Advances in Civil Engineering
Volume 2021 (2021), Article ID 6637891, 17 pages
https://doi.org/10.1155/2021/6637891

Research Article

Study on the Axial Compression Postbuckling Similitude Model of the Stiffened Cylindrical Shell with Dimple Imperfections

Jiawei Ding,¹ Xinkui Xing,1,2 Wei Yu,1,2 and Wanxu Zhu1,2

¹College of Civil and Architecture Engineering, Guilin University of Technology, Guilin 541004, China
²Guangxi Key Laboratory of New Energy and Building Energy Saving, Guilin 541004, China

Correspondence should be addressed to Wei Yu; yuwei3601@163.com

Received 23 November 2020; Revised 20 March 2021; Accepted 2 April 2021; Published 20 April 2021

Academic Editor: Daniele Baraldi

Copyright © 2021 Jiawei Ding et al. This is an open access article distributed under the Creative Commons Attribution License, which permits unrestricted use, distribution, and reproduction in any medium, provided the original work is properly cited.

Abstract.

The body of the new-type dry gas holder is a large stiffened cylindrical shell. Limited by the test site and economic conditions, the buckling characteristics of such holders are generally studied through scale model experiments. Taking the longitudinal-ring rectangular stiffened cylindrical shell as the research object, the generalized similitude condition and scaling principle formula of the structure are derived innovatively based on Donnell’s assumption and the energy method. By means of displacement loading and node coordinates updating, dimple imperfections are introduced into the ideal structure of the stiffened cylindrical shell, and then, the complete similitude and partial similitude analysis of axial compression nonlinear buckling for imperfect structures are carried out. The analysis results show that the complete similitude analysis of stiffened cylindrical shell axial-compression nonlinear buckling can be realized accurately; the partial similitude model for stiffened cylindrical shell axial-compression nonlinear buckling can better predict the buckling characteristics of its prototype structures, and the closer the Poisson’s ratio between the model and the prototype materials is, the more accurate the prediction results are. Meanwhile, the generalized similitude condition and scaling principle formula derived based on the energy method can provide useful reference for the model design and experimental verification of the axial compression buckling of the stiffened cylindrical shell with local geometric imperfections.

1. Introduction

Stiffened thin-walled cylindrical shell is usually composed of skin and ribs, which have the advantages of high specific stiffness and specific strength, so it is widely used in aerospace, ships and vessels, pressure vessels, and other structures [1]. Stiffened thin-walled cylindrical shell structures in engineering usually contain geometric imperfections, and as a result, such structures are prone to buckling failure. Due to the limitation of high cost, difficulty, and long time in the prototype buckling test for large-size stiffened thin-walled cylindrical shell structures, the results of the scale model buckling test are usually used to predict the buckling characteristics of prototype structures [2].

Scholars at home and abroad have made some progress in studying the buckling and buckling scale model of shells. The main methods include dimensional analysis, similitude transformation analysis based on the solution of the shell governing equation, and similitude transformation analysis based on the structural system governing the differential equation as well as the energy method. Simitses et al. [3] have carried out studies on laminated cylindrical shell axial-compression buckling scale models. The results show that the radius, length, and thickness of the shell are important parameters that affect the design of the scale model. Laminated cylindrical shells can realize partial similitude simulation of geometric dimension scaling, but when the materials are different, the model cannot accurately predict the prototype. Ungbhakorn and Singhatanadgid [4, 5] have also carried out the research on the complete similitude and partial similitude scaling principles for the buckling of laminated cylindrical shells. When the materials of the model and the prototype are different, the model still cannot predict the buckling characteristics of the prototype. Hilburger et al. [6, 7] have obtained more accurate ultimate buckling load of the structure with the stiffened cylindrical shell finite element model verified by the scale model test and prototype test. This method does not need to carry out a large number of tests on large-size stiffened cylindrical shells, but the author has not given the basis for designing the scale model and the buckling scaling principle formula. Balbin and Bisagni [8] have presented a scaling method for sandwich composite cylindrical shells based on the nondimensionalization buckling equations. The results of the finite element show that the agreement is better in the case in which there is a lower transverse shear influence between the prototype and the model. Based on the energy method, Yu [9] has derived the complete and partial similitude scaling principle formula for the buckling of stiffened cylindrical shells under axial compression and lateral compression and verified the accuracy of the formula by finite element simulation but has not studied the structural similitude of stiffened cylindrical shells with dimple imperfections.

