1. Introduction

OJCE

Open Journal of Civil Engineering

2164-3164

Scientific Research Publishing

10.4236/ojce.2020.102010

OJCE-99761

Articles

Engineering

Von Misses Pure Shear in Kirchhoff’s Plate Buckling

Tonye

Ngoji Johnarry

¹Francis

Williams Ebitei

Retired, Rivers-State University, Port-Harcourt, Nigeria

University of Nigeria, Nsukka, Nigeria

27032020

10021051163, March 202023, April 2020 26, April 2020

2014

This work is licensed under the Creative Commons Attribution International License (CC BY). http://creativecommons.org/licenses/by/4.0/

The pure shear strength for the all-simply supported plate has not yet been found ; what is described as pure shear in that plate, is, in fact, a pure-shear solution for another plate clamped on the “Y-Y” and simply supported on the long side, X-X. A new solution for the simply supported case is presented here and is found to be only 60-percent of the currently believed results. Comparative results are presented for the all-clamped plate which exhibits great accuracy. The von Misses yield relation is adopted and through incremental deflection-rating the effective shear curvature is targeted in aspect-ratios. For a set of boundary conditions the Kirchhoff’s plate capacity is finite and invariant for bending, buckling in axial and pure-shear and in vibration.

Rectangular Plate Kirchhoff’s Plate-Differentials Deflection Buckling Pure-Shear Von Misses

1. Introduction

Plate-bending is expertly covered by Timoshenko and Krieger [1], 1959, including the contributions of many other authors. Deflection-rating of plates will continue to rely heavily on these works. The treatise of Arthur W. Leissa [2], 1985, Ohio State University for Wright-Patterson Air Force Base-Flight Dynamics Laboratories gives a comprehensive discourse in buckling, encompassing shear-buckling and the Euler one-dimension case and citing the works and results of many others; no new pure shear solution was offered. Additionally an extensive review of shear buckling in isotropic plates by D.L. Johns [3] is available; the important correlation between the results and von Misses shear was not discussed. Mansour and Thayamballi for the Ship Structure Committee [4] in their 1980-document shed light on pure-shear plate-buckling in relation to the use of stiffeners, as in Figure 1. This present study is assuming that a stiffener-line and a simple-support line behind it amounts to zero-slope boundary, θ xx-support = 0 , in effect clamping. By the intervention of stiffeners the basic all-simply supported plate was interrupted.

Timoshenko’s results for Figure 1 case were quoted [4],

N x y = D π 2 [ 5.35 + 4 / ( b / a ) 2 ]

this, as the all-simply-supported plate, appears to make no adjustment for the absence of the stiffeners. For a square plate “ N x y = 9.35 D π 2 ”, this formula persists to date.

Piscopo [5] addressed the pure shear solution in the fashion of Timoshenko where the governing equation, “ D ∇ 4 w = ( N x y ) ( 2 ∂ 2 w / ∂ x ∂ y ) ” is enhanced as Equation (1)

D ∇ 4 w = N x y ( β ∂ 2 w / ∂ x 2 + 2 ∂ 2 w / ∂ x ∂ y ) (1)

but a direct equilibrium solution for the latter has never been found. Incidentally, there appear to be some conflicts between Equation (1) and von Misses yield relation of Equation (2)

σ v m 2 = ( 1 / 2 ) [ ( σ 1 − σ 2 ) 2 + ( σ 2 − σ 3 ) 2 + ( σ 3 − σ 1 ) 2 ] (2)

σ v m = ( σ 1 2 + σ 2 2 + σ 1 σ 2 ) 1 / 2 , in the “ σ 1 − σ 2 ” plane

A degenerate form of this equation for “ σ compression ≫ σ tension ”, is

σ v m = β σ 1

or in terms of curvature,

X v m = β X 1 (3)

Find “ X 1 = X effective ” and the pure shear problem is solved in the “von Misses/Kirchhoff’s” framework. So Equation (1) is consumed by Equation (3), leading to,

D ∇ 4 w = ( N x y ) { β ( ∂ 2 w / ∂ x 2 ) effective } = ( N x y ) ( X V M ) (4)

Equation (4) is now the new standard pure-shear equation.

