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Abstract

This article investigates the nonlinear stability of composite cylindrical panels (CPs) reinforced by carbon nanotubes (CNTs), resting on elastic foundations and subjected to combined thermomechanical loading conditions. CNTs are embedded into matrix phase through uniform distribution or functionally graded distribution. Material properties of constituents are assumed to be temperature dependent and effective elastic moduli of carbon nanotube–reinforced composite are estimated by the extended rule of mixture. Nonlinear governing equations of geometrically imperfect panels are based on first-order shear deformation theory accounting for elastic foundations and tangential constraint of straight edges. Analytical solutions are assumed to satisfy simply supported boundary conditions and closed-form expressions relating load and deflection are derived through Galerkin method. Numerical examples show the effects of preexisting nondestabilizing loads, distribution patterns, panel curvature, in-plane condition of unloaded edges, thermal environments, initial imperfection, and elastic foundations on the nonlinear stability of nanocomposite CPs under combined loading conditions.

Keywords

CNT-reinforced composite tangential constraint combined loads nonlinear stability cylindrical panel imperfection

Introduction

Cylindrical panel (CP) is structural component widely used in aerospace engineering and civil applications. These panels are frequently exposed to complex loading conditions and their stability is significant problem attracting interest of many researchers. Chang and Librescu¹ and Librescu et al.² carried out studies on the nonlinear stability of laminated composite flat and curved panels under combined loading conditions and indicated that panel curvature, initial geometrical imperfection, and preexisting nondestabilizing loads substantially influence the nonlinear response of CPs. Librescu et al.³ also indicated that tangential constraints of boundary edges and geometrical imperfection have significant and interactive effects on the thermomechanical postbuckling behavior of laminated composite CPs. Panda and coworkers^{4

–13} used nonlinear finite element method to investigate nonlinear bending, vibration, buckling, and postbuckling behaviors of laminated composite flat and curved panels under thermal, mechanical, and thermomechanical loadings. Katariya et al.^14,15 and Panda and Singh^16,17 analyzed the effects of shape memory alloy fibers on the buckling and postbuckling behaviors of laminated sandwich shallow shell structures subjected to mechanical and thermal loads. Nonlinear stability of thin and thick CPs made of ceramic-metal functionally graded (FG) material and subjected to mechanical and thermal loading conditions has been investigated in works^18,19 basing on an analytical approach. Based on finite element approach, Kar and Panda^20
–22 examined the free vibration response, compressive postbuckling, and nonlinear thermomechanical behaviors of FG curved shell panels. Thermal buckling and postbuckling behaviors of shear deformable FG curved shell panels under different temperature conditions have been dealt with by Kar et al.^23,24 making use of a numerical approach.

Due to extraordinary characteristics and extremely large aspect ratio, carbon nanotubes (CNTs) have attracted huge attention of scientists since their appearance in 1991. There is no previous material displaying unprecedentedly excellent mechanical, thermal, and electrical properties as CNTs.^25
–27 CNTs are used as advanced fillers into matrix phase to form carbon nanotube–reinforced composite (CNTRC) having many current and expected applications in various fields.^28,29 Motivated by first work of Shen,³⁰ subsequent works relating to functionally graded carbon nanotube–reinforced composite (FG-CNTRC) structures have been performed. Using finite element method, Mehar and Panda^31,32 and Mehar et al.^33
–35 investigated nonlinear free vibration response and thermoelastic flexural behavior of FG-CNTRC single layer and sandwich curved panels. Based on a numerical approach and the first-order shear deformation theory (FSDT), linear buckling behavior of FG-CNTRC rectangular and skew plates under compressive loads has been investigated in works.^36
–38 Kiani and coworker^39
–41 used Ritz method to deal with linear buckling problem for FG-CNTRC rectangular and skew plates subjected to shear and thermal loads. Postbuckling behavior of FG-CNTRC plates under axial compression has been analyzed by Zhang and Liew⁴² making use of an element-free approach. Using a two-step perturbation technique, Shen and Zhang⁴³ studied the buckling and postbuckling behaviors of higher order shear deformable FG-CNTRC plates under thermal loads. Shen and Zhu⁴⁴ also conducted results for postbuckling analysis of sandwich plates with FG-CNTRC face sheets. Employing Ritz method, Kiani^45,46 examined the postbuckling behaviors of FG-CNTRC plates and sandwich plates with FG-CNTRC face sheets under uniform temperature rise and various boundary conditions.

Linear buckling problem of axially loaded FG-CNTRC CPs with and without piezoelectric layers has been solved in works of Nasihatgozar et al.⁴⁷ and Garcia et al.⁴⁸ utilizing analytical and numerical methods, respectively. Liew et al.⁴⁹ made use of meshless method to analyze postbuckling behavior of axially loaded FG-CNTRC CPs. Based on an asymptotic perturbation technique, Shen and coworker have presented results of postbuckling analysis for thick FG-CNTRC CPs under axial compression, external pressure, thermal load, and combined mechanical loads^50

–53 taking into account effects of elastic foundation and temperature dependence of material properties. Similarly, postbuckling behaviors of FG-CNTRC circular cylindrical shells under axial compression, external pressure, and combined mechanical loads have been treated by Shen^54,55 and Shen and Xiang.⁵⁶ In aforementioned works, edges of plates and shells are assumed to be freely movable under compressive loads or immovable under thermal loads. However, plates and shells are used in conjunction with neighbor structural components and constraints of boundary edges may be elastic. Accordingly, elasticity of constraints of boundary edges should be considered for reasonable predictions. Based on a numerical approach and the FSDT, large deflection and mechanical postbuckling analyses for FG-CNTRC plates with elastically restrained edges have been addressed in works of Zhang et al.^57,58 Based on an analytical approach and classical theory, Tung and coworker have investigated the nonlinear stability of thin FG-CNTRC plates and CPs under thermal and thermomechanical loads^59

–62 taking the effects of tangential constraints of unloaded edges into consideration.

Basing on the FSDT and analytical solutions, this article deals with the nonlinear stability of moderately thick CNTRC CPs with elastically restrained straight edges exposed to thermal environments and subjected to combined action of lateral pressure and axial load. Distribution of CNTs into matrix is uniform or FG and the material properties of constituents are assumed to be temperature dependent. Numerical illustrations show that the behavior trend and load bearing capacity of nanocomposite CPs are sensitively and strongly influenced by tangential constraint of straight edges, preexisting loads, temperature conditions, and initial imperfection.

CNTRC CP resting on an elastic foundation

Consider a composite CP of axial length a, circumferential arc length b, uniform thickness h, and radius of curvature R as shown in Figure 1. The panel is reinforced by single-walled carbon nanotubes (SWCNTs) and rested on a two-parameter elastic foundation represented by Pasternak model. The panel is defined in a coordinate system xyz origin of which is located on the middle plane at a corner, x and y are axial and circumferential directions, respectively, and z is perpendicular to the middle plane with positive direction inward. CNTs are embedded into matrix phase through uniform distribution (UD) or three types of FG distribution named FG-V, FG-Λ, and FG-X and volume fractions of CNTs corresponding to these distribution types are defined as

V_{CNT} (z) = {\begin{matrix} V_{CNT}^{*} (UD) \\ (1 - 2 \frac{z}{h}) V_{CNT}^{*} (FG-V) \\ (1 + 2 \frac{z}{h}) V_{CNT}^{*} (FG- Λ) \\ 2 (2 \frac{| z |}{h}) V_{CNT}^{*} (FG-X) \end{matrix}

where $V_{CNT}^{*}$ has its definition as described in previous works^{30,36

–49} and shape of CNT distribution patterns in CP can be seen in the work.⁶² The present study uses the rule of mixture to estimate the effective Young moduli and shear modulus of CNTRC as³⁰

\begin{array}{l} E_{11} = η_{1} V_{CNT} E_{11}^{CNT} + V_{m} E^{m} \\ \frac{η_{2}}{E_{22}} = \frac{V_{CNT}}{E_{22}^{CNT}} + \frac{V_{m}}{E^{m}} \\ \frac{η_{3}}{G_{12}} = \frac{V_{CNT}}{G_{12}^{CNT}} + \frac{V_{m}}{G^{m}} \end{array}

where $V_{m} = 1 - V_{CNT}$ , and $E_{11}^{CNT}$ , $E_{22}^{CNT}$ , $G_{12}^{CNT}$ and E^m ,G^m are the Young moduli and shear modulus of the CNT and matrix, respectively, whereas η_j ( $j = 1, 2, 3$ ) are the CNT efficiency parameters.

