On the buckling resistance of grid-stiffened composite conical shells under compression

Zarei, Masoumeh; Rahimi, Gholam Hossein; Hemmatnezhad, M.

doi:10.1016/j.engstruct.2021.112213

Cited by 32 publications

(4 citation statements)

References 42 publications

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“…5,6 However, rare investigations have been carried out about the buckling behavior of composite lattice conical shells with helical stiffeners. [7][8][9] A full literature review of recent works on the free vibrational and buckling behavior of stiffened conical shells have been given in a series of papers by Zarei et al [10][11][12] and will not be repeated here, and the literature review will be hereafter focused on the application of the VCT for these structures.…”

Section: Remarks and Motivations Of The Researchmentioning

confidence: 99%

A nondestructive approach to predict buckling load of composite lattice-core sandwich conical shells based on vibration correlation technique

Zarei

Rahimi

2022

Jnl of Sandwich Structures & Materials

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In this paper the vibration correlation technique (VCT) has been used as a nondestructive method for predicting the buckling load of the composite lattice-core sandwich conical shells. This technique is capable of predicting the buckling load of different structures without reaching the failure point through modal testing. The composite lattice-core sandwich conical shell has been fabricated using a filament winding process. To perform the expriment, the fundamental natural frequency of the specimen is measured under stepped axial compression loading. The procedure is followed up without actually reaching the instability point when the structure collapses and is no longer usable. A finite element model has also been built in ABAQUS in order to determine the correlation between natural frequency and applied compressive load. A comparison of the results indicated that the VCT has provided a reliable estimate of the buckling load of composite lattice-core sandwich conical shells, especially when the structure is loaded up to at least 66% of the experimental buckling load and accuracy of the VCT decreases when the maximum load is lower than 43% of the buckling load. Results also revealed that the linear fitted curve is unsuitable for the correlation between frequency of vibration and applied load in order to predict buckling load.

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Section: Remarks and Motivations Of The Researchmentioning

confidence: 99%

A nondestructive approach to predict buckling load of composite lattice-core sandwich conical shells based on vibration correlation technique

Zarei

Rahimi

2022

Jnl of Sandwich Structures & Materials

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“…Therefore, buckling and vibration of anisogrid cylindrical and conical shells were the main research studies of most of researchers. Several cases and techniques had been published on the area of buckling of anisogrid shell and conical structures [5][6][7][8][9][10][11], including both numerical and experimental analyses. Several buckling modes on cylindrical structures were produced, giving important and interesting results.…”

Section: Introductionmentioning

confidence: 99%

Development of Anisogrid Lattice Composite Structures for Fighter Wing Applications

Kusni,

Hadi,

Gunawan

et al. 2024

International Journal of Aerospace Engineering

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This paper presents research on the use of anisogrid lattice structures in fighter wing applications. While the anisogrid lattice structure has been widely used in spacecraft structures, its implementation in main aircraft structures is still limited. The study is aimed at investigating the feasibility of utilizing an anisogrid lattice structure in fighter wing design. The analysis and optimization focus on determining the optimal weight of the composite wing structure, considering static, buckling, and flutter failure constraints. Various lift distributions, including triangular, Schrenk, and constant, are applied to evaluate the structure’s response to static failure caused by aerodynamic loads. The anisogrid structure design incorporates inclined lattice elements between ribs and spars, with spar arrangement in the wing box featuring an anisogrid configuration. The anisogrid lattice structure is expected to produce higher bending and torsional stiffness compared to conventional orthogonal structures, producing better flutter and buckling characteristics. The optimized wing structure successfully meets static, buckling, and flutter load requirements at speeds below 500 m/s. The study showcases triangular, Schrenk, and constant load distributions resulting in half-wing masses of 504, 571, and 707 kg, respectively. The results show that flutter and buckling loads are no longer the critical loads in wing structural design but static load.

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“…Although there are many published papers regard with stiffened FGM conical shells, rare investigations have been carried out about the stiffened composite conical shells. 31 Totaro 32 formulated a mathematical model to compute equivalent stiffness of the composite lattice conical shells. Morozov et al 33 studied buckling analysis of the composite lattice conical shells.…”

Section: Introductionmentioning

confidence: 99%

External pressure buckling of composite sandwich conical shells with variable skin thickness

Zarei

Rahimi

2022

Proceedings of the Institution of Mechanical Engineers, Part G:

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In this paper, an analytical model is developed to investigate the buckling analysis of the composite sandwich conical shell with variable skin thickness under lateral pressure loading. This problem involves composite shells, which are produced during the filament-winding process, where the skin thickness varies through the length of the shell. An effective smeared method is employed to reduce the reinforced lattice core into a layer. This is done by analyzing forces and moments on a unit cell. Therefore, equivalent stiffness parameters of reinforced lattice core are determined. By superimposing stiffness parameters due to the lattice core with those of the inner and outer skins, the equivalent stiffness of the sandwich panel will be obtained. Governing equations are established based on the first shear deformation theory. The power series method is used to extract the buckling load of the stiffened shell. To verify achieved results, a 3D finite element model is provided. Comparisons showed that the analytical solution is qualified enough to study the buckling behavior of the composite sandwich conical shell. Through this study, the effects of a set of important parameters like stiffener orientation angle, number of stiffeners, semi-vertex angle, and skin lamination are investigated.

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On the buckling resistance of grid-stiffened composite conical shells under compression

Cited by 32 publications

References 42 publications

A nondestructive approach to predict buckling load of composite lattice-core sandwich conical shells based on vibration correlation technique

A nondestructive approach to predict buckling load of composite lattice-core sandwich conical shells based on vibration correlation technique

Development of Anisogrid Lattice Composite Structures for Fighter Wing Applications

External pressure buckling of composite sandwich conical shells with variable skin thickness

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