The present study starts with the buckling problem but assumes a great familiarity in the bending-deflection cases. Deflection factors are related to the desired curvatures. The deflection-factors employed emanate from the capacity of the Kirchhoff’s plate differentials which form the basis of all analyses, analytical or numerical finite-elements; these factors, when found, are easily recognizable, confirming that solutions are on track. Also, a fast approximate spot-buckling-solution is necessary for additional checks; Mohr’s loading curvature-circles (Figure 2) are devised to meet this.

The Kirchhoff’s plate capacity is constant whether in shear or axial compression, so there is no need to engage in a new extensive independent analysis in shear where von Misses shear solution can be invoked. The pure-shear plate buckling is hugely significant on account of the heavy demands on heavier and heavier ships and their platting.

2. Applicable Equations

Equation (5), is the existing uniaxial buckling equation. The biaxial case, Equation (6) ensues if “N_xy” = 0

D ( ∂ 4 w / ∂ x 4 + 2 ∂ 4 w / ∂ x 2 ∂ y 2 + ∂ 4 w / ∂ y 4 ) = H = ( N x ) ( ∂ 2 w / ∂ x 2 ) (5)

D { ∂ 4 w / ∂ x 4 + 2 ∂ 4 w / ∂ x 2 ∂ y 2 + ∂ 4 w / ∂ y 4 } = H = N x ∂ 2 w / ∂ x 2 + N x y ( 2 ∂ 2 w / ∂ x ∂ y ) + N y ∂ 2 w / ∂ y 2 (6)

The shear loading—Equation (7) is balanced in the same way as the biaxial case.

D { ∂ 4 w / ∂ x 4 + 2 ∂ 4 w / ∂ x 2 ∂ y 2 + ∂ 4 w / ∂ y 4 } = H = N x y ( 2 ∂ 2 w / ∂ x ∂ y ) (7)

Under equivalent uniformly distributed transverse loading, q * , Equation (8) ensues

D { ∂ 4 w / ∂ x 4 + 2 ∂ 4 w / ∂ x 2 ∂ y 2 + ∂ 4 w / ∂ y 4 } = H = q * (8a)

Equations (5)-(8) are summarized as,

H x x + H x y + H y y = H = RHS ( loading ) (8b)

2.1. Capacity of the Kirchhoff’s Plate Differentials, “H”

By giving finite values of the left-hand differentials, the capacity of a Kirchhoff’s plate ensues; this is achieved through valid deflection shape-functions, “w”

∂ 4 w / ( ∂ x 4 ) ( 1 ) = ∬ w ( ∂ 4 w / ∂ x 4 ) ∂ x ∂ y ∬ w ∂ x ∂ y = H x x (9)

( ∂ 4 w ) / ( ∂ y 4 ) ( 1 ) = ∬ w ( ∂ 4 w / ∂ y 4 ) ∂ x ∂ y ∬ w ∂ x ∂ y = H y y (10)

( 2 ∂ 4 w ) / ( ∂ x 2 ∂ y 2 ) ( 1 ) = ∬ 2 w ( ∂ 4 w / ∂ x 2 ∂ y 2 ) ∂ x ∂ y ∬ w ∂ x ∂ y = H x y (11)

( ∂ 2 w ) / ( ∂ x 2 ) ( 1 ) = ∬ w ( ∂ 2 w / ∂ x 2 ) ∂ x ∂ y ∬ w ∂ x ∂ y = X x (12)

( ∂ 2 w ) / ( ∂ y 2 ) ( 1 ) = ∬ w ( ∂ 2 w / ∂ y 2 ) ∂ x ∂ y ∬ w ∂ x ∂ y = X y (13)

X 1 , 2 = ( X x + X y ) / 2 ± [ { ( X x − X y ) 2 / 2 } 2 + { ( X x y ) / 2 } 2 ] ; principal curvatures;

(14a)

Or by reference to the Mohr’s circle,

X 1 , 2 = ( X x + X y ) / 2 ± R ; R = Mohr’s circle radius (14b)

The average curvature, ( X x + X y ) / 2 , is found significant as an intermediate loading curvature when “ X x < X y ” over the range of “ X y > X x ” in uni-axial X-loading. For the bi-axial case, X biaxial = ( X x + X y ) .