Figure 1.

Configuration and coordinate system of a CP resting on an elastic foundation.

Effective Poisson ratio is assumed to be position and temperature independent and estimated as

ν_{12} = V_{CNT}^{*} ν_{12}^{CNT} + V_{m} ν^{m}

where $ν_{12}^{CNT}$ and ν^m are Poisson ratios of the CNT and matrix, respectively. The thermal expansion coefficients of the CNTRC CP are determined as^50,53

α_{11} = \frac{V_{CNT} E_{11}^{CNT} α_{11}^{CNT} + V_{m} E^{m} α^{m}}{V_{CNT} E_{11}^{CNT} + V_{m} E^{m}}

α_{22} = (1 + ν_{12}^{CNT}) V_{CNT} α_{22}^{CNT} + (1 + ν^{m}) V_{m} α^{m} - ν_{12} α_{11}

where $α_{11}^{CNT}$ , $α_{22}^{CNT}$ , and α^m are thermal expansion coefficients, respectively, of the CNT and isotropic matrix.

Formulations

Although higher order shear deformation theories more accurately predict thick composite structures without shear correction coefficient required, a tremendous effort in formulations is needed for these theories.^{19,21,31,33,50

–56} The FSDT was demonstrated to give good accuracy and reliable prediction for moderately thick composite and nanocomposite structures with less formulation and computation efforts.^{36

–42,45,46,49} In the present study, the FSDT is used to investigate the nonlinear stability of moderately thick CNTRC CPs. Based on the FSDT, strain components are expressed as

(\begin{matrix} ε_{x} \\ ε_{y} \\ γ_{x y} \end{matrix}) = (\begin{matrix} ε_{x}^{0} \\ ε_{y}^{0} \\ γ_{x y}^{0} \end{matrix}) + z (\begin{matrix} ε_{x}^{1} \\ ε_{y}^{1} \\ γ_{x y}^{1} \end{matrix}), (\begin{matrix} γ_{x z} \\ γ_{y z} \end{matrix}) = (\begin{matrix} ϕ_{x} + w_{, x} \\ ϕ_{y} + w_{, y} \end{matrix})

where

(\begin{matrix} ε_{x}^{0} \\ ε_{y}^{0} \\ γ_{x y}^{0} \end{matrix}) = (\begin{matrix} u_{, x} + w_{, x}^{2} / 2 \\ v_{, y} - w / R + w_{, y}^{2} / 2 \\ u_{, y} + v_{, x} + w_{, x} w_{, y} \end{matrix}), (\begin{matrix} ε_{x}^{1} \\ ε_{y}^{1} \\ γ_{x y}^{1} \end{matrix}) = (\begin{matrix} ϕ_{x, x} \\ ϕ_{y, y} \\ ϕ_{x, y} + ϕ_{y, x} \end{matrix})

where $u, v, w$ are displacement components of the middle plane in $x, y, z$ directions, respectively, and $ϕ_{x}, ϕ_{y}$ are rotations of a normal to the middle plane with respect to y, x axes, respectively. As shown in works of Panda and coworkers,^12,21,31 full kinematic model known as Green-Lagrange geometrical nonlinear strains accurately describe nonlinear behavior of structures because all nonlinear terms in strain–displacement relations are retained. However, Green-Lagrange geometrical nonlinearity leads to considerable cumbersomeness in mathematical formulations. Therefore, for most works in the literature, only nonlinear terms relating to the deflection (i.e. transverse displacement) are retained. Such approximate geometrical nonlinearity widely known as von Karman–Donnell nonlinearity is assumed in the present study.

Stress components in CNTRC CP are defined as

(\begin{matrix} σ_{x} \\ σ_{y} \\ σ_{x y} \\ σ_{x z} \\ σ_{y z} \end{matrix}) = (\begin{matrix} Q_{11} & Q_{12} & 0 & 0 & 0 \\ Q_{12} & Q_{22} & 0 & 0 & 0 \\ 0 & 0 & Q_{66} & 0 & 0 \\ 0 & 0 & 0 & Q_{44} & 0 \\ 0 & 0 & 0 & 0 & Q_{55} \end{matrix}) ((\begin{matrix} ε_{x} \\ ε_{y} \\ γ_{x y} \\ γ_{x z} \\ γ_{y z} \end{matrix}) - (\begin{matrix} α_{11} \\ α_{22} \\ 0 \\ 0 \\ 0 \end{matrix}) Δ T)

where

Q_{11} = \frac{E_{11}}{1 - ν_{12} ν_{21}}, Q_{22} = \frac{E_{22}}{1 - ν_{12} ν_{21}}, Q_{12} = \frac{ν_{21} E_{11}}{1 - ν_{12} ν_{21}}, Q_{44} = G_{13}, Q_{55} = G_{23}, Q_{66} = G_{12}

and ΔT = T − T₀ is uniform temperature rise from initial temperature T ₀ at which the CP is thermal stress free.

Based on the FSDT, force and moment resultants per unit length are expressed as follows

\begin{array}{l} N_{x} = e_{11} ε_{x}^{0} + ν_{21} e_{11} ε_{y}^{0} + e_{12} ϕ_{x, x} + ν_{21} e_{12} ϕ_{y, y} - e_{11 T} Δ T \\ N_{y} = ν_{12} e_{21} ε_{x}^{0} + e_{21} ε_{y}^{0} + ν_{12} e_{22} ϕ_{x, x} + e_{22} ϕ_{y, y} - e_{21 T} Δ T \\ N_{x y} = e_{31} γ_{x y}^{0} + e_{32} (ϕ_{x, y} + ϕ_{y, x}) \end{array}

\begin{array}{l} Q_{x} = K_{S} e_{41} (ϕ_{x} + w_{, x}), Q_{y} = K_{S} e_{51} (ϕ_{y} + w_{, y}) \\ M_{x} = e_{12} ε_{x}^{0} + ν_{21} e_{12} ε_{y}^{0} + e_{13} ϕ_{x, x} + ν_{21} e_{13} ϕ_{y, y} - e_{12 T} Δ T \\ M_{y} = ν_{12} e_{22} ε_{x}^{0} + e_{22} ε_{y}^{0} + ν_{12} e_{23} ϕ_{x, x} + e_{23} ϕ_{y, y} - e_{22 T} Δ T \\ M_{x y} = e_{32} γ_{x y}^{0} + e_{33} (ϕ_{x, y} + ϕ_{y, x}) \end{array}

where

\begin{array}{l} (e_{11}, e_{21}, e_{31}, e_{41}, e_{51}) = \int_{- h / 2}^{h / 2} (Q_{11}, Q_{22}, Q_{66}, Q_{44}, Q_{55}) d z \\ (e_{12}, e_{22}, e_{32}) = \int_{- h / 2}^{h / 2} (Q_{11}, Q_{22}, Q_{66}) z d z, (e_{13}, e_{23}, e_{33}) = \int_{- h / 2}^{h / 2} (Q_{11}, Q_{22}, Q_{66}) z^{2} d z \\ (e_{11 T}, e_{12 T}) = \int_{- h / 2}^{h / 2} Q_{11} (α_{11} + ν_{21} α_{22}) (1, z) d z, (e_{21 T}, e_{22 T}) = \int_{- h / 2}^{h / 2} Q_{22} (ν_{12} α_{11} + α_{22}) (1, z) d z \end{array}

and K_S is shear correction coefficient assumed as⁶³

K_{S} = \frac{5}{6 - (ν_{12}^{CNT} V_{CNT}^{*} + ν^{m} V_{m})}

The present study considers combined thermomechanical loading conditions as described in previous works.^2,3,18,19 For the general model of problem, CP is rested on an elastic foundation, exposed to a uniform through the thickness temperature field followed by combined mechanical loads. Based on the FSDT, nonlinear equilibrium equations of a CP resting on an elastic foundation are

