Buckling behavior of GLARE panels subjected to partial edge loads

Muddappa, P.P. Yathish; Giridhara, G.; Rajanna, T.

doi:10.1016/j.matpr.2020.10.099

Cited by 10 publications

(2 citation statements)

References 14 publications

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“…Muddappa et al made an investigation for the Glare with different thickness and boundary conditions under various loading and stress distribution by applying dynamic approach to determine buckling behavior [10].…”

Section: Introductionmentioning

confidence: 99%

Lateral Buckling of Glare for Aerospace Application

Yeter

2023

Sakarya University Journal of Science

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Glare (Glass Reinforced Aluminium) which consists of fibre metal laminate composite consisting of aluminium and glass is used aerospace structures are supposed to buckling and impact loads. Lateral buckling analyses were made to determine critical buckling loads, and results were compared to Al 2024-T3 in this paper. Weight and load carrying capacity of Glare grades were taken into consideration and the importance of weight to critical load was stated. Numerical works were carried out by starting with Glass and Aluminum then continued for Glare Grades of Glare 2A, Glare 2B, Glare 3A, Glare 3B, Glare 4A, Glare 4B, Glare 5A, Glare 5B, Glare 6A and Glare 6B to estimate buckling load values. Several comparisons were presented for Glare grades based on Al 2024-T3 through paper. Glare 2A, 2B, 3A, 3B, 6A and 6B Grades have lower weight and buckling load values compared to Al 2024-T3. Lower weight is essential for aerospace applications. But optimum weight and load carrying capacity can be selected for intended applications by taking weight and load into consideration at same time. Although Glare grades of 4A 2-1, 4B 2-1, 5A 2-1 and 5B 2-1 having closer weight (17.60g, 17.60g, 19.13g and 19.13g respectively) to Al 2024-T3 (17.31g), higher buckling loads were determined for Glare grades numerically. The best choice for Glare as an alternative to Al 2024-T3 under lateral buckling loading can be decided for point of views of less weight to critical load ratio.

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Section: Introductionmentioning

confidence: 99%

Lateral Buckling of Glare for Aerospace Application

Yeter

2023

Sakarya University Journal of Science

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“…Muddappa et al. 19 studied the buckling behavior of thin GLARE FML plates under the action of partial edge loads using first order shear deformation theory. Using an analytical approach, the influence of nonlinear dynamic response of FGM shells under thermo-electro-mechanical is investigated by.…”

Section: Introductionmentioning

confidence: 99%

Effect of nonlinear edge loads and hybridization of FMLs on buckling performance of interlaminar composites with/without cutouts

Muddappa¹,

Rajanna²,

Giridhara³

2021

Proceedings of the Institution of Mechanical Engineers, Part C:

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The solution for the buckling problems of fibre metal laminates is usually based on the assumptions that the plates are subjected to uniform edges loads without any discontinuity or damages. Nevertheless, in practice the plates are subjected to various kinds of nonlinear/nonuniform edge loads along with various sized and positioned openings. The present work mainly focused on the vibration and buckling performance of inter laminar hybrid fiber metal laminates (HFMLs) with and without cutouts subjected to different kinds of nonlinear loading conditions by utilizing finite element approach. Towards this a 9-noded heterosis plate element has been used to discretize the plate by taking into account the effect of shear deformation and rotary inertia. Since the stress distribution within the plate is highly non-uniform in nature, the dynamic approach has been used to solve the buckling problems. The present study consists of aluminum metal face sheets bonded with four layered symmetric hybrid cross-ply laminates, in which six different hybrid configurations have been considered. The performance of each hybrid configuration along with different sized and positioned cutouts is well investigated under various nonlinear loading conditions.

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