Buckling of the composite anisogrid lattice plate with clamped edges under shear load

Лопатин, А.В.; Морозов, Е.В.; Shatov, A.V.

doi:10.1016/j.compstruct.2016.09.025

Cited by 17 publications

(3 citation statements)

References 20 publications

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“…Recently, papers emerge for the case of anisogrid plates and panels. Totaro [21] in 2015 discussed anisogrid panels under compression, while Lovatin, Morozof, and Shatov [22] discussed box plate under shear loads. Niemann, Wagner, and Huhne [23] developed it further by manufacturing and did numerical analysis and experimentation of compressed anisogrid panels.…”

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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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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show abstract

“…The works [6][7] are devoted to the design of load-bearing panels considering the solution of optimal reinforcement problems. The solutions of problems of composite panels stability under shear are given in works [8][9]. Note that analytical solutions of stability and geometrically nonlinear problems can be used when considering the behaviour of defects of the splitting type.…”

Section: Introductionmentioning

confidence: 99%

Stability and post-buckling state of square composite walls of anisotropic structure spars under shear

Mitrofanov

Lebedevs

Turko

2021

20th International Scientific Conference Engineering for Rural Development Proceedings

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As an object of the research, a square fragment of the wall of the spar of the low-or medium-capacity airplane wing caisson structure is considered. When designing thin spar walls, it is advisable to use anisotropic panels with different values of critical shear stresses depending on the direction of the action of the shear forces in different design cases of loading. The paper assumes that the shape of the panel is close to square, the deflection function is described by trigonometric functions, includes two terms and satisfies the boundary conditions for hinged support. The Bubnov-Galerkin method is used to solve a geometrically nonlinear problem for a square anisotropic panel under shear loading. The presented solution of the geometrically nonlinear problem is reduced to a nonlinear system of two equations with respect to two deflection amplitudes. From the definition of the Erie stress function, analytical expressions for the membrane stresses arising from the loss of panel stability are written down in the paper. When considering a linear problem, an analytical expression for determining the critical flows at the loss of stability of square anisotropic panels is obtained. The above expression for a given tangential flux and stacking allows us to carry out the design calculation and determine the minimum thickness of an anisotropic panel. On the basis of the presented analytical expression, examples of calculations of shear stability of smooth square anisotropic panels are given and the possible effectiveness of anisotropic structures as compared to orthotropic panels is shown when considering two design cases under the action of shear forces that differ in direction and absolute values.

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“…Junyi and Balint (2016) added dispersion properties to monitored variables. Lopatin et al (2017) studied both the intensive (cell structure) and extensive (plate dimensions) parameters in search for the maximum critical buckling load.…”

Section: Lattice Materials Properties and Range Of Potential Applicationsmentioning

confidence: 99%

Old materials - new capabilities: lattice materials in structural mechanics

Augustyniak

2018

jtam

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Lattice materials (LM) are a novel concept stemming from the combination of crystallography and structural optimisation algorithms. Their practical applications have become real with the advent of versatile additive layer manufacturing (ALM) techniques and the development of dedicated CAD/CAE tools. This work critically reviews one of the major claims concerning LMs, namely their excellent stiffness-to-weight performance. First, a brief literature review of spatially uniform LMs is presented, focusing on specific strength of standard engineering materials as compared with novel structures. An original modelling and optimisation is carried out on a flat panel subject to combined shear and bending load. The calculated generalised specific stiffness is compared against reference values obtained for a uniform panel and the panel subjected to topological optimisation. The monomaterial, a spatially repetitive solution turns out to be poorly suited for stiff, lightweight designs, because of suboptimal material distribution. Spatially non-uniform and locally size-optimised structures perform better. However, its advantage over manufacturable, topologically-optimised conventional designs can at best be marginal (< 10%). Cubic-cell lattices cannot replace conventional bulk materials in the typical engineering use. The multi-cell-type and multi--material lattice structures, albeit beyond the scope of this article, are more promising from the point of view of mechanical properties. The possibility of approaching the linear scaling reported in the recent litterature can make them an attractive option in ultra-low weight designs.

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Buckling of the composite anisogrid lattice plate with clamped edges under shear load

Cited by 17 publications

References 20 publications

Development of Anisogrid Lattice Composite Structures for Fighter Wing Applications

Development of Anisogrid Lattice Composite Structures for Fighter Wing Applications

Stability and post-buckling state of square composite walls of anisotropic structure spars under shear

Old materials - new capabilities: lattice materials in structural mechanics

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