Basically speaking, there always exist some initial geometric imperfections in the shell structure in practical engineering. In recent years, many scholars have carried out further research in the field about shell buckling and imperfection sensitivity analysis. Tian and Wang [10] have proposed a method for accurate determination of compressive response of axially loaded stiffened shells based on the Worst Multiple Perturbation Load Approach. The results show that the proposed method is efficiencient to predict lower-bound buckling loads for stiffened shells. Wagner et al. [11] have presented a new design lower bound for metallic orthogonal-stiffened shells under axial compression. The analysis results of the shell with multiple cutouts and the perfect shell were compared and analyzed. Based on proper orthogonal decomposition and vibration correlation technique, Tian et al. [12] proposed the POD-VCT analysis method for imperfect shells under axial compression and verified the reliability of the method by buckling tests of shells with different structural configurations, materials, and imperfections. Among the imperfections, dimple imperfection is one of the most typical and unfavorable initial geometric imperfections [13]. Therefore, it is of great significance to study the axial compression buckling scale model of the stiffened cylindrical shell with dimple imperfections. In this paper, taking the longitudinal-ring rectangular stiffened cylindrical shell as the research object and based on the densely stiffening theory and energy method, the generalized similitude conditions and scaling principle formula of the structure are put forward, and the complete similitude and partial similitude simulation analysis of the nonlinear buckling of the structure under axial compression are carried out. Using the dimple imperfection function, dimple imperfection is introduced into the finite element model of perfect stiffened cylindrical shells. Furthermore, the nonlinear buckling similitude analysis of the prototype and scale model of the stiffened cylindrical shell with dimple imperfections is carried out to verify the generalized similitude conditions of the scale model design and the scaling principle formula of nonlinear buckling under axial compression.

2. Buckling Scaling Principle Formula of the Longitudinal-Ring Stiffened Cylindrical Shell under Axial Compression

The mathematical models of arbitrary two similar stiffened cylindrical shell structures are consistent in the process of similitude transformation, and their total energy relationship is [14]

where the prototype and model are distinguished by subscripts p and m, Xpi and Xmi correspond to the material and geometric parameters of the prototype and model, respectively, Ci represents the scaling factor of the structural parameters of the prototype and model, and Ψ(Ci) represents the transfer function of the scaling factors of two similar structures. This relational expression can be used to derive the generalized similitude conditions and the scaling principle formula for the buckling of stiffened cylindrical shells under axial compression.

The energy functional of the stiffened cylindrical shell under static force can be expressed as

where U and UL are the strain energy and external work of the structure, respectively.

Based on Donnell’s assumption, the nonlinear geometric equation of the middle plane of the stiffened cylindrical shell with initial geometric imperfections is [15]

where εx, εy, and γxy represent the axial strain, circumferential strain, and shear strain of the cylindrical shell, respectively, χx, χy, and χxy represent the curvature of the cylindrical shell, and represent the axial, circumferential, and radial displacements and the radial displacement imperfections of the cylindrical shell, respectively.

The internal force expression of the stiffened cylindrical shell based on densely stiffening theory is [16]

where Nx, Ny, and Nxy represent membrane internal forces per unit length, Mx, My, and Mxy represent bending moments per unit length, and Aij, Bij, and Dij represent tensile stiffness, coupled stiffness, and bending stiffness, respectively. The expressions of these stiffness parameters are

where subscripts s and r represent longitudinal and circumferential stiffeners, respectively, E, μ, and G represent the elasticity modulus, Poisson’s ratio, and shear modulus of the material, respectively, B and D represent the tensile stiffness and bending stiffness of the skin, respectively, Ar and As represent the cross-sectional area of stiffeners, er and es represent the eccentricity of stiffeners relative to the middle plane of the shell, Ir and Is represent the inertia moment of stiffeners relative to the middle plane of the shell, dr and ds represent the distance between two adjacent stiffeners, and Jr and Js represent the torsion constants of stiffeners.

The expression of the strain energy and external work of the stiffened cylindrical shell is [17, 18]

where L and R represent the axial length and radius of the cylindrical shell, respectively, and px represents the axial load of the structure.

From formulas (2)–(7), we can obtain the total energy of the densely stiffened cylindrical shell, which is

When the geometric parameters of the skin with two similar structures are completely similar, then . According to conversion formula (1) of total energy similitude between the scale model and prototype structure, the necessary condition for similitude between the scale model and prototype structure can be obtained, which is

According to formula (9), the similar invariant of the buckling of the densely stiffened cylindrical shell under axial compression can be obtained, which is

where represents the axial buckling load of the stiffened cylindrical shell, .

