# Local Buckling Analysis of T-Section Webs with Closed-Form Solutions

Authors: Cheng Liang; Yabo He; Sumei Liu
Journal: Mathematical Problems in Engineering
 (2016)

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## Abstract

This paper reports on approaches to estimate the critical buckling loads of thin-walled T-sections with closed-form solutions. We first develop a model using energy conservation approach under the assumption that there is no correlation between the restraint coefficient and buckling half-wavelength. Secondly, we propose a numerical approach to estimate the critical buckling conditions under the more realistic torsional stiffener constraint condition. A dimensionless parameter correlated with constraint conditions is introduced through finite element (FE) analysis and data fitting technique in the numerical approach. The critical buckling coefficient and loads can be expressed as explicit functions of the dimensionless parameter. The proposed numerical approach demonstrates higher accuracy than the approach under noncorrelation assumption. Due to the explicit expression of critical buckling loads, the numerical approach presented here can be easily used in the design, analysis, and precision manufacture of T-section webs.


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## Body

## 1. Introduction

Thin-walled structures have been widely used in a large number of engineering applications such as civil infrastructure, high pressure vessel, aircraft composites, and wind turbines. Driven by those practical applications, considerable progress has been made in the design and analysis of composite elements such as beams and columns based on thin-walled structures [1–4]. Owing to their relatively low stiffness, local buckling generally occurs in thin-walled structures before reaching the strength failure of the materials, resulting in large deformation or even catastrophic failure of the overall system. Therefore, local buckling has been a critically important aspect in the design and precision manufacture of thin-walled structures [5, 6]. Wattanutchariya and Paul proposed a model for the prediction of plate buckling during thermally enhanced microlamination process for reliability and stability of the manufacturing process [7]. Lee and Bang developed an approach for estimation of lateral buckling of a wind turbine tower with a thin circular wall through finite element (FE) analysis to ensure structure safety [8]. Kim et al. carried out a buckling analysis of filament-wound composite cylinder subject to deep water high hydrostatic pressure [9], and so forth.Particularly, a great deal of research effort has also been carried out to study the buckling behaviour of thin-walled T-sections by considering the webs and flanges of thin-walled members as independent plates. In general, methods for determining the buckling loads of T-sections can be summarized into two categories [10]: (1) exact methods and (2) approximate methods. The former assume that the plates of the structures are simultaneously blended and the conjunctions of the plates satisfy continuity conditions, while the latter are also considered discrete plate analysis as they analyze the plates separately by taking the elastic restraints between adjacent plates into consideration. The discrete plate analysis approaches assume that the plate is simply supported at the loaded edges while being restrained by various conditions at the unloaded edge. For example, (1) the plate is elastically restrained at two unloaded edges (restrained-restrained (RR)) or (2) the plate is elastically restrained at one unloaded edge and free at the other unloaded edge (restrained-free (RF)), as shown in Figure 1.Figure 1
Schematics of restrained T-sections in this study: (a) cross-sectional view of T-sections; (b) uniaxially compressed T-section web restrained at one edge by torsional stiffeners and free at the other edge.
(a) (b)When discrete plate analysis is used, it is necessary to determine the elastic restraint acting on the restrained plates. In 2001, Qiao et al. [5] obtained the critical buckling loads and half-wave numbers of axially loaded RF and RR plates by solving two transcendental equations. They established a simplified expression for the critical buckling loads related to elastic restraint coefficients by using a fitting technique. Based on the derivation process conducted by Bleich et al. under isotropic conditions [11], Qiao presented conservative and simplified expressions for the restraint coefficients of rotating springs for I- and box-sections under anisotropic conditions by regarding the restraints as rotational spring constraints. Moreover, Qiao and Shan [6] presented an expression for the rotational restraint stiffness k for various thin-walled elements through the design and analysis of the local buckling of fibre-reinforced plastic composite. By regarding the webs and flanges of T-section members as a whole, they performed a finite element (FE) analysis to calculate the rotational restraint stiffness. Meanwhile, by using the fitting technique, they derived expressions for the rotational restraint stiffness of the webs and flanges of the T-section members, respectively. However, this method cannot be generally used since the rotational stiffness of any new section needs to be fitted again. Moreover, all of the analysis proposed by Qiao and Beich is based on the assumption that the restraints provided by the T-section flange to the web section are equivalent to rotational springs; that is, the restraining bending moment of the flange to the web of a unit length is(1)Mx=k∂w∂y=kθ,where θ is the angle between the flange and the web; k is the rotational restraint stiffness.However, the rotational spring restraint assumption is not always valid; Kollar [10, 12–14] divided the elastic restraints into two kinds based on analysis of the configurations of various sections: (1) when both of the two edges of the restrained plates are restrained, the restraints are equivalent to a rotating spring [11] and (2) when one edge of the restrained plates is free, the restraints are equivalent to torsional stiffener [15]. The former occurs when the webs and flanges of box-sections and the webs of I-, C-, and Z-sections are used as restrained plates, as shown in Figure 2(a). While, when the flanges of I-, C-, and Z-sections act as the restrained plates, the latter appears, as shown in Figure 2(b). In the case of Figure 2(b), the bending moments at the edges of the restrained web are equal to the distributed torque imposed by the flange plates and are related to the rate of change of the angle θ′. As shown in Figure 3, the restraining bending moment at the intersection of the flange and the web per unit length is(2)Mx=GJθ′′=GJ∂3w∂x2∂y,where GJ represents the torsional stiffness of the flange-web restraint.Figure 2
Restrained plates. (a) A restrained plate whose two edges are adjacent to the plate; (b) restrained plate with a free edge.
(a) (b)Figure 3
Elastic restraints of the flange on the web of the T-section: torque balance over a small part of the flange.In addition, Kollar presented an expression for the torsional restraining stiffness and a simple explicit expression for the critical buckling loads of RF [10] and RR [16] plates. However, this expression is not rigorous in theory and cannot be used to obtain closed-form solutions.In this work, we propose explicit solutions for critical buckling load of the T-section webs based on the torsional restraint model through Rayleigh-Ritz method and finite element (FE) analysis. Firstly, a closed-form expression for the critical buckling load of T-section webs is established using energy conservation approach with the assumption of noncorrelation of the restrain coefficient and buckling half-wavelength. Then, based on the FE analysis and the fitting technique, an explicit expression for the buckling half-wavelength is provided to calculate the restraint coefficients of torsional stiffeners, which is more realistic than the noncorrelation assumption. By introducing a dimensionless parameterβ in the numerical approach, we present an explicit expression for the critical buckling load which can be directly applied to the design of the thin-walled of T-section structures.