N_{x, x} + N_{x y, y} = 0

N_{x y, x} + N_{y, y} = 0

Q_{x, x} + Q_{y, y} + N_{x} w_{, x x} + 2 N_{x y} w_{, x y} + N_{y} w_{, y y} + \frac{N_{y}}{R} + q - q_{f} = 0

M_{x, x} + M_{x y, y} - Q_{x} = 0

M_{x y, x} + M_{y, y} - Q_{y} = 0

where q is uniform lateral pressure receiving positive and negative values for external and internal pressures, respectively, and q_f is interactive pressure from elastic foundation represented by Pasternak model as

q_{f} = k_{1} w - k_{2} Δ w

in which k ₁ and k ₂ are elastic modulus of Winkler springs and stiffness of Pasternak shear layer, respectively, and Δ denotes Laplace operator.

By virtue of equations (7) and (10, 11) and taking into account initial geometrical imperfection, above equilibrium equations are written in a more compact form as

\begin{array}{l} a_{11} ϕ_{x, x x x} + a_{21} ϕ_{x, x y y} + a_{31} ϕ_{y, x x y} + a_{41} ϕ_{y, y y y} + a_{51} f_{, x x y y} + f_{, y y} (w_{, x x} + w_{, x x}^{*}) \\ - 2 f_{, x y} (w_{, x y} + w_{, x y}^{*}) + f_{, x x} (w_{, y y} + w_{, y y}^{*}) + \frac{f_{, x x}}{R} + q - k_{1} w + k_{2} Δ w = 0 \end{array}

where f(x, y) is a stress function defined as

N_{x} = f_{, y y}, N_{y} = f_{, x x}, N_{x y} = - f_{, x y}

$w^{*} (x, y)$ represents initial geometrical imperfection of the CP and detailed definitions of coefficients $a_{i 1} (i = 1 \div 5)$ are given in equation (1A) in Appendix 1.

Next, strain compatibility equation of a geometrically imperfect CP is defined as^18,19

ε_{x, y y}^{0} + ε_{y, x x}^{0} - γ_{x y, x y}^{0} = w_{, x y}^{2} - w_{, x x} w_{, y y} + 2 w_{, x y} w_{, x y}^{*} - w_{, x x} w_{, y y}^{*} - w_{, y y} w_{, x x}^{*} - \frac{w_{, x x}}{R}

Expressing $ε_{x}^{0}, ε_{y}^{0}, γ_{x y}^{0}$ in terms of $N_{x}, N_{y}, N_{x y}$ and using definition (21) in the obtained relations, equation (22) is rewritten in the form as

\begin{array}{l} a_{12} f_{, x x x x} + a_{22} f_{, x x y y} + a_{32} f_{, y y y y} + a_{42} ϕ_{x, x x x} + a_{52} ϕ_{y, x x y} + a_{62} ϕ_{y, y y y} + a_{72} ϕ_{x, x y y} \\ - w_{, x y}^{2} + w_{, x x} w_{, y y} - 2 w_{, x y} w_{, x y}^{*} + w_{, x x} w_{, y y}^{*} + w_{, y y} w_{, x x}^{*} + \frac{w_{, x x}}{R} = 0 \end{array}

where coefficients $a_{i 2} (i = 1 \div 7)$ can be found in equation (1B) in Appendix 1.

In the present study, all edges of the CP are assumed to be simply supported, two curved edges x = 0, a are freely movable and subjected to uniform compressive pressure P, whereas two straight edges y = 0, b are unloaded and tangentially restrained. The associated boundary conditions are expressed as

\begin{array}{l} w = ϕ_{y} = N_{x y} = M_{x} = 0, N_{x} = N_{x 0} at x = 0, a \\ w = ϕ_{x} = M_{y} = 0, N_{y} = N_{y 0} at y = 0, b \end{array}

where $N_{x 0} = - P h$ is prebuckling force resultant at movable edges x = 0, a and $N_{y 0}$ is fictitious compressive force resultant at restrained edges y = 0, b related to average end-shortening displacement Δy between edges y = 0, b as

Δ_{y} c = N_{y 0}

in which c is average tangential stiffness parameter in the y direction on each opposite edge. The definition of the average end-shortening displacement is expressed as

Δ_{y} = - \frac{1}{a b} \int_{0}^{a} \int_{0}^{b} \frac{\partial v}{\partial y} d y d x

To satisfy boundary conditions (24) approximately, the following solutions are assumed

(w, w^{*}) = (W, μ h) sin β_{m} x sin δ_{n} y

f = A_{1} cos 2 β_{m} x + A_{2} cos 2 δ_{n} y + A_{3} sin β_{m} x sin δ_{n} y + \frac{1}{2} N_{x 0} y^{2} + \frac{1}{2} N_{y 0} x^{2}

ϕ_{x} = B_{1} cos β_{m} x sin δ_{n} y, ϕ_{y} = B_{2} sin β_{m} x cos δ_{n} y

where $β_{m} = m π / a$ , $δ_{n} = n π / b$ , and $m, n, W, μ$ have their definitions as described in the work of Trang and Tung,⁶² whereas $A_{1}, A_{2}, A_{3}, B_{1}, B_{2}$ are coefficients to be determined.

Now, substitution of solutions (27–29) into equation (23) yields the following results

\begin{array}{l} A_{1} = \frac{δ_{n}^{2}}{32 a_{12} β_{m}^{2}} (W^{2} + 2 μ h W), A_{2} = \frac{β_{m}^{2}}{32 a_{32} δ_{n}^{2}} (W^{2} + 2 μ h W) \\ (a_{12} β_{m}^{4} + a_{22} β_{m}^{2} δ_{n}^{2} + a_{32} δ_{n}^{4}) A_{3} + (a_{42} β_{m}^{3} + a_{72} β_{m} δ_{n}^{2}) B_{1} + (a_{52} β_{m}^{2} δ_{n} + a_{62} δ_{n}^{3}) B_{2} - \frac{β_{m}^{2}}{R} W = 0 \end{array}

Subsequently, putting equations (7) and (10, 11) into the equations (17, 18), then substituting solutions (27–29) into the obtained relations give a system of two equations relating to coefficients $A_{3}, B_{1}, B_{2}$ and a combination of these two equations and equation (30) yields

B_{1} = B_{1}^{*} W, B_{2} = B_{2}^{*} W, A_{3} = A_{3}^{*} W

where coefficients $A_{3}^{*}, B_{1}^{*}$ , and $B_{2}^{*}$ are displayed in equation (1C) in Appendix 1.

