PSI - Issue 70

Aamir Anwar Nezami et al. / Procedia Structural Integrity 70 (2025) 105–112

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3.3 Normalized values for laminated plates and sandwich Plates The displacements and stresses for Laminated Plates and Sandwich Plates are normalized throughout the problem unless stated otherwise, as given below: 3.3.1 Normalized values for laminated plates ( , ) = (100 ⋅ 3) ℎ 2 0 3 , = (100 ⋅ 3) ℎ 3 0 4 , ( , , )=ℎ 2 1 0 2 , ( , )=ℎ 1 0 (5) 3.3.2 Normalized values for sandwich plates ( , )=( 3) ℎ 2 0 3 , =( 3) ℎ 3 0 4 , ( , , )=ℎ 2 1 0 2 , ( , )=ℎ 1 0 (6) 3.4. Problem.1: Numerical examples on Nine Layer square symmetric cross-ply laminated plates ( =1 ) A simply supported laminated cross-ply square plate ( 0 ∘ /90 ∘ /0 ∘ /90 ∘ /0 ∘ /90 ∘ /0 ∘ /90 ∘ /0 ∘ ) are adopted. The laminae thickness and the material properties are uniform for each layer. The size of the plate model: length of side is = 1.2 , and thickness is ℎ = 0.3 . The plate is subjected to bi-sinusoidal distributed load ( , ) = 0 ( / ) ( / ). bending load is 0 = 1 / 2 . The material constants are, 1 = 25 , 2 = 1 , 3 = 1 ; 12 = 0.5 ; 13 = 0.5 ; 23 = 0.2 ; 12 =0.25 ; 13 =0.25 ; 23 = 0.25 ; 3.4.1. Results for nine-layer laminated square composite plate with the symmetric cross-ply stacking sequence

(a) (b) Fig. 1. ( ) In-plane displacements U, and ( ) Transverse shear stress for symmetric cross-ply nine-layer laminated plate for various thickness ratios = /ℎ = 4, 10, 100