## 2. Variational Formula for the Local Buckling of Elastically Restrained Plates

Based on the discrete plate analysis proposed in the above section, both the web and flange of a T-section component can be simulated as RF plate units free at one unloaded edge and elastically restrained at the other unloaded edge, as shown in Figure1. Moreover, the web and the flange can be regarded as being restrained by torsional stiffeners. Here, the variational formula is adopted to analyze the local buckling of an isotropic plate with the boundary conditions presented in Figure 1 using the Rayleigh-Ritz method. Measuring a in length and b in width, the rectangular plate is uniformly loaded in the x-direction. The boundary parallel to the y-axis is simply supported. The y=b edge is a free boundary, while the y=0 edge is the boundary restrained by torsional stiffeners with torsional stiffness GJ. In this plate system, the total potential energy Π is composed of three parts: (1) the elastic strain energy Ue stored in the plate, (2) the restraint strain energy Ur preserved in the torsional stiffener constraint, and (3) the work V done by the externally applied force. These three parts can be calculated by using the appropriate function w as the buckling displacement out of the plane of the plate.The elastic strain energyUe, restraint strain energy Ur, and the work V done by the external force for orthogonal isotropic plates can be expressed as follows:(3)Ue=12∬D∇2w2-21-μ∂2w∂x2∂2w∂y2-∂2w∂x∂y2dxdy=D2∬w,xx2+w,yy2+2μw,xxw,yy+21-μw,xy2dxdy,(4)Ur=-12∫GJ∂3w∂x2yy=0∂w∂yy=0dx,(5)V=12∬Fx∂w∂x2dxdy,where D=Et3/12(1-μ2), E, t, and μ are the flexural rigidity, elastic modulus, thickness, and Poisson’s ratio of the plate, respectively; GJ represents the torsional stiffness of the torsional stiffener per unit length at y=0; Fx is the axial force per unit length of the loaded edge of the plate, while w denotes the buckling shape function of the plate.Considering small deformations and only the linear-elastic behaviour of the plate, the first-order variational form is presented as follows:(6)δUe=D∬w,xxδw,xx+w,yyδw,yy+μw,yyδw,xx+w,xxδw,yy+21-μw,xyδw,xydxdy,δUr=-12∫GJ∂3w∂x2yy=0δ∂w∂yy=0+∂w∂yy=0δ∂3w∂x2yy=0dx,δV=∬Fxw,xδw,xdxdy.For a plate system in an equilibrium state, the first-order variational form of its total potential energy equals zero; that is,(7)δΠ=δU1+δU2-δV=0.By substituting the buckling shape functionw satisfying certain boundary conditions into (7), we can establish a standard buckling eigenvalue problem which can be solved using the Rayleigh-Ritz method.


