Download - Second Progress Report 10/28/2013
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Analysis of Simply Supported Aluminum and Composite Plates with Uniform Loading to Determine Equivalent Plate Ply Stack-Up
Second Progress Report10/28/2013
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Thin Plate Theory
Three Assumptions for Thin Plate Theory• There is no deformation in the middle plane of the
plate. This plane remains neutral during bending.• Points of the plate lying initially on a normal-to-the-
middle plane of the plate remain on the normal-to-the-middle surface of the plate after bending
• The normal stress in the direction transverse to the plate can be disregarded
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Material Properties of Composite Laminate
Edge Length (a) 24 inch
Ply Thickness 0.040 inch
E1 2.25e7 psi
E2 1.75e6 psi
E3 1.75e6 psi
ν12 0.248
ν23 0.458
ν13 0.248
G12 6.38e5 psi
G23 4.64e5 psi
G13 6.38e5 psi
Applied Surface Pressure (q)
10 psi
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Governing Equations
Analysis and Performance of Fiber Composites: Agarwal & Nroutman
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Governing Equations (cont.)
Mechanics of Composite: Jones
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ANSYS Model with Mesh
Side 2
Side 1
Side 4
Side 3
Origin
• Due to Symmetry only a quarter of the plate needs to be modeled• The mesh size has an edge length of 0.75”•Side 1 and Side 2 are constrained against translation in the z-direction. •Side 2 and Side 3 is constrained against rotating in the x-direction•Side 1 and Side 4 is constrained against rotation in the y-direction•The origin is constrained against motion in the x- and y-directions• A pressure of 10 psi is applied to the area
Side 2
Origin
Side 4
Side 1
Side 3
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Results of Composite PlateComposite Plate Results
[0 90 0 90]s Laminate
•From governing equations:wmax = 0.7146”
• From ANSYSwmax = 0.7182”
• % Error = -0.5%
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Aluminum Plate Results (ref. First Progress Report)
Aluminum Plate Results
•From governing equations:wmax = 0.941399”
• From ANSYSwmax = 0.941085”
• % Error = 0.033%
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Results of Composite Plate (ANSYS)Laminate Stack-up Deflection (in)
[0 90]s 5.653
[0 90 0 90]s 0.7182
[0 90 0 90 0 90]s 0.2141
[0 90 0 90 0 90 0 90]s 0.091
[+/-30 0]s 1.404
[+/-45 0]s 1.271
[+/-60 0]s 1.405
[+/-30 0 +/-30 0]s 0.1592
[+/-45 0 +/-45 0]s 0.1452
[+/-60 0 +/-60 0]s 0.1600
[90 60 45 30 0]s 0.0014
[90 30 0]s 0.0014
[90 45 0]s 0.0036
[90 60 0]s 0.0044
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Findings
• From Slide 8, most of the ply arrangements that were created will perform better than the 0.25” thick aluminum plate.
• I will now continue the analysis of these plates to determine if any of the laminates will fail under this loading.
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Upcoming Deadlines
• Work on Thin Plate Analysis for Composite Plate for Laminate that aren’t cross-ply
• Failure Criterion Methods for Composite Stack-up