These integrals are the outcomes of criterion of buckling as relative-curvature/ deflection resonance. A typical buckling resistance integral is,

( ∂ 4 w ) / ( ∂ x 4 ) ( 1 ) = C x d 4 ( w x x - r / w ) = C x d 4 ( R x c d ) (15)

The ratio, “ ( w x x - r / w ) = R x c d ” must always be a scalar or else the function-w is inadmissible. The function-w is chosen as to make the ratio, ( w x x - r / w ), a scalar. The domain compliant factor at resonance, C_xd₄, is what is left to be found. Multiply both sides of Equation (16) and integrate to find it.

C x d 4 R x c d = [ ( ∂ 4 w / ∂ x 4 ) 1 ] = [ ∬ w ( ∂ 4 w / ∂ x 4 ) ∂ x ∂ y ∬ w ∂ x ∂ y ] (16)

2.2. Buckling Potential Limits

Three possibilities are identified relative to X- and Y-axes in emulating the reactive potentials “ ∂ 4 w / ∂ x 4 ; 2 ∂ 4 w / ∂ x 2 ∂ y 2 ; ∂ 4 w / ∂ y 4 ”.

1) σ x X x

This is first in contention in uni-axial X-compression; this case easily solves Equation (5).

2) σ y X y

This is out of contention when no load is applied in the Y-axis, whatever the value of “ X y ”.

3) σ x X a v

This “average loading-curvature” situation will always happen and also in contention. (1) and (3) are identified in the Mohr’s diagram, Figure 2.

In effect, two curvature-loading circles ( X x , X a v ) are operative and the larger circle gives the required solution for “N_x”. This process softens the stiff constraint that the wave numbers “m, n”, must be whole

2.2.1. The Curvature, “ ( ∂ 2 w / ∂ x 2 ) c r ”, in X-Compression

The solution of Equation (5) is easy when

( ∂ 2 w / ∂ x 2 ) ≥ ( ∂ 2 w / ∂ y 2 ) ; and X x = X c r = ( ∂ 2 w / ∂ x 2 )

When

( ∂ 2 w / ∂ x 2 ) < ( ∂ 2 w / ∂ y 2 )

“ X 1 ” may be interpreted as “effective principal loading curvature”.

So, Figure 2, explains Mohr’s loading-curvature, supplying the critical curvatures, exact or near-exact; exact if X x ≥ X y . with X-as major direction of compression.

2.2.2. X-Curvature, “ ( ∂ 2 w / ∂ x 2 ) c r ” from Deflection-Rating

Relying on the deflection coefficients, Δ 1 , Δ 2 at two consecutive locations, “i” and “i + 1”, Figure 3(a), the curvature at the second location may be found from Equation (17)

( Δ 1 / A 1 ) ( X x , 1 ) = ( Δ 2 / A 2 ) ( X x , 2 ) (17)

A₂/A₁ = C_A, stressed boundary lengths-ratio representing side areas: Figure 3(b) and Figure 3(c).

Aspect ratio, “s*” gap of 25-percent can be tolerated.

This equation is similar to Equation (5) as “(Force/Area)(curvature) = Constant” = Kirchhoff’s plate-capacity.

2.3. Deflection-Factor as Part of Buckling Solution

From Equation (5),

D ( ∂ 4 w / ∂ x 4 + 2 ∂ 4 w / ∂ x 2 ∂ y 2 + ∂ 4 w / ∂ y 4 ) = H = ( N x ) ( ∂ 2 w / ∂ x 2 ) = q *

For a given plate-function the “LHS” is invariant and once computed can be used for bending, buckling and vibration; “ q * ” is equivalent uniform transverse pressure. That is, deflection,

Δ = ( 1 / H ) ( w shape )

the primitive value is sufficient. The familiarity of “ Δ -value” gives confidence the solution is on track.