## 3. Explicit Solutions of the Local Buckling of Elastically Restrained Plates

When solving the buckling problem using the Rayleigh-Ritz method, it is crucial to select an appropriate shape functionw [17]. This function is expected to satisfy certain boundary restraints including force boundary restraints and displacement boundary restraints so as to ensure accuracy. Moreover, the structural form of the function is chosen to be as simple as possible for the convenience of obtaining corresponding explicit formula. Based on the recommendations of selecting shape functions in relevant studies [18, 19], the shape function shown in (8) is used to simulate the buckling deformation of plate units(8)w=yb+ψ1yb2+ψ2yb3+ψ3yb4sin⁡πxa0,where ψ1–ψ3 are coefficients determined by the boundary constraint conditions; a0=a/i is the buckling half-wavelength and i is the buckling half-wave number (i=1,2,…).The shape function used here applies strictly defined force boundary constraints at the unloaded edges. The specific expressions are presented in (9a) to (9d)(9a)wx,0=0.The torsional stiffener restraint is(9b)Mxx,0=-D∂2w∂y2y=0=GJ∂3w∂x2∂yy=0,(9c)Mxx,b=∂2w∂y2+μ∂2w∂x2y=b=0,(9d)Vy=∂3w∂y3+2-μ∂3w∂x2yy=b=0.By substituting (8) into (9a)–(9d), specific expressions for the coefficients ψ1–ψ3 can be obtained, as shown in (10a) to (10c)(10a)ψ1=GJπ2b2Da02,(10b)ψ2=-48a04ψ1+3π4b4+2π4b4ψ1-12π2a02b2-3π4b4s2+36π2a02b2s-2π4b4s2ψ1-8π2a02b2ψ1+40π2a02b2sψ172a04+30π2a02b2s-6π2a02b2-π4b4s2+π4b4,(10c)ψ3=12a04ψ1+2π4b4+π4b4ψ1-2π4b4s2+12π2a02b2s-π4b4s2ψ1+12π2a02b2sψ172a04+30π2a02b2s-6π2a02b2-π4b4s2+π4b4,where s=1-μ and ψ1 is termed as the restraint coefficient and ψ1=0 indicates that the plate is simply supported; when ψ1=∞, the plate is clamped.


### 3.1. Plates of Finite Length

By substituting (8) into (7), the corresponding analytical solutions for buckling loads and buckling coefficient after solving the standard eigenvalue problem can be derived. The specific expressions are shown as follows:(11)Fxcr=Kcrπ2Db2,(12)Kcr=b2a02+a02b22η2+ψ12π4η1+1-μη3+η4π2η1,where Fxcr and Kcr are the critical buckling load and buckling coefficient, respectively. For each buckling half-wave number i, there is a corresponding critical buckling load Fxcr. We are interested in finding the minimum value of Fxcr. In (12) η1–η4 are all functions of ψ1(13a)η1=252ψ12+180ψ22+140ψ32+420ψ1ψ2+360ψ1ψ3+315ψ2ψ3+630ψ1+504ψ2+420ψ3+4205040,(13b)η2=5ψ12+15ψ22+36ψ32+15ψ1ψ2+20ψ1ψ3+45ψ2ψ35,(13c)η3=ψ12+1.5ψ22+2ψ32+2.5ψ1ψ2+3ψ1ψ3+3.5ψ2ψ3+1.5ψ1+2ψ2+2.5ψ3+0.5,(13d)η4=-70ψ12+126ψ22+180ψ32+210ψ1ψ2+294ψ1ψ3+315ψ2ψ3+105ψ1+210ψ2+315ψ3210.


