Corrugated Wood Composite Panels For Structural Decking

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Finite Element ModelThe analytic solutions for classical plate bending differential equation are noteasily obtained and closed form solutions might not be available for some boundaryconditions. Thus, a numerical solution to plate bending, the finite element (FE) method,was used to model corrugated panels. A FE program called I-DEAS ®* developed byStructural Dynamics Research Corporation (SDRC ® ) was used to perform analysis ofcorrugated panels prior to any experimental work and also to verify the results ofexperimental testing.Specifications of ElementsCorrugated panels and oriented strand boards (OSB) have plate-like geometry.Therefore, 2-dimentional (2D) FE elements are used to model the behavior of corrugatedpanels. In general, there are three common types of 2D elements; plane stress, planestrain and thin shell elements. Corrugated panels exhibit both in-plane (x-y plane, Figure7) stress-strain behavior as well as out-of-plane (z-direction, Figure 7) bending whenzxyFigure 7: 4-node bilinear thin shell element.* I-DEAS ® and SDRC ® are the registered trademarks of the Structural Dynamics Research Corporation.20
subject to loads. Thus, thin shell elements are more appropriate for the task of modelingboth in-plane and out-of-plane behavior.I-DEAS ® provides three options for thin shell elements: 3-node, 4-node and 8-node elements. Meshing was done with 4-node bilinear thin shells elements because oftwo main reasons. First, meshing rectangular plate structures with 4-node rectangularshape elements can simplify the process of applying load and boundary conditions to themodel. Second, 8-node elements might produce better results than 4-node elements.However, the computational time and disk space required by the 8-node elements is morethan double of the 4-node elements. Hence, 4-node elements are used for meshingcorrugated panel and composite deck instead of 8-node elements. For a 4-node element,there are six degrees of freedom for each node for a 4-node bilinear element. There arethree translational displacements in the x, y, z directions,∆ x,∆y,∆z, and threerotational displacements about all three x-, y-, and z-axes,Rx,Ry,Rz.Corrugated panels produced with a random mat can be modeled with in-planeisotropic material. However, the moduli of elasticity for OSB are different in the strongaxis and weak axis directions. Thus, an orthotropic material is used for the 4-node thinshell element to model both corrugated panels and OSB. Four basic parameters areneeded to define an orthotropic 2D material. Two in-plane moduli of elasticity,ExandEy, Poison’s ratio, ν , and an in-plane shear modulus,Gxy, are needed. The in-planeshear modulus is independent of both moduli of elasticity and the Poison’s ratio fororthotropic materials.xyE is equal to E for random mat corrugated panels, because inplaneisotropic behavior is assumed.21
Page 1 and 2: Corrugated Wood Composite Panels Fo
Page 3 and 4: AcknowledgementsI would like to exp
Page 5 and 6: Molding trials on 16”x16” panel
Page 7 and 8: Table of ContentsAbstract..........
Page 9 and 10: Corrugated Panel Single Span Test..
Page 11 and 12: List of FiguresFigure 1: Corrugated
Page 13 and 14: Figure 48: Load-displacement curves
Page 15 and 16: Figure 93: Mock-up floor constructi
Page 17 and 18: Table 20: MOE and strong axis bendi
Page 19 and 20: IntroductionWood flake composite pa
Page 21 and 22: process needed to be refined in ord
Page 23 and 24: 4. Construct and test the performan
Page 25 and 26: system (OSB top layer nailed-glued
Page 27 and 28: In geometry design studies, four ge
Page 29 and 30: Similarly, the relative strength ca
Page 31 and 32: 14120Relative Stiffness and Relativ
Page 33 and 34: 21.51.8Moldability Factor1.451.4Mol
Page 35 and 36: with as little modification to the
Page 37: uniform line loads, or concentrated
Page 41 and 42: FE models are used to analyze both
Page 43 and 44: with 4-node thin shell elements. In
Page 45 and 46: Orthotropic Plate ModelTypical ligh
Page 47 and 48: 2 2∂∆( x, y) ∂∆( x, y)Myy(
Page 49 and 50: 1.41.2Fourier series approximation
Page 51 and 52: 2qLnπqn( x) = sin( yo) for n= 1,2,
Page 53 and 54: Free-Free and Simply Supported (FFS
Page 55 and 56: ∫02 2⎛ ∂∆n ∂δ∆n 2 ∂
Page 57 and 58: Convergence studies of FFSS PlatesT
Page 59 and 60: 0.440.4380” 0.4292” 0.4434”0.