Therefore, the scaling principle formula for the buckling of densely stiffened cylindrical shells under axial compression can be written as

3. Verification of Nonlinear Buckling of the Cylindrical Shell with Dimple Imperfections under Axial Compression by the Finite Element Example

In this paper, the example for nonlinear buckling of the cylindrical shell with dimple imperfections under axial compression in literature [19] is taken as the example for verification by using finite element software ANSYS, and the finite element APDL language program of the example is written to verify the accuracy and reliability of the finite element analysis in this paper. The geometric and material parameters of the cylindrical shell with dimple imperfections are shown in Table 1. The upper boundary of the structure only releases the axial displacement constraint, while the lower boundary of the structure adopts the fixed end boundary.

Table 1: Geometric and material parameters of the cylindrical shell.

Material parameters
Geometric parameters of cylindrical shell (m)

E (GPa)
μ
R
L
t

72
0.31
0.25
0.51
0.0005

The applied dimple imperfection function is [19]

where λ is the imperfection diameter, δ₀ is the imperfection amplitude, θ₀ and z₀ are the circumferential and axial coordinate values of the imperfection center, and s is the distance from the finite element grid node to the imperfection center within the imperfection range. The dimple imperfection is introduced into the perfect structural model by static analysis of displacement loading and updating the node coordinates of the model.

Newton–Raphson method (NR method) with displacement loading and arc-length method (AR method) with force loading are used for example verification. Figure 1 shows the comparison between the load-displacement curves of the perfect structural buckling under axial compression analyzed by two methods and the literature results. Table 2 lists the errors between the results obtained by the two methods and the literature results when δ₀ = 5t and λ are 0.05 m, 0.06 m, and 0.07 m, respectively.

Figure 1: Comparison of axial compression buckling load axial-compression deformation curves of the perfect cylindrical shell.

Table 2: Comparison of nonlinear buckling ultimate loads of cylindrical shells with dimple imperfections under axial compression.

δ₀ (m)
λ (m)
Literature [15] (kN)
NR method (kN)
Error (%)
AR method (kN)
Error (%)

0.5t
0.05
42.18
44.37
5.19
43.90
4.08

0.06
42.29
43.41
2.65
44.04
4.14

0.07
42.38
44.49
4.98
43.96
3.73

It can be seen from Figure 1 and Table 2 that the arc-length method APDL program for nonlinear buckling analysis of cylindrical shells under axial compression is accurate and reliable.

4. Complete Similitude Analysis of Nonlinear Buckling of the Longitudinal-Ring Rectangular Stiffened Cylindrical Shell under Axial Compression

4.1. Scaling Principle Formula for Complete Similitude of Nonlinear Buckling of the Longitudinal-Ring Rectangular Stiffened Cylindrical Shell under Axial Compression

Under the condition of complete similitude, the geometric dimension scaling factors, material parameters, and boundary conditions of the prototype and model are identical. When the geometric scaling factor of the model is k, the stiffness scaling factor of the structure is

Therefore, scaling principle formula (11) for the buckling of the densely stiffened cylindrical shell under axial compression can be simplified as

4.2. Example Analysis on Complete Similitude of Nonlinear Buckling of the Longitudinal-Ring Rectangular Stiffened Cylindrical Shell under Axial Compression

Based on finite element software ANSYS, the shell 181 element is utilized to discretize the model. See Tables 3 and 4 for parameters of the prototype and model of the longitudinal-ring stiffened cylindrical shell. The geometric scaling factors of scale models are all taken as 10. In order to ensure the accuracy and economy of finite element simulation, reasonable unit partition is made for both the prototype and model. For the model and prototype of the longitudinal-ring stiffened cylindrical shell, the interval between two adjacent stiffeners is divided into 8 equal parts, and the height of the stiffening web is divided into 3 equal parts. Use the dimple imperfection function expressed by formulae (12a) and (12b) to introduce dimple imperfection into the longitudinal-ring stiffened cylindrical shell, with the dimple imperfection center located at half of the height of the cylindrical shell. Use the arc length method in finite element analysis to study the complete similitude of the nonlinear buckling of the longitudinal-ring stiffened cylindrical shell under axial compression. The finite element model of the longitudinal-ring stiffened cylindrical shell with dimple imperfection is shown in Figure 2.

Table 3: Parameters of the longitudinal-ring stiffened cylindrical shell prototype.