### 3.2. Long Plates

In this section, long plates witha≫b are investigated to obtain the minimal critical buckling load as a function of buckling half-wavelength a0. To get the minimal value of Fxcr, it is necessary to make dFxcr/da0=0. An explicit expression for the critical aspect ratio may be found if the restraint coefficients of the rotating springs of RF plates are not related to a0, as pointed out in the literature [6]. However, when using torsional stiffeners to simulate the restraints of T-sections, the restraint coefficient ψ1 of torsional stiffeners of RF plates (as presented in (10a)) is relevant to a0. This condition results in a transcendental equation, which can be only solved numerically. In the following sections, we present two approaches to derive explicit solutions for the critical buckling load.


#### 3.2.1. Energy Conservation Approach under Noncorrelation Assumption

To obtain an explicit solution, we assume there is no correlation betweenψ1 and a0. With the shape function shown in (8) and energy conservation condition shown in (7), for a long plate with one edge restrained by rotating springs and one free edge, the critical buckling load and coefficient can be derived as(14)Fxcr=Kcrπ2Db2,(15)Kcr=22η2+ψ12π4η1+1-μη3+η4π2η1.Specifically,ψ1=0 indicates that the plate is simply supported; the buckling coefficient is Ksf; when ψ1=∞, the plate is clamped and the buckling coefficient is Kcf(16a)Ksf=0.6081-μ,(16b)Kcf=1.531-μ.


#### 3.2.2. Numerical Approach under Torsional Stiffener Restraint Assumption

As presented earlier, the critical buckling load of those plates restrained by torsional stiffeners is related to the restraint coefficientψ1. Meanwhile, the restraint coefficient ψ1 of a torsional stiffener is related to the buckling half-wavelength a0. As analytical solutions cannot be obtained for a0, a simple explicit expression for a0 based on the FE analysis and the fitting technique will be presented below.By using FEA software ANSYS, the model of the whole structure of the T-section shown in Figure4 is established to analyze the elastic buckling of the web under uniform compressive stress. To highlight the torsional stiffener restraints on the flange to the web, degree of freedom (DOF) coupling is adopted in the modelling process. The flange and the web are separately modelled. Afterwards, rotational freedoms 4 and 5 of the nodes on the intersection of the web and the flange are coupled with the displacement DOF 3 outside the web (other DOFs remain independent). The model aims to prevent the uniform compressive stress imposed on the web from being transferred to the flange, thus avoiding buckling of the flange. Meanwhile, it is necessary to restrain DOFs 1 and 2 of nodes at both ends of the flange in order to prevent the flange from rigid translational movement. In the ANSYS model, loads are applied to the nodes on the loading edges by means of nodal loads. The value of the nodal load is calculated based on the tributary area of nodes: the load on tributary area of intermediate nodes is the sum of the half-areas of the two units adjacent to this node, while that on end nodes is equal to half of its unit value.Figure 4
The web being uniaxially compressed by uniform loads (considering flange restraint).By analyzing a large number of models with varyingbf, tf, bw, and tw (bw and tw refer to the width and thickness of the web; bf and tf refer to the width and thickness of the flange) and using data fitting technique, the buckling half-wavelength a0 can be expressed as follows:(17)a0=1.6751-0.39β-0.655b,where the introduced variable β=bftf3/bwtw3 refers to the ratio of the torsional stiffness of the flange to the bending stiffness of the web. When β=0.2375, the constrained edge of the web is equivalent to a simply supported edge with a buckling half-wavelength a0 being the length a of the plate. It also indicates that the flange of the T-section cannot restrain the web when bftf3<0.2375bwtw3. In addition, when β=∞, the constrained edge of the web is equivalent to the simply supported edge with the buckling half-wavelength being a0=1.675b.By substituting (10a)–(10c), (13a)–(13d), and (17) into (15), the critical buckling load of a long plate can be calculated under the noncorrelation assumption. Take a T-section shown in Figure 4, for example, where the parameters of the T-section are follows: bw=6 cm and tw=tf=0.25 cm; bf is a variable, which means that β is also a variable. Figure 5 shows that, compared with the critical buckling load of the T-section calculated by the FE analysis, the buckling loads of the RF plate computed by (15) under the noncorrelation assumption present a maximum error of 3.52%.Figure 5
Comparison of the critical buckling coefficient of the RF plate calculated using three methods.Substituting (17) into (10a) gives(18)ψ1=GJπ2b2Da02=sπ2bftf31.675/1-0.39β-0.6552bwtw3=sπ2β1.675/1-0.39β-0.6552.An interesting point arising from (18) is that the restraint coefficient ψ1 can be directly correlated with β. This indicates that the critical buckling load and coefficient can also be derived as explicit functions of β. On this basis, an explicit expression, simpler than that in (15), was obtained using the fitting technique(19)Kcr=Ksf+Kcf-Ksf∗0.51/β,where Ksf and Kcf are given by (16a) and (16b).As shown in Figure5, compared with the critical buckling load calculated by the FE approach, the critical buckling load computed by (19) is more conservative with a maximum error of only 2.18%. The closed-form solution of the critical buckling load coefficient presented in (19) demonstrates higher accuracy than (15) under the noncorrelation assumption, as well as simplicity for practical implementation in engineering applications.


