Studies on large deflection of geometrically nonlinear corrugated structures

Kumar, Deepak; Ali, Shaikh Faruque; Arockiarajan, A.

doi:10.1007/s00707-020-02861-x

Cited by 8 publications

(10 citation statements)

References 32 publications

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“…The angle between the tangent of the free end and the positive direction of the x-axis is θ 0 . According to the literature [25,39,40], the equation of arc beam deformation without inflection point can be obtained as follows:…”

Section: Nonlinear Modelmentioning

confidence: 99%

“…The analytical models of these auxetic structures were mainly explored based on classical Euler-Bernoulli beam bending theory to predict the linear elastic properties. Moreover, these structures would experience large deformations if used in engineering due to the insufficient predictions of linear models [25][26][27][28]. Tather et al [29] created a linear and nonlinear model of a hybrid reentrant and circular wall combined composite unit to achieve negative Poisson's ratio (NPR) and improved stiffness.…”

Section: Introductionmentioning

confidence: 99%

“…Theoretical solutions of large deflections of cantilevered straight beams have been successfully applied in solving compliant mechanism deformation [34]. Kumar et al developed a chain algorithm to predict the geometrically large deflection of corrugated structures [25]. Geometrical nonlinear of single beams are gradually expanded to auxetic metamaterials, such as vertical strut combined re-entrant structure and double-V structures [19,28,29].…”

Section: Introductionmentioning

confidence: 99%

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In-plane elastic property prediction of straight-arc coupled auxetic structures

Zhang

Hao

et al. 2023

J. Phys. D: Appl. Phys.

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Auxetic metamaterials with two component exhibit widely potential engineering applications due to their exotic mechanical properties. In this work, a novel straight-arc coupled structure (SACS) is designed by introducing a circular arc structure to a classical re-entrant structure. This work aims to explore the linear and geometrical nonlinear mechanical of SACS at large strains. According to the Castigliano’s second theorem, the in-plane linear theoretical model is established to obtain equivalent Poisson's ratio and elastic modulus. A geometrical nonlinear model is further established based on large deflection theory and chain algorithm. The finite element method is used to verify the prediction of the theoretical solution, and linear and nonlinear mechanical properties of the SACS are studied by numerical simulation. The influence of geometric parameters re-entrant angle and arc radius on the mechanical properties of the SACS is investigated to compare the linear and nonlinear mechanical properties. The linear numerical simulation of straight-arc coupled structure with two transverse ribs (SACS-TR) and classical re-entrant honeycomb structure with two transverse ribs (CRS-TR) with the same dimension is carried out to analyze the in-plane elastic properties. These results demonstrate that considering the geometric nonlinear can predict the actual structural deformation more accurately, which is verified by the quasi-static compression experiment results at large strains. The straight-arc coupled structure design can enhance the auxetic effect and structure Young’s moduli under same dimension.

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Section: Nonlinear Modelmentioning

confidence: 99%

Section: Introductionmentioning

confidence: 99%

Section: Introductionmentioning

confidence: 99%

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In-plane elastic property prediction of straight-arc coupled auxetic structures

Zhang

Hao

et al. 2023

J. Phys. D: Appl. Phys.

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“…3(a) is split into several straight (Oa 1 , a 2 a 3 , ..., a 34 a 35 ) and semicircular beams (a 1 a 2 , a 3 a 4 , ..., a 33 a 34 ). These beams are considered to be cantilever beams fixed to the end of the previous beam like chain links [23]. The equivalent loads are calculated using static equilibrium for each beam (Fig.…”

Section: Deflections Of the Single Corrugated Structure Due To End Lo...mentioning

confidence: 99%

“…A corrugated structure composed of a wavy plate [20] is a promising candidate for variable-camber morphing wings. Research pertaining to analysis of corrugated structures over recent years has produced results that favour their use for morphing applications [21][22][23]. Corrugated structures have small stiffness along the axial direction, thereby allowing suitable axial deformations under low actuation loads.…”

Section: Introductionmentioning

confidence: 99%

Aerodynamic study of single corrugated variable-camber morphing aerofoil concept

et al. 2021

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Camber morphing is an effective way to control the lift generated by any aerofoil and potentially improve the range (as measured by the lift-to-drag ratio) and endurance (as measured by $C_l^{3/2}/C_d$ ). This can be especially useful for fixed-wing Unmanned Aerial Vehicles (UAVs) undergoing different flying manoeuvres and flight phases. This work investigates the aerodynamic characteristics of the NACA0012 aerofoil morphed using a Single Corrugated Variable-Camber (SCVC) morphing approach. Structural analysis and morphed shapes are obtained based on small-deformation beam theory using chain calculations and validated using finite-element software. The aerofoil is then reconstructed from the camber line using a Radial Basis Function (RBF)-based interpolation method (J.H.S. Fincham and M.I. Friswell, “Aerodynamic optimisation of a camber morphing aerofoil,” Aerosp. Sci. Technol., 2015). The aerodynamic analysis is done by employing two different finite-volume solvers (OpenFOAM and ANSYS-Fluent) and a panel method code (XFoil). Results reveal that the aerodynamic coefficients predicted by the two finite-volume solvers using a fully turbulent flow assumption are similar but differ from those predicted by XFoil. The aerodynamic efficiency and endurance factor of morphed aerofoils indicate that morphing is beneficial at moderate to high lift requirements. Further, the optimal morphing angle increases with an increase in the required lift. Finally, it is observed for a fixed angle-of-attack that an optimum morphing angle exists for which the aerodynamic efficiency becomes maximum.

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