Material parameters
Geometric parameters of skin (m)
Stiffeners parameters

E (GPa)
μ
Rp
Lp
tp
hsp (mm)
tsp (mm)
Nsp
hrp (mm)
trp (mm)
Nrp

72.40
0.3
2.4257
6.0885
0.0127
38.354
24.384
60
38.354
24.384
24

Table 4: Parameters of the completely similar model of the longitudinal-ring stiffened cylindrical shell.

Material parameters
Geometric parameters of skin (m)
Stiffeners parameters

E (GPa)
μ
Rm
Lm
tm
hsm (mm)
tsm (mm)
Nsm
hrm (mm)
trm (mm)
Nrm

72.40
0.3
0.24257
0.60885
0.00127
3.8354
2.4384
60
3.8354
2.4384
24

Note. t-skin thickness, hr and hs-height of rectangular stiffeners, tr and ts-thickness of rectangular stiffeners, and Nr and Ns-number of stiffeners.

(a)

(b)

Figure 2: Longitudinal-ring stiffened cylindrical shell finite element model with dimple imperfection introduced (3x magnification).

Table 5 shows the comparison of critical load buckling of the longitudinal-ring rectangular stiffened cylindrical shell under axial compression. It can be seen from Table 5 that, under the nine working conditions consisting of three imperfection amplitudes and three imperfection diameters, the absolute value of the relative error between the critical load of the prototype structure predicted by the scale model based on scaling principle formula (14) and the critical load of the prototype structure is within 2.500%, which indicates that the complete similitude of nonlinear buckling of the stiffened cylindrical shell with dimple imperfections under axial compression can be realized accurately.

Table 5: Complete similitude simulation of nonlinear buckling of longitudinal-ring rectangular stiffened cylindrical shell under axial compression.

δ₀ (m)
Model
Prototype
Error (%)

λ (m)
Critical buckling load/kN·m⁻¹
λ (m)
Critical buckling load (kN·m⁻¹)
Critical buckling load for predicted prototype (kN·m⁻¹)

0.1
0.048
715.790
0.480
7090.300
7157.900
0.950

0.060
631.083
0.600
6224.060
6310.830
1.390

0.072
592.084
0.720
5985.940
5920.840
−1.080

0.3
0.048
683.33
0.480
6780.880
6833.300
0.770

0.060
515.110
0.600
5273.950
5151.100
−2.320

0.072
489.879
0.720
4895.220
4898.790
0.070

0.5
0.048
642.638
0.480
6382.980
6426.380
0.680

0.060
483.181
0.600
4810.450
4831.810
0.440

0.072
448.419
0.720
4476.690
4484.190
0.170

Note. is the sum of the thickness of the cylindrical shell skin and the height of stiffeners.

Figures 3(a) and 3(b), respectively, show the relationship between the critical loads and the imperfection amplitudes and diameters of the prototype and the model. It can be seen that the critical loads of the prototype and the model decrease with the increase of imperfection amplitude and diameter.

(a)

(b)

Figure 3: Imperfection sensitivity of the prototype and model under different imperfection diameters and amplitudes. (a) Prototype. (b) Model.

Figure 4 shows the comparison of load-displacement curves of the structural prototype, model, and the prediction prototype under three kinds of imperfection amplitudes when the imperfection diameters of the prototype and model are 0.720 m and 0.072 m, respectively. It can be seen from Figure 4 that the load-displacement curve of the complete similitude scale model can accurately predict the load-displacement curve of the prototype.

(a)

(b)

(c)

Figure 4: Comparison of complete similitude load-displacement curves for nonlinear buckling of the stiffened cylindrical shell under axial compression when λp = 0.72 m and λm = 0.072 m. (a) δ0 = 0.1. (b) δ0 = 0.3. (c) δ0 = 0.5.

Figure 5 shows the displacement vector and nephogram of the structural prototype and the complete similitude scale model at the point corresponding to the critical load when the imperfection diameter of the prototype and the model is 0.720 m and 0.072 m, respectively, and the imperfection amplitude is 0.5. From Figure 5, it can be seen that the buckling modes of the model and the prototype are the same at the point corresponding to the critical load.

(a)

(b)

(c)

(d)

(e)

(f)

Figure 5: Comparison of buckling modes between the prototype and complete similitude model when λp = 0.720 m, λm = 0.072 m, and δ₀ = 0.5. (a) Oblique view of the prototype (10x magnification). (b) Front view of the prototype (10x magnification). (c) Near imperfection of the prototype (1x). (d) Oblique view of the model (10x magnification). (e) Front view of the model (10x magnification). (f) Near imperfection of the model (1x).

