Structural stability and dynamics of FGM plates using an improved 8-ANS finite element.
Functionally graded material (FGM) is a special kind of composites in which the material properties vary continuously and smoothly from one surface to the other. One of the main advantages of FGM is that it mitigates acute stress concentrations and singularities at intersections between interfaces usually presented in laminated composites. Chung and Chi  proposed a sigmoid FGM, which is composed of two power law functions to define a new volume fraction and indicated that the use of a sigmoid FGM can significantly reduce the stress intensity factors of a cracked body. Recent work on the bending, vibration, buckling, and transient analysis of FGM plates can be founded in Han et al. [2, 3] and Jung and Han . Recently, the works on FGM and shear deformation theories with the thickness stretching effect are employed and developed by researchers (Belabed et al. , Hamidi et al. , Lee et al. , and Han et al. ).
It should be noted that they only investigated structural behaviors of simply supported FGM plates. Thus, needs exist for the development of shell finite element which is simple to use for vibration and buckling analysis FGM plates with arbitrary boundary conditions.
When compressive loads are applied onto most structures including FGM plates, they tend to buckle or are subjected to dynamic loads during their operation. Understanding the natural frequency and buckling behavior is an important issue from design perspective. Consequently, numerous studies on vibration and buckling of various plates can be found in literatures. For proper use of FGM plates as various structural components, their dynamic and stability response should be studied. To the best of the author's knowledge, there are no solutions for structural stability response of FGM plates under combined compressive, tensile, and shear loads based on shear deformation theory of plate.
Bucalem and Bathe  improved the MITC8 shell elements  and concluded that while it performed quite effectively in some cases, in a few analyses the element presented a very stiff behavior rendering. In 8-node shell element [11,12], the keeping of locking phenomena was found to continue through numerical solutions on the standard test problem of Macneal and Harder . In order to improve the 8-node ANS shell element, a new combination of sampling points is adopted. Recently, Han et al.  presented modified 8-ANS shell element using the new interpolation functions and combination of sampling points for the assumed natural strain.
However, a few literatures have been found on the dynamic analysis of FGM plates with various boundary conditions and structural stability analysis under combined compressive, tensile, and shear loads. In the present work modified 8-ANS shell element has been employed to study the effect of power law index on dynamic analysis of FGM plates with various boundary conditions and buckling analysis under combined compressive, tensile, and shear loads. To validate the present 8-ANS shell element models, the numerical examples are studied and compared with those results from the references. The solutions of vibration and buckling analysis are numerically illustrated in a number of tables and figures to show the influence of power law index, side-to-thickness ratio, aspect ratio, types of loads, and boundary conditions in FGM structures.
2. Modified 8-ANS Finite Element
2.1. Kinematics of Shell. The displacement U of an arbitrary point of the shell (see Figure 1) for the first-order shear deformation theory can be expressed
[bar.u] ([[xi].sup.[alpha]]) = u([[xi].sup.[alpha]]) + ([[xi].sub.3][phi]([[xi].sup.[alpha]]), (1)
where [phi] is vector of rotation at the midsurface of shell.
A three-dimensional Green's strain tensor in the linear case (infinitesimal strain theory) is given by
2[E.sub.ij] = [[bar.u].sub.,i] x [g.sub.j] + [[bar.u].sub.,j] x [g.sub.i], (2)
where a comma [().sub.,i] = [partial derivative]/[partial derivative][[xi].sup.i] is partial differentiation and [g.sub.i] is a triad of base vectors for the spatial coordinates [[xi].sup.i] at the surfaces ([[xi].sub.3] = const.) parallel to the midsurface of shell. If the displacement equation (1) is substituted into (2), the strain-displacement relations are obtained. From these strain-displacement relations, kinematics in different curvilinear coordinates can be acquired and expressed through the physical components in the matrix form
E = BU, (3)
where U are physical components of displacement u and rotation [phi] as follows:
[U.sup.T] = [[u.sub.1], [u.sub.2], [u.sub.3], [[phi].sub.1], [[phi].sub.2], [[phi].sub.3]]. (4)
The shell theory presented above is the so-called first-order shear deformation theory with six degrees of freedom.
