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Second Progress Report 10/28/2013

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

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Second Progress Report 10/28/2013

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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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