Next, the solutions (27–29) are substituted into equilibrium equation (20) and applying Galerkin method for the resulting equation gives

\begin{array}{l} a_{13} \bar{W} + a_{23} \bar{W} (\bar{W} + μ) + a_{33} \bar{W} (\bar{W} + 2 μ) + a_{43} \bar{W} (\bar{W} + μ) (\bar{W} + 2 μ) \\ - (m^{2} B_{a}^{2} {\bar{N}}_{x 0} + n^{2} {\bar{N}}_{y 0}) (\bar{W} + μ) + 16 B_{a} R_{a} \frac{B_{h} γ_{m} γ_{n}}{m n π^{4}} {\bar{N}}_{y 0} + 16 q \frac{B_{h}^{2} γ_{m} γ_{n}}{m n π^{4}} = 0 \end{array}

where

\begin{array}{l} a_{13} = \frac{π}{B_{h}} ({\bar{a}}_{11} {\bar{B}}_{1}^{*} m^{3} B_{a}^{3} + {\bar{a}}_{21} {\bar{B}}_{1}^{*} m n^{2} B_{a} + {\bar{a}}_{31} {\bar{B}}_{2}^{*} m^{2} n B_{a}^{2} + {\bar{a}}_{41} {\bar{B}}_{2}^{*} n^{3}) \\ + (\frac{π^{2} {\bar{a}}_{51}}{B_{h}^{5} {\bar{b}}_{14}} m^{2} n^{2} B_{a}^{2} - \frac{m^{2} B_{a}^{3}}{B_{h}^{4} {\bar{b}}_{14}} R_{a}) (m^{2} π^{2} {\bar{b}}_{24} B_{a}^{3} R_{a} - {\bar{b}}_{34} B_{h}^{3}) - \frac{E_{0}^{m} K_{1}}{π^{2} B_{h}^{2}} - \frac{E_{0}^{m} K_{2}}{B_{h}^{2}} (m^{2} B_{a}^{2} + n^{2}) \\ a_{23} = \frac{32 B_{a}^{2}}{3 B_{h}^{5} {\bar{b}}_{14}} m n γ_{m} γ_{n} (m^{2} π^{2} {\bar{b}}_{24} B_{a}^{3} R_{a} - {\bar{b}}_{34} B_{h}^{3}), a_{33} = \frac{2 n γ_{m} γ_{n}}{3 m π^{2} B_{h} {\bar{a}}_{12}} B_{a} R_{a} \\ a_{43} = - \frac{m^{2} n^{2} π^{2}}{16 B_{h}^{2}} (\frac{n^{2}}{{\bar{a}}_{12} m^{2}} + \frac{m^{2} B_{a}^{4}}{{\bar{a}}_{32} n^{2}}), B_{a} = \frac{b}{a}, B_{h} = \frac{b}{h}, R_{a} = \frac{a}{R} \\ ({\bar{N}}_{x 0}, {\bar{N}}_{y 0}) = \frac{1}{h} (N_{x 0}, N_{y 0}), \bar{W} = W / h, γ_{i} = \frac{1}{2} [1 - {(- 1)}^{i}] · (i = m, n) \end{array}

in which

\begin{array}{l} ({\bar{a}}_{11}, {\bar{a}}_{21}, {\bar{a}}_{31}, {\bar{a}}_{41}) = \frac{1}{h^{3}} (a_{11}, a_{21}, a_{31}, a_{41}), {\bar{a}}_{51} = \frac{a_{51}}{h}, ({\bar{a}}_{12}, {\bar{a}}_{32}, {\bar{B}}_{1}^{*}, {\bar{B}}_{2}^{*}) = (a_{12}, a_{32}, B_{1}^{*}, B_{2}^{*}) h \\ {\bar{b}}_{14} = b_{14} h^{3}, {\bar{b}}_{24} = \frac{b_{24}}{h^{2}}, {\bar{b}}_{34} = b_{34} h, (K_{1}, K_{2}) = \frac{b^{2}}{E_{0}^{m} h^{3}} (k_{1} b^{2}, k_{2}) \end{array}

and $E_{0}^{m}$ is value of E^m calculated at room temperature $T_{0} = 300 K$ . In the following, fictitious force resultant $N_{y 0}$ will be determined. It is deduced from equations (7), (10), and (21) that

\begin{array}{l} \frac{\partial v}{\partial y} = \frac{1}{a_{82}} [e_{11} f_{, x x} - e_{21} ν_{12} f_{, y y} + (e_{12} e_{21} ν_{12} - e_{11} e_{22} ν_{12}) ϕ_{x, x} + (e_{12} e_{21} ν_{12} ν_{21} - e_{11} e_{22}) ϕ_{y, y}] \\ + \frac{1}{a_{82}} (e_{21 T} e_{11} - e_{21} e_{11 T} ν_{12}) Δ T - \frac{1}{2} w_{, y}^{2} - w_{, y} w_{, y}^{*} \end{array} + \frac{w}{R}

where a₈₂ is defined in equation (1B) of the Appendix 1.

Now, placing the solutions (27–29) into equation (35) and putting the resulting v, y into equation (26) yield the expression of the Δy, and a combination of this expression with equation (25) leads to the following result

{\bar{N}}_{y 0} = g_{11} {\bar{N}}_{x 0} + g_{21} \bar{W} + g_{31} \bar{W} (\bar{W} + 2 μ) + g_{41} Δ T

where coefficients $g_{i 1} (i = 1 \div 4)$ are displayed in equation (2A) in Appendix 2.

Placing ${\bar{N}}_{y 0}$ from equation (36) and ${\bar{N}}_{x 0} = - P$ into equation (32) leads to the following relation

\begin{array}{l} P = g_{13} \bar{W} + g_{23} \bar{W} (\bar{W} + μ) + g_{33} \bar{W} (\bar{W} + 2 μ) + g_{43} \bar{W} (\bar{W} + μ) (\bar{W} + 2 μ) \\ + [16 B_{a} R_{a} \frac{B_{h} γ_{m} γ_{n}}{m n π^{4}} - n^{2} (\bar{W} + μ)] \frac{g_{41}}{g_{53}} Δ T + 16 q \frac{B_{h}^{2} γ_{m} γ_{n}}{g_{53} m n π^{4}} \end{array}

where

\begin{array}{l} g_{13} = \frac{1}{g_{53}} (a_{13} + 16 B_{a} R_{a} g_{21} \frac{B_{h} γ_{m} γ_{n}}{m n π^{4}}), g_{23} = \frac{1}{g_{53}} (a_{23} - n^{2} g_{21}) \\ g_{33} = \frac{1}{g_{53}} (a_{33} + 16 B_{a} R_{a} g_{31} \frac{B_{h} γ_{m} γ_{n}}{m n π^{4}}), g_{43} = \frac{1}{g_{53}} (a_{43} - n^{2} g_{31}) \\ g_{53} = 16 B_{a} R_{a} g_{11} \frac{B_{h} γ_{m} γ_{n}}{m n π^{4}} - (m^{2} B_{a}^{2} + n^{2} g_{11}) (\bar{W} + μ) \end{array}

Equation (37) expresses the nonlinear load–deflection relation of CNTRC CPs under preexisting lateral pressure and subjected to uniform axial compression load in thermal environments. In general, as predicted from equations (37) and (38), bifurcation type buckling response does not occur when CNTRC CPs under combined loads and/or general cases of in-plane boundary conditions. In particular, CNTRC CPs may exhibit bifurcation type buckling response in special cases of panel geometry, loading, and in-plane boundary conditions. Specifically, when straight edges are freely movable (i.e. c = 0), geometrically perfect (μ = 0) CNTRC CPs subjected to axial compression only (i.e. $q = 0$ ) may exhibit a bifurcation type buckling response with buckling axial loads are

