Homogenization of Plates with Microstructure and Application to Corrugated Core Sandwich Panels

Sharma, Anurag; Sankar, Bhavani V.; Haftka, Raphael T.

doi:10.2514/6.2010-2706

Cited by 19 publications

(22 citation statements)

References 4 publications

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“…The last example is to model a corrugated-core sandwich panel, a concept used for Integrated Thermal Protection System (ITPS) studied in Sharma et al (2010). The ITPS panel along with the details of the unit cell is sketched in Fig.…”

Section: Integrated Thermal Protection Systemmentioning

confidence: 99%

Homogenization and dimensional reduction of composite plates with in-plane heterogeneity

Lee

2011

International Journal of Solids and Structures

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a b s t r a c tThe variational asymptotic method is used to construct a new model for composite plates which could have in-plane heterogeneity due to both geometry and material. We first formulate the original threedimensional problem in an intrinsic form which is suitable for geometrically nonlinear analysis. Taking advantage of smallness of the plate thickness and heterogeneity, we use the variational asymptotic method to rigorously construct an effective plate model unifying a homogenization process and a dimensional reduction process. This approach is implemented in the computer code VAPAS using the finite element technique for the purpose of dealing with realistic heterogeneous plates. A few examples are used to demonstrate the capability of this new model.

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Section: Integrated Thermal Protection Systemmentioning

confidence: 99%

Homogenization and dimensional reduction of composite plates with in-plane heterogeneity

Lee

2011

International Journal of Solids and Structures

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“…As expected, we found out that the maximum deflection using the refined plate theory is only 4.77% off the direct 3D FEA analysis. We digress here to point out that the present approach is different from the approach in [29] mainly in the following two aspects. First, to obtain the effective classical plate stiffnesses, [29] needs to carry out six analyses of a 3D unit cell under six different sets of boundary conditions and loading conditions and postprocess the 3D stresses to compute the plate resultants.…”

Section: Integrated Thermal Protection Systemmentioning

confidence: 99%

“…Both materials are isotropic with E 1 = 109.36 GPa, ν 1 = 0.3, E 2 = 209.482 GPa, ν 2 = 0.063. Although a 3D UC is needed for the study in [29], only a 2D UC is needed for the present approach as it is uniform along one of the in-plane directions. The effective classical plate stiffnesses obtained in our previous work [21] have an excellent agreement with those obtained [29] with the largest difference (around 1%) appearing for the extension-bending coupling stiffness (ā 14 ).…”

Section: Integrated Thermal Protection Systemmentioning

confidence: 99%

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Refined modeling of composite plates with in‐plane heterogeneity

Lee¹,

Yu²,

Hodges³

2013

Z Angew Math Mech

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This article is concerned with the mechanical behavior of heterogeneous composite plates with elastic moduli and layered geometries varying through the thickness direction and periodically along the in-plane directions. By using the concept of decomposition of the rotation tensor, we first formulate the three-dimensional elastic problem in an intrinsic form for application to the geometrically nonlinear problem. The variational asymptotic method is then exercised, leading to simultaneous homogenization and dimensional reduction to construct an effective and simple model suitable for plates with in-plane periodicity. In particular, having obtained the refinement terms up to the second order, we develop a refined plate model, namely a generalized Reissner-Mindlin model that is capable of capturing the transverse shear deformations. In order to deal with realistic and complex plate geometries and constituent materials efficiently and conveniently, the proposed model is implemented into a single unified formulation suitable for incorporation into a commercial analysis package. Numerical results computed herein for a few examples are compared to similar results available in the literature to demonstrate the application and performance of the present model.

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“…Fluted-core and similar designs, such as corrugated-core, are not new and have been explored previously through experiment and analysis. [3][4][5][6][7][8][9] Fluted-and corrugated-core structures have also been proposed and/or used on a limited number of aerospace structures. [10][11][12][13] However, a better understanding of the behavior and failure mechanisms of different fluted-corecomposite designs and construction methods is needed if they are to be incorporated into a wider variety of large weight-critical applications.…”

Section: Introductionmentioning

confidence: 99%

Compression Behavior of Fluted-Core Composite Panels

Schultz

Oremont

Guzman

et al. 2011

52nd AIAA/ASME/ASCE/AHS/ASC Structures, Structural Dynamics and Materials Conference

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In recent years, fiber-reinforced composites have become more accepted for aerospace applications. Specifically, during NASA's recent efforts to develop new launch vehicles, composite materials were considered and baselined for a number of structures. Because of mass and stiffness requirements, sandwich composites are often selected for many applications. However, there are a number of manufacturing and in-service concerns associated with traditional honeycomb-core sandwich composites that in certain instances may be alleviated through the use of other core materials or construction methods. Flutedcore, which consists of integral angled web members with structural radius fillers spaced between laminate face sheets, is one such construction alternative and is considered herein. Two different fluted-core designs were considered: a subscale design and a full-scale design sized for a heavy-lift-launch-vehicle interstage. In particular, axial compression of flutedcore composites was evaluated with experiments and finite-element analyses (FEA); axial compression is the primary loading condition in dry launch-vehicle barrel sections. Detailed finite-element models were developed to represent all components of the fluted-core construction, and geometrically nonlinear analyses were conducted to predict both buckling and material failures. Good agreement was obtained between test data and analyses, for both local buckling and ultimate material failure. Though the local buckling events are not catastrophic, the resulting deformations contribute to material failures. Consequently, an important observation is that the material failure loads and modes would not be captured by either linear analyses or nonlinear smeared-shell analyses. Compression-after-impact (CAI) performance of fluted-core composites was also investigated by experimentally testing samples impacted with 6 ft.-lb. impact energies. It was found that such impacts reduced the ultimate load carrying capability by approximately 40% on the subscale test articles and by less than 20% on the full-scale test articles. Nondestructive inspection of the damage zones indicated that the detectable damage was limited to no more than one flute on either side of any given impact. More study is needed, but this may indicate that an inherent damagearrest capability of fluted core could provide benefits over traditional sandwich designs in certain weight-critical applications.

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Homogenization of Plates with Microstructure and Application to Corrugated Core Sandwich Panels

Cited by 19 publications

References 4 publications

Homogenization and dimensional reduction of composite plates with in-plane heterogeneity

Homogenization and dimensional reduction of composite plates with in-plane heterogeneity

Refined modeling of composite plates with in‐plane heterogeneity

Compression Behavior of Fluted-Core Composite Panels

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