## 3.1. Plates of Finite Length

By substituting (8) into (7), the corresponding analytical solutions for buckling loads and buckling coefficient after solving the standard eigenvalue problem can be derived. The specific expressions are shown as follows:(11)Fxcr=Kcrπ2Db2,(12)Kcr=b2a02+a02b22η2+ψ12π4η1+1-μη3+η4π2η1,where Fxcr and Kcr are the critical buckling load and buckling coefficient, respectively. For each buckling half-wave number i, there is a corresponding critical buckling load Fxcr. We are interested in finding the minimum value of Fxcr. In (12) η1–η4 are all functions of ψ1(13a)η1=252ψ12+180ψ22+140ψ32+420ψ1ψ2+360ψ1ψ3+315ψ2ψ3+630ψ1+504ψ2+420ψ3+4205040,(13b)η2=5ψ12+15ψ22+36ψ32+15ψ1ψ2+20ψ1ψ3+45ψ2ψ35,(13c)η3=ψ12+1.5ψ22+2ψ32+2.5ψ1ψ2+3ψ1ψ3+3.5ψ2ψ3+1.5ψ1+2ψ2+2.5ψ3+0.5,(13d)η4=-70ψ12+126ψ22+180ψ32+210ψ1ψ2+294ψ1ψ3+315ψ2ψ3+105ψ1+210ψ2+315ψ3210.


## 3.2. Long Plates

In this section, long plates witha≫b are investigated to obtain the minimal critical buckling load as a function of buckling half-wavelength a0. To get the minimal value of Fxcr, it is necessary to make dFxcr/da0=0. An explicit expression for the critical aspect ratio may be found if the restraint coefficients of the rotating springs of RF plates are not related to a0, as pointed out in the literature [6]. However, when using torsional stiffeners to simulate the restraints of T-sections, the restraint coefficient ψ1 of torsional stiffeners of RF plates (as presented in (10a)) is relevant to a0. This condition results in a transcendental equation, which can be only solved numerically. In the following sections, we present two approaches to derive explicit solutions for the critical buckling load.


### 3.2.1. Energy Conservation Approach under Noncorrelation Assumption

To obtain an explicit solution, we assume there is no correlation betweenψ1 and a0. With the shape function shown in (8) and energy conservation condition shown in (7), for a long plate with one edge restrained by rotating springs and one free edge, the critical buckling load and coefficient can be derived as(14)Fxcr=Kcrπ2Db2,(15)Kcr=22η2+ψ12π4η1+1-μη3+η4π2η1.Specifically,ψ1=0 indicates that the plate is simply supported; the buckling coefficient is Ksf; when ψ1=∞, the plate is clamped and the buckling coefficient is Kcf(16a)Ksf=0.6081-μ,(16b)Kcf=1.531-μ.