2.2. Various Enhanced Strain Interpolation Patterns. In this study, the ordinary 8 nodes of Lagrangian displacement interpolations are used and the various combinations of assumed natural strain interpolation functions are employed for the very efficient 8-node shell element. Figure 2 shows various patterns of sampling points that can be used for membrane, in-plane shear, and out-of-plane shear strain interpolations for the new 8-ANS finite element. Based on Figure 2, the [beta] pattern is used for membrane and the [delta] pattern and [[gamma].sup.*.sub.6] pattern are used for in-plane and out-of-plane shear, respectively. The interpolation functions by Polit et al.  are used in the [[gamma].sup.*.sub.6] patterns. In the [[gamma].sup.*.sub.6] patterns, the strain component of center point is replaced by the mean of the components at points S1 and [S.sub.2] (Bathe and Dvorkin, ).
3. Material Properties of the FGM
An FGM can be defined by the variation in the volume fractions. In this paper, the sigmoid function is used for FGM structures. The volume fraction using two power law functions which confirm smooth distribution of stresses is defined by
[MATHEMATICAL EXPRESSION NOT REPRODUCIBLE IN ASCII], (5a)
[MATHEMATICAL EXPRESSION NOT REPRODUCIBLE IN ASCII], (5b)
where subscripts 1 and 2 represent the two materials used and p is the power law index, which indicates the material variation profile through the thickness. The material properties of the S-FGM using the rule of mixture can be expressed as follows:
[MATHEMATICAL EXPRESSION NOT REPRODUCIBLE IN ASCII], (6a)
[MATHEMATICAL EXPRESSION NOT REPRODUCIBLE IN ASCII]. (6b)
4. Equilibrium Equation
By using virtual work principle, the equilibrium equation is obtained based on the membrane (N), bending (M), and transverse shear resultant forces (Q) as follows:
[MATHEMATICAL EXPRESSION NOT REPRODUCIBLE IN ASCII], (7)
where [E.sup.m.sub.[alpha][beta]], [E.sup.b.sub.[alpha][beta]], and [E.sup.s.sub.[alpha]3] are membrane, bending, and transverse shear strain components, [K.sub.L] is the linear stiffness matrix, and f is the body force.
5. Buckling and Vibration Analysis
When the equation is employed to estimate buckling loads, the stability condition may be simplified by
[K.sub.L][u.sup.a] + [[gamma].sub.cr][Gu.sup.a] = 0, (8)
where [u.sup.a] is the vector of the nodal value of the displacements, [[gamma].sub.cr] is the buckling load parameter and denotes the proportional increase in load needed to reach neutral equilibrium, and G is the geometric stiffness matrix. Applying to the structure a reference loading [N.sub.ref] and carrying out a generalized linear static analysis, (8) represents the standard eigenvalue problem. The lowest eigenvalue [[lambda].sub.cr] in (8) is associated with buckling load. Therefore, the buckling load can be obtained by
[N.sub.cr] - [[lambda].sub.cr] [N.sub.ref]. (9)
The consistent mass is used to formulate the mass matrices for the FGM shell element. The mass matrix is determined using interpolation functions as follows:
M = [[integral].sub.V] [[rho][N.sup.T]N dV, (10)
where N is a matrix of shape functions.
Unlike (8), the governing equations of motion for free vibration analysis are of the form
[K.sub.L][u.sup.a] + M[[??].sup.a] - 0, (11)
where the superposed dot denotes differentiation with respect to time.
6. Numerical Results
6.1. Patch Test. Firstly, the patch tests proposed by Simo et al.  are investigated. In Figure 3, the boundary conditions and loading types are presented, simultaneously. The normalized solutions of nodal displacements on the right edges are shown in Table 1. The nondimensional form is expressed as follows:
Normalized solution = Present solution/Reference solution. (12)
6.2. Vibration Analysis
6.2.1. Simply Supported Rectangular FGM Plate. To validate the present 8-ANS finite element with FGM, a sigmoid FGM plate with geometrical properties is shown in Figure 4. The material properties are given by
[MATHEMATICAL EXPRESSION NOT REPRODUCIBLE IN ASCII], (13)
where [E.sub.1], [[rho].sub.1], [v.sub.1]] and [E.sub.2], [[rho].sub.2], [v.sub.2] express the property of the top and bottom faces of the plate, respectively. Equation (13) is used in computing the numerical values of all cases.
The nondimensional form of the results is defined by
[bar.[omega]] = [omega] ([a.sup.2]/h [square root of [[rho].sub.1]/[E.sub.2]]). (14)
Table 2 shows the nondimensional natural frequency of S-FGM simply supported plates for convergence test. It is noticed that present 8-ANS finite element shows an excellent agreement to the result by analytical solution.
It is shown that the natural frequency of pure metal plate is smaller than that of pure ceramic plate in Table 3. The natural frequencies of the functionally graded material plates are intermediate to that of the metal and ceramic plates. Table 3 shows that numerical results of vibration analysis are reduced by increasing the power law p.
