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Published byDeasia Treadwell Modified over 2 years ago

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Analysis of Simply Supported Aluminum and Composite Plates with Uniform Loading to Determine Equivalent Plate Ply Stack-Up Second Progress Report 10/28/2013

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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 Thickness0.040 inch E1E1 2.25e7 psi E2E2 1.75e6 psi E3E3 ν 12 0.248 ν 23 0.458 ν 13 0.248 G 12 6.38e5 psi G 23 4.64e5 psi G 13 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 Plate Composite Plate Results [0 90 0 90]s Laminate From governing equations: wmax = 0.7146 From ANSYS wmax = 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 ANSYS wmax = 0.941085 % Error = 0.033%

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Results of Composite Plate (ANSYS) Laminate Stack-upDeflection (in) [0 90]s5.653 [0 90 0 90]s0.7182 [0 90 0 90 0 90]s0.2141 [0 90 0 90 0 90 0 90]s0.091 [+/-30 0]s1.404 [+/-45 0]s1.271 [+/-60 0]s1.405 [+/-30 0 +/-30 0]s0.1592 [+/-45 0 +/-45 0]s0.1452 [+/-60 0 +/-60 0]s0.1600 [90 60 45 30 0]s0.0014 [90 30 0]s0.0014 [90 45 0]s0.0036 [90 60 0]s0.0044

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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 arent cross-ply Failure Criterion Methods for Composite Stack-up

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