Page 61 and 62: Beam ModelIn simple beam theory, th
Page 63 and 64: Qz ( )⎧⎪⎪⎪h− th+t2 2⎛ 2
Page 65 and 66: ⎡h+t2⎢ 12 ⎥first= 2 ⎢ ( τf
Page 67 and 68: of elasticity (psi) and shear modul
Page 69 and 70: 3∆ ≈ PL PLFEcb 1cs148EI+ 4GA(63
Page 71 and 72: Two-span ModelFor the two-span cond
Page 73 and 74: was encountered. The error was larg
Page 75 and 76: Composite Deck Beam ModelBending st
Page 77 and 78: of the corrugated panel. Substituti
Page 79 and 80: Cefffor a specific bond, such as a
Page 81 and 82: if the closing gap was at a distanc
Page 83 and 84: weight of panel at the time of test
Page 85 and 86: Green aspen logs were used to produ
Page 87 and 88: Gauge Pressure750 psi020 180 210Tim
Page 89 and 90:
Testing of 16”x16” PanelsThe st
Page 91 and 92:
0.10 or lower. This indicates that
Page 93 and 94:
zxy0.25”x0.25” 4-nodethin shell
Page 95 and 96:
700Load/Deflection (lbs/in), y60050
Page 97 and 98:
Load/Deflection (lbs/in), y60050040
Page 99 and 100:
Beam ModelPPLL eqFigure 45: Equival
Page 101 and 102:
Table 13: MOE, bending stiffness an
Page 103 and 104:
The moisture contents of the specim
Page 105 and 106:
Finite Element ModelFE models were
Page 107 and 108:
The panel skin thickness also exhib
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The load-to-deflection ratio can di
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used for each thickness level. The
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The smallest span used in the calib
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Test ResultsThe average moisture co
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Table 23: Maximum shear and moment
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Maximum Moment (lbf-in/ft)500040003
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Test ResultsFigure 61: Load-deflect
Page 123 and 124:
Test ProceduresTwo edge test assemb
Page 125 and 126:
Lateral Density ProfileThe 16”x16
Page 127 and 128:
Manufacture of 4ft x 8ft Corrugated
Page 129 and 130:
as the carrier with an idea of desi
Page 131 and 132:
Full-Scale Panel TestingBending pro
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approximate the solution for deflec
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Table 30: Flexure test results of 4
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Load22 ½” o.c. or30 ½” o.c.24
Page 139 and 140:
ending stiffness were both over 400
Page 141 and 142:
Corrugated Panel Two-Span Continuou
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the FE model estimation. The averag
Page 145 and 146:
Strength Axis Static Bending of 2
Page 147 and 148:
Test ProceduresNon-destructive flex
Page 149 and 150:
used as the element thicknesses for
Page 151 and 152:
of the partial composite test. Figu
Page 153 and 154:
1 .10 4 FE Model (average)Load/Defl
Page 155 and 156:
Composite Deck Two-Span Continuous
Page 157 and 158:
ick elements for adhesive, etc.) us
Page 159 and 160:
1.6 .10 4 FE Model (average)1.4 . 1
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Composite T-BeamComposite nailed-gl
Page 163 and 164:
ottom flange of the I-joist. A tota
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EIwandEIfare the bending stiffnesse
Page 167 and 168:
whereL adis the length of the adhe
Page 169 and 170:
EIuis the bending stiffness of the
Page 171 and 172:
Table 38: Material properties of th
Page 173 and 174:
System BehaviorThe bending stiffnes
Page 175 and 176:
Table 40: System effect of nailed-g
Page 177 and 178:
A’Joints of OSBunderlayment(solid
Page 179 and 180:
¼” dia. AFG-01 adhesiveFigure 92
Page 181 and 182:
lockings were also installed at the
Page 183 and 184:
Comparison to Traditional Floor Sys
Page 185 and 186:
The baseline flexural capacities of
Page 187 and 188:
Conclusions and RecommendationsConc
Page 189 and 190:
The potential of using the shallow
Page 191 and 192:
dj= depth of I-joist (in)E = modulu
Page 193 and 194:
h = channel depth of the corrugated
Page 195 and 196:
Sc= section modulus of the corrugat
Page 197 and 198:
τfirst= first order shear stressϖ
Page 199 and 200:
Howard, J.L. (2001). “U.S. Forest
Page 201 and 202:
Appendix A. Moment of Inertia of Co
Page 203 and 204:
Appendix B. Moldability FactorConce
Page 205 and 206:
Appendix D. FFSS Plate Under Line L
Page 207 and 208:
Ff = @(x)2.*qo./b.*sin(beta(k).*yo)
Page 209 and 210:
Appendix F. Test Data for 16”x16
Page 211 and 212:
Edge Point LoadPanel Type-ALower de
Page 213 and 214:
Appendix H. Lateral Density Profile
Page 215 and 216:
Panel:Date:5-4November 11, 2002Widt
Page 217 and 218:
08LT24”x32”08RT24”x64”11LT2
Page 219 and 220:
30T48”x48”35LT24”x64”35RT24
Page 221 and 222:
Nominal 32” Two-Span TestPanelNo.
Page 223 and 224:
Nominal 24” Two-Span Composite Te
Page 225 and 226:
Appendix K. Shear Modulus of I-Jois
Page 227:
Appendix L. Allowable Moment Estima
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Corrugated Wood Composite Panels For Structural Decking

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