Table 4 shows the numerical results of FGM plate for which p = 10. In this example, the natural frequency is normalized with respect to the plate width a, thickness h, density [[rho].sub.1], and elastic modulus [E.sub.2] for various rectangular plate aspect ratios. As the plate aspect ratio increases, the natural frequency reduces and approaches 3.69.
6.2.2. FGM Plate with Arbitrary Edges. For convenience, a four-letter notation is used to describe the boundary conditions of the edges (see Figure 5). For example, CFSF indicates that first edge is clamped (C), second edge is free (F), third edge is simply supported (S), and the last is free (F). The natural frequencies of FGM CFFF plates are investigated and presented in Table 5. The results are expressed in the nondimensional form using (15). Numerical results show that the natural frequencies are reduced by increasing the power law index p. The results also confirm that power law index has significant effect on the dynamic response of FGM plates:
[bar.[omega]] = [omega] ([a.sup.2]/h [square root of [[rho].sub.1]/[E.sub.2]]) x 10. (15)
In Table 6, the natural frequencies of FGM plates with arbitrary boundary conditions are presented. Four arbitrary values of the power law index p are examined. As expected, results show that the natural frequencies are reduced by increasing the power law index p.
Based on present study, comprehensive results of natural frequency of FGM plates are also illustrated in Figure 7 for different boundary conditions. In each boundary condition, five different power law indices are considered. In Figure 8, two different values of side-to-thickness ratio are examined. In addition, five arbitrary values of the power law index are examined. These new results can be used for comparison with further FG plate models.
6.3. Buckling Analysis
6.3.1. Simply Supported Rectangular FGM Plate. For validation, the stability analysis results of S-FGM simply supported plates (see Figure 4) using Navier's method are compared with present 8-ANS finite element. The material properties and nondimensional form are used as shown in Section 6.2.1 and (14), respectively. It is shown that the pure ceramic plate has the largest buckling load and the pure metal plate has the smallest one in Table 7. The buckling loads of the FGM plates are intermediate to that of the metal and ceramic plates.
The buckling loads versus the plate aspect ratio are presented in Table 8. There, for large plate aspect ratios (i.e., b/a [greater than or equal to] 2.0), the plate buckles into a single half wave in the x-direction. As the plate aspect ratio decreases, the plate buckles with increasing half waves in the x-direction.
6.3.2. FGM Cantilever Plate. In Table 9, the stability analysis results of S-FGM cantilever plates (see Figure 6) with various aspect ratio are presented. The results are presented in the nondimensional form. Numerical results show that the buckling loads are reduced by increasing the power law index p. The results also confirm that power law index has significant effect on the buckling loads of FGM cantilever plates. The stability analysis results of S-FGM cantilever plates under various loading types are investigated in Table 10. As expected, numerical results show that the buckling loads are reduced by increasing the power law index p and also confirm that loading types have very significant effect on the buckling loads of FGM cantilever plates.
Based on present study, comprehensive results of buckling loads of FGM plates under combined loads are also illustrated in Figures 9 and 10 for CFFF boundary conditions. The influence of in-plane load direction on the relationship between critical shear and in-plane loading is studied, when acting in combination. It is noticed that the tension may produce positive stiffness and the FGM plate becomes stronger than when it is subjected to compression.
In Figure 10, the natural frequencies of FGM plates under combined loading are investigated. Four arbitrary values of the power law index p are examined. As expected, results show that the buckling loads are increased by decreasing the power law index p.
7. Concluding Remarks
The natural frequency and buckling response have been studied for FGM plates. Extensive results obtained from computations refer to different loading, different geometry, different boundaries, and different power law indices. The advanced finite element analysis based on the modified 8node ANS formulation shows the significance of various boundary conditions and loading conditions for FGM plates. From this study, a number of conclusions have been founded.
(1) It is shown that the natural frequencies are reduced by increasing the power law index p. The results also confirm that power law index has significant effect on the dynamic response of FGM plates.
(2) Dynamic response of FGM plates is affected by its boundary conditions. Clamped edges always produce a higher performance of the FGM plates than simply supported edges.
(3) It is noticed that the tension may produce positive stiffness and the FGM plate becomes stronger than when it is subjected to compression. For combined shear and compressive loading the stability envelopes are symmetric about the line [N.sub.xy].
(4) The suitable selection of sampling point used in ANS method is very important for vibration and buckling behavior of FGM plates. It is noticed that locking phenomenon occurs in the results of reference when the plates become very thin. This phenomenon may lead us to a conclusion that the suitable selection of sampling points prevents the locking problem from occurring in vibration and buckling analysis of either thick FGM plates or very thin ones.