2.4. Buckling in Pure ShearElementary Statics and Pure Shear—“CCCC” Plate

Figure 4(a) for a square plate; the applied pure-shear is transformed into compression/tension loading of an inner square.

Invoke the already known solution on the inner square, Figure 4(a), relying on compression, that is, with N_cr.= 10.66𝜌

2N_xycos45 = (10.66) (1/(0.707b)²); in Ref [2], “10.47” replaces “10.66”

N_xy = 15.08; cf. {14.81ρ, [2] }; the minor difference stems from differences in the deflection shape. Figure 4(b) shows the shear and effective normal stress circles.

For automatic values at any aspect-ratio, simply multiply “ X e ” by the von Misses shear factor of “ 1 / 2 ” and complete Table 1 or, indeed, Table 2 or any tables.

Table 1 “CCCC” plate and s*; Nx = DKcr.; “ X ” from “ Δ ”; ( Δ i ≡ w s h / H )

s* (1)	Δ s ∗ (2)	C_A (3)	X Δ (4)	H (5)	K_cr ([Ref. [4] ) (6)	( δ X / δ Δ ) = monitor (7)	2 X x y = 0.707 X Δ (8)	N_xy = (5)/(8) “Pure-shear” (9)
1	0.00128		29.61	3116.8	10.66ρ, [10.4]	-	20.93	15.0; ( [4] = 14.8)
1.25	0.00186	1.05	21.72	2146.2	10.01ρ, [9.9]	−13, 600.0
1.5	0.00229	1.071	19.00	1746.0	9.3ρ, [9.3]	− 6, 325.6
1.75	0.00258	1.055	18.06	1547.85	8.68ρ, [8.6]	− 3, 241.4
2.0	0.002784	1.053	17.88	1436.65	8.14ρ, [8.0]	−900.0	12.64	11.5
2.25	0.002923	1.051	17.88	1368.3	7.75ρ, [7.7]	0
2.35	0.002967	1.019	17.88	1348.2	7.64𝜌	0
2.45	0.003005	1.019	17.88	1331.05	7.54𝜌	0
2.5	0.003022	1.009	17.88	1323.39	7.50ρ, [7.5]	0
2.75	0.00309 (0.00302)	1.045	18.24 (17.88)	1292.5	7.32𝜌	+493.2, δ X / δ Δ = min, so, δ Δ = 0	12.64	10.3; ( [4] = 9.8)
3	0.00302	1.0526	18.70 (17.88)	1292.5	7.32ρ, [7.35]	“H, X ”, move together

Table 2 “SSSS” plate and s*; Nx = DKcr.; “ X ” from “ Δ ”; ( Δ i ≡ w s h / H )

s* (1)	Δ (2)	C_A (3)	X Δ (4)	H (5)	K_cr; (Ref. [4] ) (6)	( δ X / δ Δ ) = monitor (7)	2 X x y = 0.7 X Δ (8)	N_xy (ref. [2] ) “Pure-shear” (9)	Mass = m ∗ = ∬ w w / ∬ w (10)	ω² = fundamental m = n = 1 (5)/(10) (11)
1	0.00416	-	6.0875	240.34	4.0ρ [4ρ]	-	4.3	5.66ρ [9.3ρ]	0.617	389
1.25	0.00619	1.06	4.337	161.60	3.78 [>4ρ]	−862
1.50	0.00798	1.06	3.566	125.36	3.56 [>4ρ]	−431
1.75	0.00948	1.055	3.174	105.73	3.375 [>4ρ]	−265
2.0	0.0106	1.051	2.977	93.73	3.195 [4ρ]	−173			0.617	152
2.25	0.0116	1.051	2.859	86.11	3.05 [>4ρ]	−118
2.50	0.01236	1.0048	2.812	80.85	2.91ρ	−61.8
2.75	0.0130	1.046	2.797	77.02	2.79ρ	−23.4
3.00	0.0135	1.043	2.797	74.18	2.69 [4ρ]	−0.0
3.25	0.0139 (0.0135)	1.04	2.83 (2.797)	72.0	2.60ρ	+82.5, ( δ X / δ Δ = min, so, δ Δ = 0)	2.0	3.65ρ [5.3ρ]	0.617	117
3.50	0.0135				2.60	(“H, X ” move together)