5. Partial Similitude Analysis of Axial Compression Nonlinear Buckling of the Longitudinal-Ring Rectangular Stiffened Cylindrical Shell

5.1. Partial Similitude Scaling Principle Formula for Axial Compression Nonlinear Buckling of the Longitudinal-Ring Stiffened Cylindrical Shell

It is extremely difficult to satisfy all the similitude conditions, and it is not applicable in practical engineering, so it is necessary to carry out studies on the partial similitude model. In this paper, considering the situation that the materials and geometric dimensions of the scale model are different from those of the prototype, aluminum (Al), copper, brass, and plastic (PVC) are used, respectively, as the materials for the scale model. The material parameters are shown in Table 6.

Table 6: Material parameters of the scale model.

Material
E (GPa)
μ

Aluminum
68.75
0.30

Copper
124
0.33

Brass
106
0.34

PVC
3.79
0.40

Taking the ratio of elastic modulus between the prototype and model as k and the scaling factor of skin geometric dimension as k₁, then there is a similitude relation as follows:

Substituting formula (15) into necessary similitude condition formula (9) and similitude invariant formula (10), we can get

Therefore, by simplifying formula (11), we can get the scaling principle formula of the partial similitude of the longitudinal-ring rectangular stiffened cylindrical shell buckling under axial compression, which is

5.2. Example Analysis on Partial Similitude of Axial Compression Nonlinear Buckling of the Longitudinal-Ring Rectangular Stiffened Cylindrical Shell

Taking the skin geometric scaling factor k₁ as 10 and solving equation sets (15) and (16), respectively, the geometric dimensions of circumferential and longitudinal stiffeners of the partial similitude scale model can be obtained, namely, hrm = hsm = 3.8354 mm and trm = tsm = 2.4384 mm. It can be seen that the geometric scaling factor of stiffeners is equal to that of the skin.

Taking the dimple imperfection diameter of 0.060 m as an example, under three imperfection amplitudes of 0.1, 0.3, and 0.5, the arc-length method in finite element analysis was used to study the partial similitude of axial compression nonlinear buckling of the longitudinal-ring stiffened cylindrical shell for the partial similitude models made of four materials.

It can be seen from Table 7 that, for the scale model made of aluminum under three working conditions consisting of three imperfection amplitudes, the absolute value of the relative error between the critical load of the prototype structure predicted by the scale model based on scaling principle formula (19) and the critical load of the prototype structure is within 1.00%. With the increase of Poisson’s ratio deviation between the scale model and prototype, the relative error of critical load between the prediction prototype structure and the prototype structure increases. When the scale model is made of PVC, the relative error between the critical load of the prediction prototype structure and that of the prototype structure reaches −8.83%.

Table 7: Partial similitude simulation of axial compression nonlinear buckling of the longitudinal-ring rectangular stiffened cylindrical shell.

δ₀ (m)
Material
Critical buckling load (kN·m⁻¹)
Error (%)

Model
Prototype
Prediction prototype

0.1
Aluminum
595.318
6224.06
6269.24
0.73

0.3
500.759
5273.95
5273.45
−0.01

0.5
454.787
4810.45
4789.32
−0.43

0.1
Copper
1055.31
6224.06
6033.68
−3.06

0.3
898.381
5273.95
5136.44
−2.60

0.5
812.553
4810.45
4645.73
−3.42

0.1
Brass
900.281
6224.06
5976.10
−3.98

0.3
767.129
5273.95
5092.24
−3.45

0.5
692.715
4810.45
4598.27
−4.41

0.1
PVC
32.182
6224.06
5674.80
−8.83

0.3
27.270
5273.95
4808.64
−8.82

0.5
24.951
4810.45
4399.72
−8.54

Figure 6 shows the load-displacement curves of the prototype, the four partial similitude scale models, and their corresponding prediction prototypes when the dimple imperfection diameter is 0.060 m and the imperfection amplitude is 0.5. Figure 7 shows the displacement vector and nephogram at the points corresponding to the critical buckling loads of the structural prototype and the partial similitude scale models made of four materials when the imperfection amplitude is 0.5. It can be seen that, for the partial similitude model made of Al, the load-displacement curve of its prediction prototype can accurately predict the load-displacement curve of the prototype structure; the critical buckling load error between the prediction prototype and the prototype is −0.43%; the buckling modes of the model and the prototype at the point corresponding to critical buckling load are the same. With the increase of Poisson’s ratio deviation between the partial similitude scale model and the prototype, the deviation of the load-displacement curve between the prediction prototype and prototype increases gradually. For the scale models made of copper, brass, and PVC, the critical buckling load errors between their prediction prototypes and prototypes are −3.42%, −4.41%, and −8.54%, respectively. The buckling modes of the scale models of the three materials are consistent with those of the prototypes.

