Micromechanical Analysis of Composite Corrugated-Core Sandwich Panels for Integral Thermal Protection Systems

Martínez, Óscar; Sankar, Bhavani V.; Haftka, Raphael T.; Bapanapalli, Satish K.; Blosser, Max L.

doi:10.2514/1.26779

Cited by 83 publications

(32 citation statements)

References 8 publications

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“…The current study extends the work by Martinez et al [20] by considering effects of various geometric parameters on the global bending response of composite sandwich plates with corrugated core. The sandwich plates contain a unidirectional corrugated core with repeated unit cell.…”

Section: Introductionmentioning

confidence: 85%

“…The in-plane extensional-shear and out-of-plane bending-twisting responses of laminated plates with respect to their own mid-planes are governed by the following constitutive relation [20]. …”

Section: Stiffness Matrix For the Face And Web Members Of The Unit Cellmentioning

confidence: 99%

“…Martinez et al [20] were the first authors to develop an equivalent plate model for composite corrugated-core sandwich panels using a micromechanics approach. They idealized the composite corrugated sandwich plate as an equivalent orthotropic thick-plate continuum.…”

Section: Introductionmentioning

confidence: 99%

“…For p = 80 mm, θ min is 45º, but as p is changed from 20 mm to 320 mm, θ min reduces from 75.96º to 14.04º . To maintain a constant cross-sectional area of 478 mm 2 , the web thickness (t c ) is calculated as a function of web inclination angle  using Equation (20). …”

mentioning

confidence: 99%

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Global bending response of composite sandwich plates with corrugated core: Part I: Effect of geometric parameters

Boorle

Mallick

2016

Composite Structures

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Section: Introductionmentioning

confidence: 85%

Section: Stiffness Matrix For the Face And Web Members Of The Unit Cellmentioning

confidence: 99%

Section: Introductionmentioning

confidence: 99%

mentioning

confidence: 99%

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Global bending response of composite sandwich plates with corrugated core: Part I: Effect of geometric parameters

Boorle

Mallick

2016

Composite Structures

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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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An Investigation for Effective Thermal Properties of Titanium Alloy Lattice Sandwich Panels

Li¹,

Yang²

2021

Proceedings of the International Conference on Aerospace System Science and Engineering 2020

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Micromechanical Analysis of Composite Corrugated-Core Sandwich Panels for Integral Thermal Protection Systems

Cited by 83 publications

References 8 publications

Global bending response of composite sandwich plates with corrugated core: Part I: Effect of geometric parameters

Global bending response of composite sandwich plates with corrugated core: Part I: Effect of geometric parameters

Compression Behavior of Fluted-Core Composite Panels

An Investigation for Effective Thermal Properties of Titanium Alloy Lattice Sandwich Panels

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