The “SSSS” case for “s* = 1” in Table 2 show results much smaller than those of Timoshenko, 5.66ρ here to 9.35ρ of Ref. [2].

3. Illustration: Axial Compression3.1. The “SSCS” Plate, <xref ref-type="fig" rid="fig5">Figure 5</xref>

1) W = ( sin G x / a + A x / a ) ( sin n π y / b ) ; n = 1 , 2 , 3 , ⋯ ; G = 4.5; A = 0.977.

2) ∬ w ∂ x ∂ y = 0.482 。

3) ∬ w ( ∂ 4 w / ∂ x 4 ) ∂ x ∂ y 1 = 0.225 G 4 / a 4 .

4) ∬ w ( ∂ 4 w / ∂ y 4 ) ∂ x ∂ y 1 = 0.384 n 4 π 4 / b 4 .

5) ∬ 2 w ( ∂ 4 w / ∂ x 2 ∂ y 2 ) ∂ x ∂ y 1 = 0.45 n 2 G 4 / a 2 b 2 .

6) ∬ w ( ∂ 2 w / ∂ x 2 ) ∂ x ∂ y 1 = 0.225 G 2 / a 2 .

7) ∬ w ( ∂ 2 w / ∂ y 2 ) ∂ x ∂ y 1 = 0.384 n 2 π 2 / b 2 .

H = H x x + H x y + H y y = 191.42 + 186.6 + 77.6 = 455.6 ; { Δ fund = w s h / H = 0.00278 q * b 4 / D } ; X x = 9.45 ; X y = 7.687 ; X x , c r = 9.45 ; so: N x , c r = 455.6 / 9.45 = 48.2 = ( 4.88 ρ ) ( ρ ) .

Confirm that “ Δ fund ” is correct, cf., (0.0028) [1]; this is important.

Since, also, “ X x > X y ” the result found must be exact or near-exact. Ref. [2] includes the result of “(4.85ρ)” from another source.

Check Pure Shear, N x y = H / ( 2 X x y )

Find “ 2 X x y ” by von Misses as

2 X x y = ( 1 / 2 ) ( X x -effective ) = 0.707 × 9.45 = 6.681

N x y = 455.6 / 6.681 = 6.91 ρ

for “SSCS at a/b = 1”.

3.2. The “CCCC”: Δ -Method

W = ( 1 − cos m π x / a ) ( 1 − cos n π y / b ) ; m , n = 2 , 4 , 6 , ⋯

a / b = 1 ;

1) Uniaxial compression; H_xx = 1168.8; H_xy = 779.2; X x = X y = X c r = 29.61 ; H_yy = 1168.8; H = 3116.8; N s * = 1 = 31168.8 / 29.61 = 10.66 ρ ; Δ c = 0.00128 ; cf, (0.00126) [1]; the nearness of the primitive- Δ to the final- Δ , (0.00128 to 0.00126), confirms “H” on which “N_x” depends. Further, the exactness of the w-function is verified.

2) In pure-shear

N x y = 3116.8 / ( 0.707 × 29.61 ) = 15.08 ρ ; cf (14.81ρ), [2]; note X x = X y = X effective ; at “a/b” = 1.

Note that the “CCCC” plate is summarized in Table 1 for the “ Δ -method” to reflect aspect-ratios; using Equation (17) for “ X i ” from “ X i − 1 ”.