P_{b} = - \frac{a_{13}}{m^{2} B_{a}^{2}}

As CNTRC CPs are exposed to a uniform temperature field and subjected to preexisting nondestabilizing axial load followed by lateral pressure, equation (37) is rewritten as

\begin{array}{l} q = {g'}_{13} \bar{W} + {g'}_{23} \bar{W} (\bar{W} + μ) + {g'}_{33} \bar{W} (\bar{W} + 2 μ) + {g'}_{43} \bar{W} (\bar{W} + μ) (\bar{W} + 2 μ) \\ - [16 B_{a} R_{a} \frac{B_{h} γ_{m} γ_{n}}{m n π^{4}} - n^{2} (\bar{W} + μ)] \frac{g_{41} m n π^{4}}{16 B_{h}^{2} γ_{m} γ_{n}} Δ T + \frac{g_{53} m n π^{4}}{16 B_{h}^{2} γ_{m} γ_{n}} P \end{array}

where

{g'}_{13} = - \frac{g_{13} g_{53} m n π^{4}}{16 B_{h}^{2} γ_{m} γ_{n}}, {g'}_{23} = - \frac{g_{23} g_{53} m n π^{4}}{16 B_{h}^{2} γ_{m} γ_{n}}, {g'}_{33} = - \frac{g_{33} g_{53} m n π^{4}}{16 B_{h}^{2} γ_{m} γ_{n}}, {g'}_{43} = - \frac{g_{43} g_{53} m n π^{4}}{16 B_{h}^{2} γ_{m} γ_{n}}

It is predicted from equations (38) and (40) that axially precompressed CNTRC CPs under lateral pressure in a thermal environment may experience a bifurcation type buckling response with corresponding buckling pressures as

q_{b} = [\frac{B_{a}}{B_{h}} R_{a} g_{11} - \frac{μ m n π^{4}}{16 B_{h}^{2} γ_{m} γ_{n}} (m^{2} B_{a}^{2} + n^{2} g_{11})] P - (\frac{B_{a}}{B_{h}} R_{a} - \frac{μ m n^{3} π^{4}}{16 B_{h}^{2} γ_{m} γ_{n}}) g_{41} Δ T

Equations (37) and (40) describe the nonlinear relations of load and deflection for CNTRC CPs under combined thermomechanical loadings.

Results and discussion

This section presents numerical examples for CPs made of poly(methyl methacrylate) as matrix material and are reinforced by (10,10) SWCNTs. The temperature-dependent properties of the matrix is assumed to be $ν^{m} = 0.34$ , $α^{m} = 45 (1 + 0.0005 Δ T) \times 10^{- 6} / K$ and $E^{m} = (3.52 - 0.0034 T) GPa$ in which $T = T_{0} + Δ T$ with $T_{0} = 300 K$ . The temperature-dependent properties of the SWCNTs are given at discrete values of temperature in the works^43,50 and, by mathematical interpolation, are formulated as continuous functions of temperature in the work,⁵¹ and omitted here for sake of brevity. The CNT efficiency parameters $η_{j} (j = 1 \div 3)$ depending on CNT volume fraction are given as^43,50,54 $(η_{1}, η_{2}, η_{3}) = (0.137, 1.022, 0.715)$ for case of $V_{CNT}^{*} = 0.12$ , $(η_{1}, η_{2}, η_{3}) = (0.142, 1.626, 1.138)$ for case of $V_{CNT}^{*} = 0.17$ and $(η_{1}, η_{2}, η_{3}) = (0.141, 1.585, 1.109)$ for case of $V_{CNT}^{*} = 0.28$ . In addition, it is assumed that $G_{13} = G_{12}$ and $G_{23} = 1.2 G_{12}$ .⁴³

Verification

To verify the proposed approach, buckling response of simply supported CNTRC CPs with all movable edges under axial load alone in the thermal environments is considered. Critical buckling loads are calculated by equation (39) and given in Table 1 in comparison with results of Shen and Xiang⁵⁰ basing on asymptotic solutions and a perturbation technique. Next, the nonlinear response of CNTRC CPs with all movable edges under combined loads in a thermal environment is considered. Load–deflection curves are traced by equation (40) and displayed in Figure 2 in comparison with those obtained by Shen and Xiang⁵³ using asymptotic solutions and a perturbation technique. Table 1 and Figure 2 show that the present results well agree with those in the literature for special cases of loading and in-plane boundary condition.

Table 1.

Comparisons of critical buckling loads $P_{c r} b h$ (in kN) for CNTRC CPs with all movable edges subjected to axial compression only ( $a / b = 0.98$ , $a / R = 0.5$ , $b / h = 20$ , $h = 1 mm$ , $V_{CNT}^{*} = 0.17$ , $(m, n) = (1, 1)$ ).

$(K_{1}, K_{2})$	References	UD	FG-X	FG-V
$(0, 0)$	Shen and Xiang⁵⁰	5.79^a (5.29^b)	8.76 (8.14)	4.62 (4.16)
	Present	5.69 (5.34)	7.42 (6.95)	4.53 (4.24)
$(100, 0)$	Shen and Xiang⁵⁰	6.96 (6.57)	9.93 (9.43)	5.78 (5.45)
	Present	6.91 (6.56)	8.64 (8.16)	5.74 (5.46)
$(100, 10)$	Shen and Xiang⁵⁰	9.36 (8.97)	12.33 (11.84)	8.19 (7.85)
	Present	9.35 (9.01)	11.09 (10.61)	8.19 (7.91)

UD: uniform distribution; CNT: carbon nanotube; CNTRC: carbon nanotube–reinforced composite; CP: cylindrical panel; FG: functionally graded.

^a $T = 300 K$ .

^b $T = 400 K$ .

Figure 2.

Comparison of load–deflection curves of CNTRC CPs subjected to external pressure combined with axial compression.

To measure the degree of tangential constraints of straight edges in a more convenient way, a dimensionless tangential stiffness parameter is defined as follows

λ = \frac{c}{c + e_{11}}

Obviously, λ = 0 and λ = 1 represent movable and immovable cases of unloaded straight edges, respectively, and intermediate levels of tangential constraints of straight edges are defined by $0 < λ < 1$ .

In what follows, numerical results for CNTRC CPs with square planform (a = b) under combined loading conditions will be presented. For sake of brief expression, CNTRC CPs are assumed to be geometrically perfect $(μ = 0)$ , placed at room temperature ( $T = 300 K$ ) and without elastic foundations ( $K_{1} = K_{2} = 0$ ), unless otherwise specified.

As mentioned, bifurcation buckling behavior of CNTRC CPs may occur for special cases, that is, geometrically perfect CPs with all movable edges under axial compression load only. The effects of CNT distribution types, a/R curvature ratio, elastic foundations, and thermal environments on critical buckling axial loads of such CPs are shown in Table 2. As can be seen, critical buckling loads are increased when a/R ratio and/or stiffness of elastic foundations are increased, and decreased as temperature is elevated. Among four types of CNT distribution, FG-X panels have the highest buckling loads, UD panels have higher buckling loads than the remaining two distribution patterns, and buckling loads of FG-V panels are slightly higher than those of FG-Λ panels.

Table 2.

Critical buckling loads $P_{c r}$ (MPa) of CNTRC CPs with all movable edges under axial compression only ( $a / b = 1$ , $b / h = 20$ , $V_{CNT}^{*} = 0.17$ , λ = 0, $(m, n) = (1, 1)$ ).

$(K_{1}, K_{2})$	a/R	UD	FG-X	FG-V	FG-Λ
(0, 0)	0.1	252.04^a (238.77^b)	336.80 (316.96)	191.45 (181.62)	189.54 (179.99)
	0.3	260.24 (245.85)	345.12 (324.15)	201.68 (190.43)	195.94 (185.56)
	0.5	276.64 (260.02)	361.75 (338.52)	220.22 (206.42)	210.66 (198.31)
(100, 0)	0.1	315.37 (302.09)	400.12 (380.29)	254.78 (244.94)	252.86 (243.32)
	0.3	323.56 (309.18)	408.44 (387.47)	265.00 (253.75)	259.27 (248.88)
	0.5	339.96 (323.35)	425.07 (401.85)	283.54 (269.75)	273.98 (261.63)
(100, 5)	0.1	377.87 (364.59)	462.63 (442.79)	317.28 (307.44)	315.37 (305.82)
	0.3	386.07 (371.68)	470.94 (449.97)	327.50 (316.25)	321.77 (311.38)
	0.5	402.46 (385.85)	487.57 (464.35)	346.04 (332.25)	336.48 (324.13)

UD: uniform distribution; CNT: carbon nanotube; CNTRC: carbon nanotube–reinforced composite; CP: cylindrical panel; FG: functionally graded.

