomechanical properties of composite sandwich panels emphasizes the need of a progressive damage model to quantify the various failure modes [ 41 ]. A comprehensive review on the equivalent model approaches is provided by Aborehab et al [ 42 ].…”

Section: Introductionmentioning

confidence: 99%

Representative Cell Analysis for Damage-Based Failure Model of Polymer Hexagonal Honeycomb Structure under the Out-of-Plane Loadings

et al. 2020

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The honeycomb (HC) core of sandwich structures undergoes flexural loading and carries the normal compression and shear. The mechanical properties and deformation response of the core need to be established for the design requirements. In this respect, this article describes the development of the smallest possible representative cell (RC) models for quantifying the deformation and failure process of the Nomex polymer-based hexagonal HC core structure under the out-of-plane quasi-static loadings. While the hexagonal single and multi-cell models are suitable for the tension and compression, a six-cell model is the simplest RC model developed for shear in the transverse and ribbon direction. Hashin’s matrix and fiber damage equations are employed in simulating the failure process of the orthotropic cell walls, using the finite element (FE) analysis. The FE-calculated load–displacement curves are validated with the comparable measured responses throughout the loading to failure. The location of the fracture plane of the critical cell wall in the out-of-plane tension case is well predicted. The wrinkling of the cell walls, leading to the structural buckling of the HC core specimen in the compression test, compares well with the observed failure mechanisms. In addition, the observed localized buckling of the cell wall by the induced compressive stress during the out-of-plane shear in both the transverse and ribbon direction is explained. The mesoscale RC models of the polymer hexagonal HC core structure have adequately demonstrated the ability to predict the mechanics of deformation and the mechanisms of failure.

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“…The fatigue damage caused by temperature gradient is mainly considered for the possible failure of engine in operation. For the above two kinds of stress-strain problems, the finite element method is usually used to calculate [4]- [6]. It can be seen that the finite element modeling of key components and the rapid solution of corresponding statics equations are the focus of the aircraft health management system.…”

Section: Introductionmentioning

confidence: 99%

Strength Check of Aircraft Parts Based on Multi-GPU Clusters for Fast Calculation of Sparse Linear Equations

Zhang

Hu²

2020

IEEE Access

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In order to improve the cost-effectiveness ratio, the next-generation vehicle needs to meet the requirements of reuse, while adopting a lighter structural weight, so it is necessary to realize the strength calculation and condition monitoring of key components in the digital twin. Most of the current monitoring methods are based on the characteristics of various data acquisition systems, but they need the support of a large number of flight data. The disadvantages of the above strategy can be avoided by reducing the structure of aircraft components to a finite element model and quickly checking the key components in the health management system. In order to solve the problem of fast calculation of the finite element model of the key components of the aircraft, a parallel algorithm and framework of large-scale sparse matrix preprocessing conjugate gradient method based on CUDA(Compute Unified Device Architecture) technology is proposed in the multi GPU(Graphics Processing Unit) workstation cluster environment. Once the sparse matrix is too large to be processed in a single workstation, this paper discusses how to realize the optimized data segmentation in the distributed multi-GPU computing environment. For the problem of iterative solution of matrix preprocessing, two preprocessing strategies of matrix bandwidth reduction parallelization and incomplete Cholesky decomposition are proposed, and asynchronous task concurrency and load balancing strategies are designed on the architecture. The calculation of some examples in the standard sparse matrix database shows that the algorithm and architecture proposed in this paper have the ability to solve large-scale sparse matrix quickly and efficiently, and can complete the fast strength verification of vehicle components.

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Finite element based damage and failure analysis of honeycomb core sandwich composite structures for space applications

Cited by 3 publications

References 19 publications

Effect of graphene nanoparticles on the strength of sandwich structure inspired by dragonfly wings under low‐velocity impact

Effect of graphene nanoparticles on the strength of sandwich structure inspired by dragonfly wings under low‐velocity impact

Representative Cell Analysis for Damage-Based Failure Model of Polymer Hexagonal Honeycomb Structure under the Out-of-Plane Loadings

Strength Check of Aircraft Parts Based on Multi-GPU Clusters for Fast Calculation of Sparse Linear Equations

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