The pure-shear strength values varied from “15.0ρ” at s* = 1 to “10.3ρ” at s* = 2.5 (near infinity); these compare well with those of Ref. [2], 14.8ρ to 9.8, respectively.

3.3. The “SSSS” Plate, (Nx from Δ) Is Compiled in <xref ref-type="table" rid="table2">Table 2</xref>

The trend is similar to the “CCCC” in Table 1; pure-shear results are only 60-percent of existing.

Brief Application to Free-Vibration in the “SSSS”

This is elaborated in Columns 10 and 11 in Table 2. Find mass-factor m ∗ = ∬ w w ∂ x ∂ y / ∬ w ∂ x ∂ y and, ω 2 = H / m * . Illustration is for m = n = 1, first.

3.4. The “CSCS” Plate in Pure-Shear

W = ( 1 − cos m π x / a ) ( sin m π y / b ) ; m = 2 , 4 , 6 , ⋯ , n = 1 , 2 , 3 , ⋯

a/b = 1: H_xx = 612; H_xy = 306; H_yy = 114.75; H = 1032.75; Δ c = 0.001936 , cf, 0.00192 [1]; X x = 15.5 ; X y = 11.625 ; N x = 6 . 75 ρ = exact ; N x y = 1032.75 / ( 0.707 × 15.5 ) = 9.5 ρ , expected to be exact.

Table 3 elaborates the “CSCS” case in the same fashion as the “CCCC” plate in Table 1. The results for pure-shear match the literature “SSSS” values and so the “SSSS” literature-values are untenable. The real “SSSS” values are as given in Table 2 and are about 60-percent of those in Table 3. Comparing ratios, N x , CSCS / N x , SSSS = 6.75 / 4 = 1.6875 and N x y , CSCS / N x y , SSSS = 9.5 / 5.66 = 1.678 ; these ratios are expected to be of the same order; and they are.

3.5. Deflection Limit

In Tables 1-3, the factor, δ X / δ Δ , exhibits a critical stationary-point, Figure 6, where “ Δ limit ” is sampled. The minimum buckling load, for very long plates,

Table 3 “CSCS” plate and s*; Nx = DKcr.; “ X ” from “ Δ ”; ( Δ i ≡ w s h / H )

s* (1)	Δ s ∗ ([Ref. [1] ) (2)	C_A (3)	X Δ (4)	H (5)	K_cr; (Ref. [2] ) (6)	( δ X / δ Δ ) = monitor (7)	2 X x y = 0.707 X Δ (8)	N_xy = (5)/(8) “Pure-shear” (9)
1	0.001936 [0.00192]	-	15.5	1032.18	6.75ρ, [6.75]	-	10.96	9.5ρ
1.15	0.0029	-	11.63	688.72	6.0ρ, []		8.22	8.5ρ
1.4	0.00465	1.059	7.68	430.35	5.68ρ, []	−2257 (−2144)	5.43	8.0ρ
1.65	0.00646	1.057	5.84	309.7	5.37	−1016 (−903)	4.13	7.6ρ
1.90	0.0081	1.054	4.91	246.5	5.09ρ, []	−581 (−468)	3.47	7.2ρ
2.15	0.0095	1.051	4.54	209.6	4.68ρ, []	−257 (−144)	3.21	6.6ρ
2.4	0.0107	1.049	4.23	186.3	4.46ρ	−258 (−145)	2.99	6.3ρ
2.65	0.0117	1.046	4.05	170.7	4.27ρ	−180 (−77)	2.863	6.04ρ
2.9	0.0125	1.043	3.96	159.8	4.09ρ; stop!!	−113 (0)**	2.80	5.78ρ
3.15	0.0132	1.043	3.92	151.79	3.92	−243 (−130)	2.77	5.55ρ

is indicated at that point, whatever the values of “m, n or s*”. The relative weakness of a plate is indicated in bending-buckling-vibration-analyses [6] - [12]. By Yaghoobi [13] the buckling strength of the “SSSS” at s* = 1.5 is 91-percent of the value at s* = 1; this is the kind of statement sought-after here. This sits well with the ratio of 89-percent in Table 2. In “plate buckling solution based on pre-buckling deflection” [14], relevance of deflection was focused on. Here, the analysis starts with beam-strip solutions that are already fully known; for simply supported strip, c = 5/384 = 0.01302 and the “SSSS” plate ends in this value when it is very long or very short; for example check the in Table 2 in the “SSSS” at s* = 3.5; so the size of “” can, also, be used to terminate solutions.