(a)

(b)

(c)

(d)

Figure 6: Comparison of partial similitude load-displacement curves for axial compression nonlinear buckling of the stiffened cylindrical shell when δ₀ = 0.5. (a) The model material is aluminum. (b) The model material is copper. (c) The model material is brass. (d) The model material is PVC.

(a)

(b)

(c)

(d)

(e)

(f)

(g)

(h)

(i)

(j)

(k)

(l)

(m)

(n)

(o)

Figure 7: Comparison of buckling modes between the prototype and partial similitude model when λm = 0.060 m and δ₀ = 0.5. (a) Oblique view of the prototype (10x magnification). (b) Front view of the prototype (10x magnification). (c) Near imperfection of the prototype (1x). (d) Oblique view of the aluminum model (10x magnification). (e) Front view of the aluminum model (10x magnification). (f) Near imperfection of the aluminum model (1x). (g) Oblique view of the copper model (10x magnification). (h) Front view of the copper model (10x magnification). (i) Near imperfection of the copper model (1x). (j) Oblique view of the brass model (10x magnification). (k) Front view of the brass model (10x magnification). (l) Near imperfection of the brass model (1x). (m) Oblique view of the PVC model (10x magnification). (n) Front view of the PVC model (10x magnification). (o) Near imperfection of the PVC model (1x).

6. Conclusions

In this paper, the longitudinal-ring rectangular stiffened cylindrical shell is taken as the research object; a scaling finite element model of the stiffened cylindrical shell with dimple imperfections is designed and established according to the generalized similitude conditions and scaling principle formula derived by the energy method, and the nonlinear buckling analysis of structural complete similitude and partial similitude under axial compression is also carried out. The following are the conclusions obtained:

(a)The axial compression nonlinear buckling results of the stiffened cylindrical shell complete the similitude scale model that can accurately predict the buckling characteristics of the prototype structure by combining with the corresponding scaling principle formula, which shows that the generalized similitude conditions and scaling principle formula of structural axial-compression nonlinear buckling complete similitude are correct.(b)The prediction prototype results obtained from the axial compression nonlinear buckling of the stiffened cylindrical shell partial similitude scale model can better predict the buckling characteristics of prototype structures, which shows that the generalized similitude conditions and scaling principle formula of structural axial-compression partial similitude have better accuracy. Meanwhile, the results also show that when the geometric parameters and material parameters are different, the greater the deviation of Poisson’s ratio between the model and the prototype, the greater the error of the calculated results and the worse the coincidence of the load-displacement curves. Therefore, when designing the scale model, the material of the model should be selected as close as possible to Poisson’s ratio of the prototype material, and the analogue prediction of structural axial-compression nonlinear buckling characteristics should be carried out.(c)The generalized similitude conditions and scaling principle formulas of the axial compression nonlinear buckling of stiffened cylindrical shells with dimple imperfections established in this paper can provide a useful reference for the safety assessment of the axial compression nonlinear buckling of similar large-size stiffened cylindrical shells in practical engineering and have certain practical application value.(d)In this study, the material of the structure is regarded as linear elastic. However, plastic buckling is prone to occur in stiffened shells in some cases. So whether the proposed method is suitable for structures considering material nonlinearity and plastic buckling needs further study. In addition, we have noticed some studies [20–22] on nano/microstructure. So it is also worth studying to analyze the scaled nano/microshells and plates with methods of this paper.

Data Availability

The original data required by the fund project cannot be made public and can be made available from the corresponding author upon request.

Conflicts of Interest

The authors declare that they have no conflicts of interest.

Acknowledgments

This work was supported by the National Natural Science Foundation of China (Grant no. 51868013), Natural Science Foundation of Guangxi Province (Grant nos. 2018GXNSFBA138056 and 2018GXNSFAA050145), Guangxi Innovation-Driven Development Special Project (Grant no. GuiKe AA18118008), Science and Technology Project of Guangxi (Grant no. Guike AD19245127), and Doctoral Research Initiation Fund of Guilin University of Technology (Grant no. GUTQDJJ2017034). The authors are grateful for these financial supports.

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