^a $T = 300 K$ .

^b $T = 400 K$ .

Axially precompressed CNTRC CP under external pressure

Numerical examples for CNTRC CPs under preexisting nondestabilizing axial load and subjected to uniform external pressure are presented in Figures 3 to 8. Figure 3 shows the effects of CNT distribution and preexisting axial load on the nonlinear response of CNTRC CPs with all movable edges subjected to external pressure. It is evident that FG-X type distribution of CNTs gives the best load carrying capability of nanocomposite CPs and pressure–deflection equilibrium paths are significantly dropped due to the presence of preexisting nondestabilizing axial load. Thus, only FG-X panels are considered in the remainder of this section. The effects of tangential constraint of unloaded straight edges on the nonlinear response of axially precompressed CNTRC CPs subjected to external pressure are examined in Figure 4. As can be observed, pressure–deflection paths of CPs with immovable straight edges $(λ = 1)$ are remarkably higher than those of CPs with movable straight edges $(λ = 0)$ . In addition, there is a little difference in the nonlinear response of CPs with immovable and partially movable straight edges because pressure–deflection paths are almost unchanged as λ varies from 0.2 to 1.

Figure 3.

Effects of CNT distribution pattern and preexisting axial load on the nonlinear response of CNTRC CPs subjected to external pressure.

Figure 4.

Effects of in-plane restraint of straight edges and preexisting axial load on the nonlinear response of CNTRC CPs subjected to external pressure.

Figure 5.

Effects of in-plane restraint of straight edges on the nonlinear response of CNTRC CPs exposed to elevated temperature and subjected to combined loads.

Figure 6.

Effects of thermal environments and preexisting axial load on the nonlinear response of CNTRC CPs subjected to external pressure.

Figure 7.

Effects of geometrical imperfection and preexisting axial load on the nonlinear response of CNTRC CPs exposed to elevated temperature and subjected to external pressure.

Figure 8.

Effects of elastic foundations and in-plane restraint of unloaded edges on the nonlinear response of CNTRC CPs subjected to combined loads.

Next, the effects of tangential constraint of unloaded straight edges on the nonlinear response of axially precompressed CNTRC CPs exposed to elevated temperature ( $T = 500 K$ ) and subjected to external pressure are analyzed in Figure 5. As shown, under this combined thermomechanical loading condition, the CPs experience a bifurcation type buckling response for arbitrary degree of tangential constraint of straight edges. Furthermore, buckling pressure and postbuckling equilibrium path are strongly enhanced when λ increases from 0 to 0.1, slowly enhanced as λ increases from 0.1 to 0.5, and then almost unchanged when λ varies from 0.5 to 1. It is explained that compressive prestress at restrained straight edges make the CP more curved and more stable under external pressure. Figure 6 indicates the effects of thermal environments and preexisting axial load on the nonlinear response of CNTRC CPs with immovable straight edges subjected to external pressure. It is recognized that buckling pressures of CPs under combined loads (i.e. P ≠ 0) are very slightly higher than those of CPs under external pressure alone (i.e. P = 0). In contrast, the CPs under combined loads experience a snap-through instability and have pronouncedly lower postbuckling paths, whereas postbuckling paths are higher and more stable as the CPs under external pressure alone (i.e. P = 0). It is interesting to note that, when straight edges are prevented from tangential displacement, bifurcation type buckling pressure and postbuckling strength of the CPs are increased as environment temperature become higher.

Subsequently, Figure 7 considers the effects of geometrical imperfection on the nonlinear response of CNTRC CPs with immovable straight edges exposed to elevated temperature ( $T = 400 K$ ) subjected to external pressure (P = 0) and combined loads (P = 300 MPa) in which positive and negative values of μ represent inward and outward initial deviations, respectively, of CP surfaces. For the CPs under external pressure alone, initial imperfection has immaterial effect on the nonlinear response in small region of deflection, and postbuckling paths are enhanced as μ increases from −0.1 to 0.1 in deep region of deflection. In contrast, for the CP under combined loads, buckling pressure and postbuckling path of the CP are considerably higher as surfaces of CP are initially deviated outward (i.e. μ < 0). As the ultimate illustration of this subsection, the effects of elastic foundations on the nonlinear stability of axially precompressed CNTRC CPs with restrained straight edges exposed to elevated temperature and subjected to external pressure are depicted in Figure 8. It is clear that elastic foundations have beneficial influences on the nonlinear stability of the CPs because the postbuckling equilibrium paths are higher and more stable (i.e. more benign snap-through response) due to the support of elastic foundations, although buckling pressures are unchanged with various values of stiffness parameters of elastic foundation.

Initially pressurized CNTRC CP under axial compression

This subsection presents numerical illustrations for CNTRC CPs under preexisting lateral pressure and subjected to axial compression. Figure 9 gives the effects of preexisting lateral pressure on the nonlinear response of CNTRC CPs with all movable edges (λ = 0) subjected to axial compression in which positive and negative values of q represent external and internal lateral pressures, respectively. Evidently, in this situation of in-plane boundary condition, the CP exhibits bifurcation type buckling behavior under axial compressive load only (i.e. q = 0), and preexisting lateral pressure has sensitive effect on the behavior tendency of axially loaded CPs. Specifically, the CPs have no longer bifurcation type buckling behavior through preexisting lateral pressure, and the CPs are deflected outward (negative deflection) and inward (positive deflection) at the onset of axial compression due to preexisting internal and external pressures, respectively. Next, when straight edges are immovable (λ = 1), there is no bifurcation buckling response of axially loaded CPs for arbitrary value of lateral pressure q, as demonstrated in Figure 10. This figure also indicates that the CPs are deflected outward at the onset of axial compression due to internal pressures or small external pressures (q = 0 or q = 10 kPa in this example) and are deflected inward as preexisting external pressure is sufficiently large.

Figure 9.

Effects of preexisting lateral pressure on the nonlinear response of CNTRC CPs with movable edges subjected to axial compression.

Figure 10.

Effects of preexisting lateral pressure on the nonlinear response of CNTRC CPs with immovable straight edges subjected to axial compression.

Next, the effects of preexisting lateral pressure and tangential constraint of straight edges on the nonlinear response of CNTRC CPs subjected to axial compression are analyzed in Figure 11. For the CPs under axial load only (q = 0), the CPs are bifurcately buckled as λ = 0 (movable straight edges) and are monotonically deflected outward as λ ≠ 0 (restrained straight edges). Under action of preexisting external lateral pressure (q = 100 kPa), axially loaded CPs are immediately deflected inward with arbitrary degree of tangential constraint of straight edges, and axial load–deflection equilibrium paths become higher when the straight edges are more rigorously restrained (i.e. higher values of λ). Then, Figure 12 shows the effects of thermal environments and in-plane boundary condition on the nonlinear response of CNTRC CPs under combined loads. It is observed that the CPs are deflected inward and load–deflection paths are more slightly dropped as temperature is elevated for movable case of straight edges. As the straight edges are immovable, the CPs are deflected inward and outward at room and elevated temperatures, respectively, and load–deflection paths are sharply dropped as temperature becomes higher.

Figure 11.

Effects of preexisting lateral pressure and tangential constraint of straight edges on the nonlinear response of CNTRC CPs subjected to axial compression.

Figure 12.

Effects of thermal environments and tangential constraint of straight edges on the nonlinear response of CNTRC CPs subjected to combined loads.

