Experimental and numerical studies on the buckling and post-buckling behavior of single blade-stiffened CFRP panels

Kolanu, Naresh Reddy; Raju, Gangadharan; Ramji, M.

doi:10.1016/j.compstruct.2018.05.015

Cited by 56 publications

(16 citation statements)

References 28 publications

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“…Generally, the total response would be given by superimposing infinite terms of modes associated with a scale factor, although the lowest modes are frequently more critical. Experimental evidence on the buckling behavior of similar structures (Kolanu et al, 2018; Zou and Bisagni, 2018) showed that the first buckling eigenmode mainly dominate the macroscopic response. Thus, the first buckling mode shape was introduced and a scale factor equal to 5% of the skin’s thickness was used.…”

Section: Numerical Modelingmentioning

confidence: 99%

Strain-based health indicators for the structural health monitoring of stiffened composite panels

Milanoski

Λούτας

2020

Journal of Intelligent Material Systems and Structures

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A common defect of composite-stiffened structures is the disbond at the interface between the two constituents (skin/stringer), as a result of inefficient manufacturing process or foreign object impacts in service. Generally, discontinuities within the volume of an elastic solid medium, subjected to mechanical load, cause anomalies on the strain field in the near vicinity of the discontinuity. Utilizing this observation, this work investigates the effect of artificially induced disbonds in the skin/stiffener interface of an aeronautical-grade generic element. A structural health monitoring methodology is developed, leveraging on numerically simulated strains along the stringer foot which aims to assess the health state of the panel as the size of the disbonds increases. The study is implemented using a parametric finite element model generating various disbond scenarios. Longitudinal strain values are acquired at the exact points where in reality actual fiber Bragg grating sensors will be located. Two types of commonly utilized strain-based health indicators are evaluated, and their drawbacks are revealed and discussed. A new health indicator is proposed that proves its capability to monitor growing disbonds while being both load- and baseline-independent.

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Section: Numerical Modelingmentioning

confidence: 99%

Strain-based health indicators for the structural health monitoring of stiffened composite panels

Milanoski

Λούτας

2020

Journal of Intelligent Material Systems and Structures

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“…Besides, the damage index, defined based on the recorded guided waves, was sensitive to the enlargement of the debonding area. Kolanu et al 32 investigated the failure of a CFRP-stiffened panel subjected to the compression loading using AE, DIC, infrared thermography, and strain gauges. DIC captured the strain distributions during the buckling and post-buckling, while strain gauges could precisely detect the onset of buckling.…”

Section: Introductionmentioning

confidence: 99%

Damage assessment of a titanium skin adhesively bonded to carbon fiber–reinforced plastic omega stringers using acoustic emission

Saeedifar

Saleh

Nijhuis³

et al. 2021

Structural Health Monitoring

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This study is devoted to the use of acoustic emission technique for a comprehensive damage assessment, that is, damage detection, localization, and classification, of an aeronautical metal-to-composite bonded panel. The structure comprised a titanium panel adhesively bonded to carbon fiber–reinforced plastic omega stringers. The panel contained a small initial artificial debonding between the titanium panel and one of the carbon fiber–reinforced plastic stringers. The panel was subjected to a cyclic increasing in-plane compression load, including loading, unloading, and then reloading to a higher load level, until the final fracture. The generated acoustic emission signals were captured by the acoustic emission sensors, and digital image correlation was also used to obtain the strain field on the surface of the panel during the test. The results showed that acoustic emission can accurately detect the damage onset, localize it, and also trace its evolution. The acoustic emission results not only were consistent with the digital image correlation results, but also managed to detect the damage initiation earlier than digital image correlation. Finally, the acoustic emission signals were clustered using particle swarm optimization method to identify the different damage mechanisms. The results of this study demonstrate the capability of acoustic emission for the comprehensive damage characterization of aeronautical bi-material adhesively bonded structures.

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“…Carbon fiber-reinforced polymer (CFRP)-stiffened composite plates subjected to axial compression load was studied by Ishikawa et al [ 1 ], Stevens et al [ 2 ], Chiarelli et al [ 3 ], Kong et al [ 4 ], Falzon and Hitchings [ 5 ], Meeks et al [ 6 ], Mo et al [ 7 ], Zhu et al [ 8 ], Feng et al [ 9 ], Kolanu et al [ 10 ], Massod et al [ 11 ] and Tan et al [ 12 ]. Glass fiber-reinforced polymer (GFRP)-stiffened composite plates subjected axial compression load was studied by Roberts et al [ 13 ] and Kolanu et al [ 14 ].…”

Section: Introductionmentioning

confidence: 99%

GFRP Stiffened Plate with Square Cutout under Axial and Out-of-Plane Load

Sirajudeen

Alagusundaramoorthy

2021

Polymers

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The high-strength-to-weight ratio and corrosion resistance properties of glass-fiber-reinforced polymer (GFRP) composites makes them potentially well-suited for application in ship structures, bridges and off-shore oil platforms. These structures are often formed by stiffened plates and are subjected to axial load and out-of-plane load. Cutouts and openings are provided in the plates for access and maintenance. The main objective of this study was to examine the buckling behavior of GFRP-stiffened composite plates with square cutouts under a combination of axial and out-of-plane load up to failure. Four blade-stiffened composite plates without a cutout and four with square cutout were fabricated with stiffeners as a continuous layup of the flange plate using glass fiber and epoxy resin. The initial geometric imperfections were measured, and plate imperfections (Δx), stiffener imperfections (Δsy) and overall imperfections (Δsx) were calculated from the measurements. All fabricated-stiffened composite plates were tested up to failure. The finite element model was developed in ANSYS software and validated with the experimental results. It was observed that GFRP-stiffened composite plates failed by stiffener compression/stiffener tension mode of failure. The presence of out-of-plane loads and cutouts reduced the axial load carrying capacity of the stiffened composite plates.

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Experimental and numerical studies on the buckling and post-buckling behavior of single blade-stiffened CFRP panels

Cited by 56 publications

References 28 publications

Strain-based health indicators for the structural health monitoring of stiffened composite panels

Strain-based health indicators for the structural health monitoring of stiffened composite panels

Damage assessment of a titanium skin adhesively bonded to carbon fiber–reinforced plastic omega stringers using acoustic emission

GFRP Stiffened Plate with Square Cutout under Axial and Out-of-Plane Load

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