In order to design the FGM plates under the in-plane shear loading, the present formulation and results may serve as benchmark for future guidelines and may be extended to dynamic instability analysis of various FGM structures. The numerical results of present study may serve as benchmark for future guidelines in designing FGM plates under compressive, tension, shear, and combined loading with arbitrary boundary conditions. Also, the present theory should provide engineers with the capability for the design of various FGM plates and shells.
The author declares that there are no competing interests regarding the publication of this paper.
This work was supported by the research grant of the Kongju National University in 2015.
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Division of Construction and Environmental Engineering, Kongju National University, 275 Budai, Cheonan 330-717, Republic of Korea
Correspondence should be addressed to Weon-Tae Park; email@example.com
Received 22 April 2016; Accepted 7 June 2016
Academic Editor: Guillermo Rus
Caption: Figure 1: Kinematics of the first-order shear deformation theory.
Caption: Figure 2: Four possible patterns of sampling points for 8-node ANS shell element.
Caption: Figure 3: Mesh for patch test (Simo et al. ). Length of the square L = 10; Young's modulus E = 1.0 x [10.sup.7]; Poisson's ratio v = 0.3; and thickness h = 1.0 and boundary displacement conditions for patch tests.
Caption: Figure 4: Geometry of FGM plates.
Caption: Figure 5: Geometry of FGM cantilever plates.
Caption: Figure 6: FGM cantilever plates under combined loads.
Caption: Figure 7: Effect of power law index on the nondimensional natural frequency of FGM plate with arbitrary edges.
Caption: Figure 8: Effect of power law index on the nondimensional natural frequency of CCFF FGM plate with variation of side-to-thickness ratio.
Caption: Figure 9: Buckling load of FGM plates: combined compressive, tensile, and shear loading.
Caption: Figure 10: Buckling load of FGM plates with various power law index: combined compressive and shear loading.
Table 1: Results of patch test under bending, shear, and tension. Patch tests Bending Shear Reference solutions [[theta].sub.y] ML- w = 6SL-5GA = 0.312 x EI = 0.12 x [10.sup.-5] [10.sup.-4] Normalized solutions 1.000 1.000 Patch tests Tension Reference solutions u = TL-EA = 1.0 x [10.sup.-6] Normalized solutions 0.992 Table 2: Normalized nondimensional natural frequency of S-FGM plate (power law index: p = 10). Nodes per side 4-node shell Ratio (/ element (see exact) ) (b) 5 8.076 1.105 9 7.517 1.029 17 7.366 1.008 33 7.329 1.003 Analytical 7.307 -- solution (a) Nodes per side Present Ratio (present/exact) 5 7.717 1.056 9 7.351 1.006 17 7.323 1.002 33 -- -- Analytical -- -- solution (a) (a) Result is computed using Navier's method with first-order shear deformation theory, independently. (b) Results are computed using the quasi-conforming 4-ANS finite element, independently. Table 3: Nondimensional natural frequency of simply supported FGM plates (a/h = 100). Mode number Material Navier 1 parameter (p) solution Ref.  Present Pure ceramic 8.992 (a) 9.041 (a) 8.772 P = 1 7.518 7.555 7.526 P = 2 7.419 7.457 7.430 p = 5 7.333 7.373 7.348 p= 10 7.307 7.348 7.323 Pure metal 6.123 (a) 6.148 (a) 6.287 Mode number Material 2 3 parameter (p) Ref.  Present Ref.  