The effects of CNT volume fraction and elastic foundations on the nonlinear response of CNTRC CPs with movable edges subjected to combined loads at elevated temperature are illustrated in Figure 13. As expected, load–deflection equilibrium paths are enhanced due to the presence of elastic foundations and/or increase in volume percentage of CNTs. Finally, Figure 14 considers the effects of initial geometrical imperfection and a/R curvature ratio on the nonlinear response of CNTRC CPs with immovable straight edges exposed to thermal environment and subjected to axial load combined with preexisting external pressure. As shown, relatively shallow CP (a/R = 0.1) is deflected outward as μ = −0.1 (outward initial deviation) or μ = 0 (perfect geometry) and deflected inward as μ = 0.1 (inward initial deviation). In another behavior trend, deeper CP (a/R = 0.5) is deflected outward with arbitrary value of imperfection size μ. This suggests that interactive effects of initial imperfection and preexisting lateral pressure can change effective curvature of the CPs, although immovability of straight edges (and fictitious force resultant at these edges) essentially influence the behavior tendency of nanocomposite CPs.

Figure 13.

Effects of CNT volume fraction and elastic foundation on the nonlinear response of CNTRC CPs subjected to combined loads.

Figure 14.

Effects of initial imperfection and a/R curvature ratio on the nonlinear response of CNTRC CPs subjected to combined loads. CNTRC: carbon nanotube–reinforced composite; CP: cylindrical panel.

Concluding remarks

Basing on an analytical approach, nonlinear stability of moderately thick CNTRC CPs with tangentially restrained unloaded straight edges resting on elastic foundations, exposed to thermal environments and subjected to combined loading conditions has been presented. The results reveal that bifurcation type buckling response of CNTRC CPs only occurs for some special cases of panel geometry, tangential constraint of straight edges, and combined thermomechanical loading condition. Tangential constraints of straight edges and preexisting lateral pressure have important influences on the behavior trend and load carrying capacity of CNTRC CPs under combined loads. The study indicates that the nonlinear response and direction of deflection of the CPs under combined loads depend on direction and value of lateral pressure, size of initial geometrical imperfection, curvature of CPs, and temperature condition. In addition, elastic foundations have beneficial effects on the load carrying capability and stability of postbuckling paths of the CPs. As a final remark, the behavior of CNTRC CPs with restrained straight edges subjected to combined thermomechanical loads is complex and, thus, this article may have contribution for a better understanding about the nonlinear stability of nanocomposite CPs under abovementioned conditions of loading and tangential constraint of edges.

Footnotes

Funding

The author(s) disclosed receipt of the following financial support for the research, authorship, and/or publication of this article: This research is funded by Vietnam National Foundation for Science and Technology Development (NAFOSTED) under grant number 107.02-2017.11.

ORCID iD

Hoang Van Tung

Appendix 1

The coefficients $a_{i 1} (i = 1 \div 5)$ in the equation (20) are defined as

The detailed definitions of the coefficients $a_{i 2} (i = 1 \div 7)$ in the equation (23) are

The coefficients $A_{3}^{*}, B_{1}^{*}$ , and $B_{2}^{*}$ in equation (31) are defined as follows

in which

Appendix 2

The details of the coefficients $g_{i 1} (i = 1 \div 4)$ in equation (36) are

in which

and

References

Chang

Librescu

. Postbuckling of shear-deformable flat and curved panels under combined loading conditions. Int J Mech Sci 1995; 37(2): 121–143.

Librescu

Nemeth

Starnes

Jr , et al. Nonlinear response of flat and curved panels subjected to thermomechanical loads. J Thermal Stress 2000; 23: 549–582.

Librescu

Lin

Nemeth

, et al. Thermomechanical postbuckling of geometrically imperfect flat and curved panels taking into account tangential edge constraints. J Thermal Stress 1995; 18: 465–482.

Hirwani

Biswash

Mehar

, et al. Numerical flexural strength analysis of thermally stressed delaminated composite structure under sinusoidal loading. IOP Conf Ser Mater Sci Eng 2018; 338(1): 012019.

Panda

Singh

. Large amplitude free vibration analysis of thermally post-buckled composite doubly curved panel using nonlinear FEM. Finite Elem Anal Des 2011; 47(4): 378–386.

Panda

Singh

. Nonlinear free vibration analysis of thermally post-buckled composite spherical shell panel. Int J Mech Mater Des 2010; 6(2): 175–188.

Mahapatra

Panda

. Nonlinear free vibration analysis of laminated composite spherical shell panel under elevated hygrothermal environment: a micromechanical approach. Aerosp Sci Technol 2016; 49: 276–288.

Hirwani

Panda

Mahapatra

. Thermomechanical deflection and stress responses of delaminated shallow shell structure using higher-order theories. Compos Struct 2018; 184: 135–145.

Mahapatra

Panda

Kar

. Nonlinear flexural analysis of laminated composite panel under hygro-thermo-mechanical loading—a micromechanical approach. Int J Comput Method 2016; 13(3): 1650015.

10.

Panda

Katariya

. Stability and free vibration behavior of laminated composite panels under thermo-mechanical loading. Int J Appl Comput Mathemat 2015; 1(3): 475–490.

11.

Katariya

Panda

Mahapatra

. Nonlinear thermal buckling behavior of laminated composite panel structure including the stretching effect and higher-order finite element. Adv Mater Res 2017; 6(4): 349–361.

12.

Panda

Singh

. Thermal post-buckling behavior of laminated composite cylindrical/hyperboloid shallow shell panel using nonlinear finite element method. Compos Struct 2009; 91: 366–374.

13.

Panda

Singh

. Thermal postbuckling behavior of laminated composite spherical shell panel using NFEM. Mech Based Des Struct Mach 2013; 41(4): 468–488.

14.

Katariya

Das

Panda

. Buckling analysis of SMA bonded sandwich structure-using FEM. IOP Conf Ser Mater Sci Eng 2018; 338(1): 012035.

15.

Katariya

Panda

Hirwani

, et al. Enhancement of thermal buckling strength of laminated sandwich composite panel structure embedded with shape memory alloy fibre. Smart Struct Syst 2017; 20(5): 595–605.

16.

Panda

Singh

. Post-buckling analysis of laminated composite doubly curved panel embedded with SMA fibers subjected to thermal environment. Mech Adv Mater Struct 2013; 20(10): 842–853.

17.

Panda

Singh

. Thermal post-buckling analysis of a laminated composite spherical shell panel embedded with shape memory alloy fibres using non-linear finite element method. Proc Instit Mech Eng Part C J Mech Eng Sci 2010; 224(4): 757–769.

18.

Tung

. Postbuckling behavior of functionally graded cylindrical panels with tangential edge constraints and resting on elastic foundations. Compos Struct 2013; 100: 532–541.

19.

Tung

Duc

. Nonlinear response of shear deformable FGM curved panels resting on elastic foundations and subjected to mechanical and thermal loading conditions. Appl Mathematical Model 2014; 38: 2848–2866.

20.

Kar

Panda

. Free vibration responses of temperature dependent functionally graded curved panels under thermal environment. Latin Am J Solids Struct 2015; 12(11): 2006–2024.

21.

Kar

Panda

. Post-buckling behavior of shear deformable functionally graded curved shell panel under edge compression. Int J Mech Sci 2016; 115–116: 318–324.

22.

Kar

Panda

. Nonlinear thermomechanical behavior of functionally graded material cylindrical/hyperbolic/elliptical shell panel with temperature-dependent and temperature-independent properties. J Pressure Vessel Tech 2016; 138(6): 061202.

23.

Kar

Panda

Mahapatra

. Thermal buckling behavior of shear deformable functionally graded single/doubly curved shell panel with TD and TID properties. Adv Mater Res 2016; 5(4): 205–221.

24.

Kar

Mahapatra

Panda

. Effect of different temperature load on thermal postbuckling behavior of functionally graded shallow curved shell panels. Compos Struct 2017; 160: 1236–1247.

25.

Thostenson

Ren

Chou

. Advances in the science and technology of carbon nanotubes and their composites: a review. Compos Sci Technol 2001; 61(13): 1899–1912.

