An Analytically Designed Subcomponent Test to Reproduce the Failure of a Composite Wing Box Beam

Davis, Dena S.; Farley, Gary L.; Ambur, Damodar R.; Davis, Randall C.; Shuart, Mark J.; Wang, John T.; Lotts, C. G.

doi:10.2514/6.1993-1344

Cited by 5 publications

(3 citation statements)

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“…The conventional engineering approach tends to result in over-sizing composite components to ensure buckling resistance, leading to heavier structures. Foundational works by Budiansky [4] and Dickson et al [5] contribute theoretical principles and practical design methodologies, respectively, to enhance the reliability and efficiency of aerospace structures.…”

Section: Discussionmentioning

confidence: 99%

“…The study contributes valuable empirical data, shedding light on the behavior of specific composite structures subjected to compressive loads. Davis [4] conducts a detailed analysis and test correlation of a stiffened composite wing pane. The paper bridges theoretical simulations with practical tests, validating numerical methodologies against real-world scenarios and contributing to the accuracy of post-buckling simulations.…”

Section: Introductionmentioning

confidence: 99%

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Virtual Full Scale Static Test of a Civil Tilt Rotor Composite Wing in Non-Linear Regime

Chiariello,

Perillo,

Linari

et al. 2024

Aerospace

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This study addresses the crucial role of post-buckling behavior analysis in the structural design of composite aeronautical structures. Traditional engineering practices tend to result in oversized composite components, increasing structural weight. EASA AMC 20-29’s Building Block Approach suggests phased testing, but its time and cost challenges necessitate a shift to high-fidelity post-buckling analyses, exemplified by MSC NASTRAN SOL 400. This approach, showcased in the analysis of the Next Generation Civil Tilt Rotor Technology Demonstrator’s wing (NGTCTR-TD), effectively de-risks static tests, contributing to a more efficient certification process. The study demonstrates how advanced simulations provide detailed insights into local buckling phenomena, allowing precise stress distribution analysis. These analyses eliminate the risk of structural failure, paving the way for safer, more efficient, and cost-effective airframe structures. Future developments aim to validate numerical analyses with experimental data, further emphasizing the reliability and benefits of high-fidelity simulations.

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Section: Discussionmentioning

confidence: 99%

Section: Introductionmentioning

confidence: 99%

Virtual Full Scale Static Test of a Civil Tilt Rotor Composite Wing in Non-Linear Regime

Chiariello,

Perillo,

Linari

et al. 2024

Aerospace

View full text Add to dashboard Cite

show abstract

“…Such discontinuity can lead to load and stress re-distributions of the panel. In advanced composites technology (ACT) work of NASA, it is reported that failure of stiffener runout at composite C130 wing box section is most critical [14,15]. Faggiani and Falzon [16] demonstrated the failure mode of stiffened aerostructures with stiffener runs out using finite element analysis (FEA).…”

Section: Introductionmentioning

confidence: 99%

CNT Reinforced Laminated Composite under In-Plane Tensile Loading: A Finite Element Study

Bhowmik

Akhtar

Kalshyan

et al. 2020

MSF

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The present study is mainly aimed at investigating the distribution of in-plane stresses of a rectangular plate under localized uniform in-plane tensile loading through finite element analysis. The configuration used in the analysis is analogous to the case of premature failure of stiffened panel due to the termination of a stiffener in aircraft wing structure. In this current work, three different types of materials namely, isotropic, plain woven and transversely isotropic materials are being considered. Aluminium is taken as isotropic; high strength carbon/epoxy is being assigned as plain woven composite and carbon nanotube based hybrid composite is used as transversely isotropic material, due to their wide range of applications in aircraft structures. The effect of different materials on overall axial, transverse and shear stress distributions at different layers of the stiffened composite panels are demonstrated using finite element analyses. Further, the variations of these stresses along axial and transverse directions are also compared for different materials. It can be concluded from the present study that the peak stress developed near the load application zone should be incorporated in the design criteria of such plates to avoid failure.

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Numerical Analysis of Stiffener Runout Sections

Faggiani

Falzon

2007

Appl Compos Mater

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The recent trend of incorporating more composite material in primary aircraft structures has highlighted the vulnerability of stiffened aerostructures to through-thickness stresses, which may lead to delamination and debonding at the skin-stiffener interface, leading to collapse. Stiffener runout regions are particularly susceptible to this problem and cannot be avoided due to the necessity to terminate stiffeners at rib intersections or at cutouts, interrupting the stiffener load path. In this paper, experimental tests relating to two different stiffener runout specimens are presented and the failure modes of both specimens are discussed in detail. A thinner-skinned specimen showed sudden and unstable crack propagation, while a thicker-skinned specimen showed initially unstable but subsequent stable crack growth. Detailed finite element models of the two specimens are developed, and it is shown how such models can explain and predict the behaviour and failure mode of stiffener runouts. The models contain continuum shell elements to model the skin and stiffener, while cohesive elements using a traction-separation law are placed at the skinstiffener interface to effectively model the debonding which promotes structural failure.

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An Analytically Designed Subcomponent Test to Reproduce the Failure of a Composite Wing Box Beam

Cited by 5 publications

References 0 publications

Virtual Full Scale Static Test of a Civil Tilt Rotor Composite Wing in Non-Linear Regime

Virtual Full Scale Static Test of a Civil Tilt Rotor Composite Wing in Non-Linear Regime

CNT Reinforced Laminated Composite under In-Plane Tensile Loading: A Finite Element Study

Numerical Analysis of Stiffener Runout Sections

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