### 3.2.2. Numerical Approach under Torsional Stiffener Restraint Assumption

As presented earlier, the critical buckling load of those plates restrained by torsional stiffeners is related to the restraint coefficientψ1. Meanwhile, the restraint coefficient ψ1 of a torsional stiffener is related to the buckling half-wavelength a0. As analytical solutions cannot be obtained for a0, a simple explicit expression for a0 based on the FE analysis and the fitting technique will be presented below.By using FEA software ANSYS, the model of the whole structure of the T-section shown in Figure4 is established to analyze the elastic buckling of the web under uniform compressive stress. To highlight the torsional stiffener restraints on the flange to the web, degree of freedom (DOF) coupling is adopted in the modelling process. The flange and the web are separately modelled. Afterwards, rotational freedoms 4 and 5 of the nodes on the intersection of the web and the flange are coupled with the displacement DOF 3 outside the web (other DOFs remain independent). The model aims to prevent the uniform compressive stress imposed on the web from being transferred to the flange, thus avoiding buckling of the flange. Meanwhile, it is necessary to restrain DOFs 1 and 2 of nodes at both ends of the flange in order to prevent the flange from rigid translational movement. In the ANSYS model, loads are applied to the nodes on the loading edges by means of nodal loads. The value of the nodal load is calculated based on the tributary area of nodes: the load on tributary area of intermediate nodes is the sum of the half-areas of the two units adjacent to this node, while that on end nodes is equal to half of its unit value.Figure 4
The web being uniaxially compressed by uniform loads (considering flange restraint).By analyzing a large number of models with varyingbf, tf, bw, and tw (bw and tw refer to the width and thickness of the web; bf and tf refer to the width and thickness of the flange) and using data fitting technique, the buckling half-wavelength a0 can be expressed as follows:(17)a0=1.6751-0.39β-0.655b,where the introduced variable β=bftf3/bwtw3 refers to the ratio of the torsional stiffness of the flange to the bending stiffness of the web. When β=0.2375, the constrained edge of the web is equivalent to a simply supported edge with a buckling half-wavelength a0 being the length a of the plate. It also indicates that the flange of the T-section cannot restrain the web when bftf3<0.2375bwtw3. In addition, when β=∞, the constrained edge of the web is equivalent to the simply supported edge with the buckling half-wavelength being a0=1.675b.By substituting (10a)–(10c), (13a)–(13d), and (17) into (15), the critical buckling load of a long plate can be calculated under the noncorrelation assumption. Take a T-section shown in Figure 4, for example, where the parameters of the T-section are follows: bw=6 cm and tw=tf=0.25 cm; bf is a variable, which means that β is also a variable. Figure 5 shows that, compared with the critical buckling load of the T-section calculated by the FE analysis, the buckling loads of the RF plate computed by (15) under the noncorrelation assumption present a maximum error of 3.52%.Figure 5
Comparison of the critical buckling coefficient of the RF plate calculated using three methods.Substituting (17) into (10a) gives(18)ψ1=GJπ2b2Da02=sπ2bftf31.675/1-0.39β-0.6552bwtw3=sπ2β1.675/1-0.39β-0.6552.An interesting point arising from (18) is that the restraint coefficient ψ1 can be directly correlated with β. This indicates that the critical buckling load and coefficient can also be derived as explicit functions of β. On this basis, an explicit expression, simpler than that in (15), was obtained using the fitting technique(19)Kcr=Ksf+Kcf-Ksf∗0.51/β,where Ksf and Kcf are given by (16a) and (16b).As shown in Figure5, compared with the critical buckling load calculated by the FE approach, the critical buckling load computed by (19) is more conservative with a maximum error of only 2.18%. The closed-form solution of the critical buckling load coefficient presented in (19) demonstrates higher accuracy than (15) under the noncorrelation assumption, as well as simplicity for practical implementation in engineering applications.


## 3.2.1. Energy Conservation Approach under Noncorrelation Assumption

To obtain an explicit solution, we assume there is no correlation betweenψ1 and a0. With the shape function shown in (8) and energy conservation condition shown in (7), for a long plate with one edge restrained by rotating springs and one free edge, the critical buckling load and coefficient can be derived as(14)Fxcr=Kcrπ2Db2,(15)Kcr=22η2+ψ12π4η1+1-μη3+η4π2η1.Specifically,ψ1=0 indicates that the plate is simply supported; the buckling coefficient is Ksf; when ψ1=∞, the plate is clamped and the buckling coefficient is Kcf(16a)Ksf=0.6081-μ,(16b)Kcf=1.531-μ.


