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Analysis of Simply Supported Plate Loading: Equivalence and Material Properties

Investigating aluminum and composite plate behavior under uniform loading using thin plate theory assumptions, composite laminate properties, governing equations, and ANSYS modeling for performance comparison. Progress update, results, findings, and upcoming research deadlines included.

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Analysis of Simply Supported Plate Loading: Equivalence and Material Properties

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

  2. 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

  3. Material Properties of Composite Laminate

  4. Governing Equations Analysis and Performance of Fiber Composites: Agarwal & Nroutman

  5. Governing Equations (cont.) Mechanics of Composite: Jones

  6. ANSYS Model with Mesh • 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 1 Side 1 Side 4 Side 4 Side 2 Side 2 Origin Origin Side 3 Side 3

  7. Results of Composite Plate • Composite Plate Results • [0 90 0 90]s Laminate • From governing equations:wmax = 0.7146” • From ANSYSwmax = 0.7182” • % Error = -0.5%

  8. Aluminum Plate Results (ref. First Progress Report) • Aluminum Plate Results • From governing equations:wmax = 0.941399” • From ANSYSwmax = 0.941085” • % Error = 0.033%

  9. Results of Composite Plate (ANSYS)

  10. 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.

  11. Upcoming Deadlines • Work on Thin Plate Analysis for Composite Plate for Laminate that aren’t cross-ply • Failure Criterion Methods for Composite Stack-up

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