Present Pure ceramic 22.705 (a) 21.940 22.705 (a) 21.940 P = 1 18.992 18.819 18.993 18.820 P = 2 18.745 18.575 18.747 18.576 p = 5 18.533 18.365 18.535 18.367 p= 10 18.470 18.302 18.472 18.304 Pure metal 15.459 (a) 15.726 15.459 (a) 15.726 (a) Results are calculated by [rho] = ([[rho].sub.1] + [[rho].sub.2])l2. Table 4: Nondimensional fundamental frequency of simply sup -ported FGM plates with various aspect ratio (p = 10). Solutions Aspect ratio (b/a) 0.5 2.0 5.0 10.0 Navier solution 18.258 4.568 3.800 3.691 Ref.  18.346 4.593 3.817 3.706 Present 18.276 4.577 3.803 3.692 Table 5: Nondimensional natural frequency of FGM CFFF plates (a/h = 100). Mode number Material 1 2 parameter (p) Ref.  Present Ref.  Present Pure ceramic 15.814 (a) 15.430 38.767 (a) 37.780 P = 1 13.222 13.228 32.415 32.389 P = 2 13.047 13.052 31.986 31.960 p = 5 12.896 12.901 31.617 31.590 p= 10 12.851 12.856 31.507 31.480 Pure metal 10.767 (a) 11.060 26.395 (a) 27.079 Mode number Material 3 4 parameter (p) Ref.  Present Ref.  Present Pure ceramic 97.148 (a) 94.570 124.28 (a) 120.80 P = 1 81.236 81.074 103.92 103.56 P = 2 80.166 80.000 102.54 102.19 p = 5 79.244 79.073 101.36 101.00 p= 10 78.969 78.797 101.01 100.65 Pure metal 66.144 (a) 67.785 84.615 (a) 86.584 (a) Results of  are calculated by [rho] = ([[rho].sub.1] + [[rho].sub.1])/2. Table 6: Nondimensional natural frequency of FGM plates (a/h = 100). Boundary conditions Material parameter (p) CFFF SSFF SSSS CCFF CCSS Pure ceramic 15.430 54.302 87.718 98.502 128.59 P = 1 13.228 46.643 75.264 84.446 110.25 P = 2 13.052 46.078 74.304 83.327 108.79 P = 5 12.901 45.591 73.478 82.364 107.53 p = 10 12.856 45.446 73.231 82.077 107.15 Pure metal 11.060 38.922 62.873 70.603 92.176 Table 7: Nondimensional buckling loads of FGM simply supported plates ([[bar.N].sub.cr] = [N.sub.cr][b.sup.2]/[E.sub.2][hs.up.3]). Material parameter (p) Navier Ref.  Present solution Pure ceramic 7.794 7.828 7.797 P = 1 5.448 5.484 5.466 P = 2 5.305 5.346 5.331 P = 5 5.183 5.229 5.216 p=10 5.147 5.195 5.182 Pure metal 3.613 3.629 3.615 Table 8: Nondimensional buckling loads of FGM simply supported plates ([[bar.N].sub.cr] = [N.sub.cr][b.sup.2]/[E.sup.2][h.sup.3], p = 10). Solutions Aspect ratio (b/a) 0.5 2.0 5.0 10.0 Navier solution 5.138 8.043 34.800 131.28 Ref.  5.211 8.127 34.969 131.87 Present 5.165 8.110 34.859 131.37 Table 9: Nondimensional buckling loads of FGM plates ([[bar.N].sub.cr] = ([N.sub.cr][b.sup.2]/[E.sub.2][h.sup.3]) x 10). Aspect ratio (b/a) Material 1 2 parameter (p) Ref.  Present Ref. * Present Pure ceramic 4.693 4.679 9.551 19.040 P = 1 3.281 3.271 6.677 13.310 P = 2 3.194 3.185 6.501 12.959 p = 5 3.121 3.111 6.351 12.660 p= 10 3.099 3.090 6.307 12.572 Pure metal 2.176 2.169 4.428 8.8265 Aspect ratio (b/a) Material 5 10 parameter (p) Ref. * Present Ref. * Present Pure ceramic 24.160 120.75 48.449 485.42 P = 1 16.890 84.411 33.872 339.32 P = 2 16.445 82.185 32.981 330.38 p = 5 16.067 80.293 32.224 322.77 p= 10 15.955 79.733 32.000 320.52 Pure metal 11.200 55.979 22.460 225.03 * Results of  are calculated by ([[bar.N].sub.cr] = [N.sub.cr][a.sup.2]/[E.sub.2][h.sup.3] (b/a) x 10. Table 10: Nondimensional buckling loads of FGM plates ([[bar.N].sub.cr] = ([N.sub.cr][b.sup.2]/[E.sub.2][h.sup.3]) x 10). Types of combined loading Material Compression Shear + comp. parameter (p) Present Present Pure ceramic 4.679 4.279 P = 1 3.271 2.991 P = 2 3.185 2.912 p = 5 3.111 2.845 p = 10 3.090 2.826 Pure metal 2.169 1.984 Types of combined loading Material Pure shear Shear + tension parameter (p) Present Present Pure ceramic 15.135 95.116 P = 1 10.580 66.495 P = 2 10.302 64.745 p = 5 10.065 63.257 p = 10 9.9946 62.816 Pure metal 7.0163 44.094
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|Title Annotation:||Research Article|
|Publication:||Advances in Materials Science and Engineering|
|Date:||Jan 1, 2016|
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