3.6. Higher Modes in Buckling: The “SSSS”

Table 2 has already solved this problem, relying only on the fundamental wave, m = n = 1, but the question may be posed: what is the failure mode for a given aspect ratio? In combining two neighboring symmetrical waves, the tried Dunkerley’s approximate resultant is used to study this question.

For example: s* = 2.5, try two waves, placed between the actions, 1) , or C_2.5,1; and 2) m = 3,; in details:

1) C_2.5,1: H_xx = 1.54; H_xy = 19.2; H_yy = 60.1; H = 80.8;;;;.

2) C_2.5,3: H_xx = 374; H_xy = 519; H_yy = 180.2; H = 1073;;

Combining by Dunkerley’s:

, cf, 2.91 in Table 2 above. This is a fail-safe combination.

So, it can be said that the waves “m = 1 and m = 3” combine for the aspect ratio, s* = 2.5; N_2.5,1,3 = 2.77ρ. This result is very different from the reference value of “4ρ” [1] [2]. In this way the complementary question of failure-mode is answered after the strength-solution.

4. Conclusions

1) The finite “Capacity” of the Kirchhoff’s plate differentials is constant in shear, in plate-buckling, in pure-shear plate-buckling, among others; compliant deflection functions supply domain relations.

2) The von Misses shear condition was shown to correlate exactly with the behavior of all-clamped rectangular plate in pure shear.

3) Using the same method new results are found for the “SSSS” plate; they are about 60-percent of currently held values. The imposition of stiffeners introduces boundary conditions different from the “SSSS” and so the present results, without stiffeners, appear more realistic.

4) The presently held “SSSS” shear values are, here, found corresponding to those of a plate clamped on Y-Y and simply-supported on the long side, X-X, with very good accuracy.

5) It is, therefore, concluded that the pure-shear results for the “SSSS” plate had not been found until the new results presented here: for “a/b = 1”, N_xy = 5.66ρ and not 9.3ρ. The difference is huge with respect to safety and frequency of maintenance of vessels.

Conflicts of Interest

The study reported here is original and there is no conflict of interest whatsoever.

Cite this paper

Johnarry, T.N. and Ebitei, F.W. (2020) Von Misses Pure Shear in Kirchhoff’s Plate Buckling. Open Journal of Civil Engineering, 10, 105-116. https://doi.org/10.4236/ojce.2020.102010

Nomenclature

a, b: rectangular plate dimensions in X, Y

s*: aspect ratio, a/b

E: Young’s modulus of elasticity

t: thickness of plate

D: flexural rigidity of plate, (isotropic);

: poisson’s ratio

w: deflection symbol; w_sh = shape-function value

: general value of displacement; = small change in the displacement

w_xx_-r; w_yy_-r: relative curvature in X-direction; Y-direction

w_xx_-r/w: relative-curvature/deflection ratio; must be a scalar for any solution

XX-SC, YY-CC: plate simply and clamped on X-X; and clamped-clamped on Y-Y

r_cap: capacity ratio of axes as,

: curvature; = small change in the curvature; = von Misses effective curvature

m, n: wave numbers

; N_cr: critical stress symbol; critical buckling load symbol

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Leissa, A.W. (1985) Buckling of Laminated Composite Plates and Shell Panels。 Ohio State University, June 1985 for Flight Dynamics Laboratory, Wright Patterson Air-Force Base.

Johns, D.L. (1972) Shear Buckling of Isotropic and Orthotropic Plates—A Review. Aeronautical Research Council—Report. R & M No. 3677, London.

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