## 3.2.2. Numerical Approach under Torsional Stiffener Restraint Assumption

As presented earlier, the critical buckling load of those plates restrained by torsional stiffeners is related to the restraint coefficientψ1. Meanwhile, the restraint coefficient ψ1 of a torsional stiffener is related to the buckling half-wavelength a0. As analytical solutions cannot be obtained for a0, a simple explicit expression for a0 based on the FE analysis and the fitting technique will be presented below.By using FEA software ANSYS, the model of the whole structure of the T-section shown in Figure4 is established to analyze the elastic buckling of the web under uniform compressive stress. To highlight the torsional stiffener restraints on the flange to the web, degree of freedom (DOF) coupling is adopted in the modelling process. The flange and the web are separately modelled. Afterwards, rotational freedoms 4 and 5 of the nodes on the intersection of the web and the flange are coupled with the displacement DOF 3 outside the web (other DOFs remain independent). The model aims to prevent the uniform compressive stress imposed on the web from being transferred to the flange, thus avoiding buckling of the flange. Meanwhile, it is necessary to restrain DOFs 1 and 2 of nodes at both ends of the flange in order to prevent the flange from rigid translational movement. In the ANSYS model, loads are applied to the nodes on the loading edges by means of nodal loads. The value of the nodal load is calculated based on the tributary area of nodes: the load on tributary area of intermediate nodes is the sum of the half-areas of the two units adjacent to this node, while that on end nodes is equal to half of its unit value.Figure 4
The web being uniaxially compressed by uniform loads (considering flange restraint).By analyzing a large number of models with varyingbf, tf, bw, and tw (bw and tw refer to the width and thickness of the web; bf and tf refer to the width and thickness of the flange) and using data fitting technique, the buckling half-wavelength a0 can be expressed as follows:(17)a0=1.6751-0.39β-0.655b,where the introduced variable β=bftf3/bwtw3 refers to the ratio of the torsional stiffness of the flange to the bending stiffness of the web. When β=0.2375, the constrained edge of the web is equivalent to a simply supported edge with a buckling half-wavelength a0 being the length a of the plate. It also indicates that the flange of the T-section cannot restrain the web when bftf3<0.2375bwtw3. In addition, when β=∞, the constrained edge of the web is equivalent to the simply supported edge with the buckling half-wavelength being a0=1.675b.By substituting (10a)–(10c), (13a)–(13d), and (17) into (15), the critical buckling load of a long plate can be calculated under the noncorrelation assumption. Take a T-section shown in Figure 4, for example, where the parameters of the T-section are follows: bw=6 cm and tw=tf=0.25 cm; bf is a variable, which means that β is also a variable. Figure 5 shows that, compared with the critical buckling load of the T-section calculated by the FE analysis, the buckling loads of the RF plate computed by (15) under the noncorrelation assumption present a maximum error of 3.52%.Figure 5
Comparison of the critical buckling coefficient of the RF plate calculated using three methods.Substituting (17) into (10a) gives(18)ψ1=GJπ2b2Da02=sπ2bftf31.675/1-0.39β-0.6552bwtw3=sπ2β1.675/1-0.39β-0.6552.An interesting point arising from (18) is that the restraint coefficient ψ1 can be directly correlated with β. This indicates that the critical buckling load and coefficient can also be derived as explicit functions of β. On this basis, an explicit expression, simpler than that in (15), was obtained using the fitting technique(19)Kcr=Ksf+Kcf-Ksf∗0.51/β,where Ksf and Kcf are given by (16a) and (16b).As shown in Figure5, compared with the critical buckling load calculated by the FE approach, the critical buckling load computed by (19) is more conservative with a maximum error of only 2.18%. The closed-form solution of the critical buckling load coefficient presented in (19) demonstrates higher accuracy than (15) under the noncorrelation assumption, as well as simplicity for practical implementation in engineering applications.


## 4. Conclusion

We present closed-form solutions for the critical buckling loads of thin-walled T-section structures. An explicit expression of the critical buckling loads is derived based on energy conservation and constraint coefficient-buckling half-wavelength noncorrelation assumption. Secondly, we develop a numerical approach by taking account of the correlation of the constraint coefficient and buckling half-wavelength. Through FE analysis and data fitting, the buckling half-wavelengtha0 can be correlated with the geometric parameters of the T-section via a variable β. β is not merely a data fitting parameter but also directly corresponds to various constraint conditions. It is found that the restraint coefficient ψ1 can be expressed as a closed-form solution of β under energy conservation approach. Therefore, the critical buckling load and coefficient can also be derived as explicit functions of β.The explicit expression of critical buckling coefficient [see (19)] derived by the numerical approach provides benefits of not only convenient applications in engineering practice, but also higher accuracy than the explicit expression obtained under the noncorrelation assumption [see (15)]. We expect the closed-form solutions proposed herein to be valuable for design and precision manufacture of T-section structures.



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*Source: 6929352-2016-12-13.xml*