26.

Thostenson

Chou

. Nanocomposites in context. Compos Sci Technol 2005; 65(3–4): 491–516.

27.

Coleman

Khan

Blau

, et al. Small but strong: a review of the mechanical properties of carbon nanotube-polymer composites. Carbon 2006; 44(9): 1624–1652.

28.

Paradise

Goswami

. Carbon nanotubes—production and industrial applications. Mater Des. 2007; 28(5): 1477–1489.

29.

Gohardani

Elola

Elizetxea

. Potential and prospective implementation of carbon nanotubes on next generation aircraft and space vehicles: a review of current and expected applications in aerospace sciences. Prog Aeros Sci 2014; 70: 42–68.

30.

Shen

. Nonlinear bending of functionally graded carbon nanotube-reinforced composite plates in thermal environments. Compos Struct 2009; 91(1): 9–19.

31.

Mehar

Panda

. Geometrical nonlinear free vibration analysis of FG-CNT reinforced composite flat panel under uniform thermal field. Compos Struct 2016; 143: 336–346.

32.

Mehar

Panda

. Thermoelastic flexural analysis of FG-CNT doubly curved shell panel. Aircraft Eng Aeros Technol 2018; 90(1): 11–23.

33.

Mehar

Panda

Bui

, et al. Nonlinear thermoelastic frequency analysis of functionally graded CNT-reinforced single/doubly curved shallow shell panels by FEM. J Thermal Stress 2017; 40(7): 899–916.

34.

Mehar

Panda

Patle

. Thermoelastic vibration and flexural behavior of FG-CNT reinforced composite curved panel. Int J Appl Mech 2017; 9(4): 1750046.

35.

Mehar

Panda

Mahapatra

. Thermoelastic deflection responses of CNT reinforced sandwich shell structure using finite element method. Scientia Iranica 2018; 25(5): 2722–2737.

36.

Lei

Liew

. Buckling analysis of functionally graded carbon nanotube-reinforced composite plates using the element-free kp-Ritz method. Compos Struct 2013; 98: 160–168.

37.

Zhang

Lei

Liew

. Buckling analysis of FG-CNT reinforced composite thick skew plates using an element-free approach. Compos Part B Eng 2015; 75: 36–46.

38.

Lei

Zhang

Liew

. Buckling of FG-CNT reinforced composite thick skew plates resting on Pasternak foundations based on an element-free approach. Appl Math Comput 2015; 266: 773–791.

39.

Kiani

. Shear buckling of FG-CNT reinforced composite plates using Chebyshev-Ritz method. Compos Part B Eng 2016; 105: 176–187.

40.

Mirzaei

Kiani

. Thermal buckling of temperature dependent FG-CNT reinforced composite plates. Meccanica 2016; 51(9): 2185–2201.

41.

Kiani

. Thermal buckling of temperature-dependent FG-CNT-reinforced composite skew plates. J Thermal Stress 2017; 40(11): 1442–1460.

42.

Zhang

Liew

. Postbuckling analysis of axially compressed CNT reinforced functionally graded composite plates resting on Pasternak foundations using an element-free approach. Compos Struct 2016; 138: 40–51.

43.

Shen

Zhang

. Thermal buckling and postbuckling behavior of functionally graded carbon nanotube-reinforced composite plates. Mater Des 2010; 31(7): 3403–3411.

44.

Shen

Zhu

. Postbuckling of sandwich plates with nanotube-reinforced composite face sheets resting on elastic foundations. Eur J Mech A/Solids 2012; 35: 10–21.

45.

Kiani

. Thermal post-buckling of FG-CNT reinforced composite plates. Compos Struct 2017; 159(C): 299–306.

46.

Kiani

. Thermal postbuckling of temperature dependent sandwich plates with FG-CNTRC face sheets. J Thermal Stress 2018; 41(7): 866–882.

47.

Nasihatgozar

Daghigh

Eskandari

, et al. Buckling analysis of piezoelectric cylindrical composite panels reinforced with carbon nanotubes. Int J Mech Sci 2016; 107: 69–79.

48.

Garcia

Rodriguez

Castro

, et al. Buckling analysis of functionally graded carbon nanotube reinforced curved panels under axial compression and shear. Compos Part B Eng 2017; 108: 243–256.

49.

Liew

Lei

, et al. Postbuckling of carbon nanotube-reinforced functionally graded cylindrical panels under axial compression using a meshless approach. Comput Method Appl Mech Eng 2014; 268: 1–17.

50.

Shen

Xiang

. Postbuckling of axially compressed nanotube-reinforced composite cylindrical panels resting on elastic foundations in thermal environments. Compos Part B Eng 2014; 67: 50–61.

51.

Shen

. Postbuckling of nanotube-reinforced composite cylindrical panels resting on elastic foundations subjected to lateral pressure in thermal environments. Eng Struct 2016; 122: 174–183.

52.

Shen

Xiang

. Thermal postbuckling of nanotube-reinforced composite cylindrical panels resting on elastic foundations. Compos Struct 2015; 123: 383–392.

53.

Shen

Xiang

. Nonlinear response of nanotube-reinforced composite cylindrical panels subjected to combined loadings and resting on elastic foundations. Compos Struct 2015; 131: 939–950.

54.

Shen

HS.

Postbuckling of nanotube-reinforced composite cylindrical shells in thermal environments, Part I: Axially-loaded shells. Compos Struct 2011; 93: 2096–2108.

55.

Shen

HS.

Postbuckling of nanotube-reinforced composite cylindrical shells in thermal environments, Part II: Pressure-loaded shells. Compos Struct 2011; 93(10): 2496–2503.

56.

Shen

Xiang

. Postbuckling of nanotube-reinforced composite cylindrical shells under combined axial and radial mechanical loads in thermal environment. Compos Part B Eng 2013; 52: 311–322.

57.

Zhang

Liew

Jiang

. An element-free analysis of CNT-reinforced composite plate with column supports and elastically restrained edges under large deformation. Compos Part B Eng 2016; 95: 18–28.

58.

Zhang

Liew

Reddy

. Postbuckling of carbon nanotube reinforced functionally graded plates with edges elastically restrained against translation and rotation under axial compression. Comput Method Appl Mech Eng 2016; 298: 1–28.

59.

Tung

. Thermal buckling and postbuckling behavior of functionally graded carbon nanotube-reinforced composite plates resting on elastic foundations with tangential-edge restraints. J Therm Stress 2017; 40(5): 641–663.

60.

Trang

LTN

Tung

. Tangential edge constraint sensitivity of nonlinear stability of CNT-reinforced composite plates under compressive and thermomechanical loadings. J Eng Mech ASCE 2018; 144(7): 04018056.

61.

Tung

Trang

LTN

. Imperfection and tangential edge constraint sensitivities of thermomechanical nonlinear response of pressure-loaded carbon nanotube-reinforced composite cylindrical panels. Acta Mech 2018; 229(5): 1949–1969.

62.

Trang

LTN

Tung

. Thermomechanical nonlinear analysis of axially compressed carbon nanotube-reinforced composite cylindrical panels resting on elastic foundations with tangentially restrained edges. J Therm Stress 2018; 41(4): 418–438.

63.

Efraim

Eisenberger

. Exact vibration analysis of variable thickness thick annular isotropic and FGM plates. J Sound Vib 2007; 299: 720–738.

Nonlinear stability of CNT-reinforced composite cylindrical panels with elastically restrained straight edges under combined thermomechanical loading conditions

Abstract

Keywords

Introduction

CNTRC CP resting on an elastic foundation

Formulations

Results and discussion

Verification

Axially precompressed CNTRC CP under external pressure

Initially pressurized CNTRC CP under axial compression

Concluding remarks

Footnotes

Funding

ORCID iD

Appendix 1

Appendix 2

References