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Design a box section to be used as a cantilever beam of length L = 2 m subject to a tip load P = 1000 N.
Compute the bending stiffness of a cantilever I-beam of length L = 30 cm, subjected to a tip-shear force Vz = 445 N.
Derive an expression for the failure moment per unit area in terms of the ratio r = h/b, for a constant material strength Fx.
What is the required wall thickness and material type for minimum cost?
Compute the laminate FPF strength Fxt. Note that the 904 lamina is the first to crack, thus defining FPF.
Design a cylindrical pressure vessel with diameter d = 4 m, internal pressure p = 3.0 MP a, with a COV Cp = 0.10 to achieve a reliability Re = 0.95 .
Draw the top view repetitive unit cell (RUC) for 5/1/2 weave counting along the x-direction.
Redefine the weave parameters, first by 90o rotating the weaving pattern, and second by considering the opposite face of the weaving pattern.
Draw the top view repetitive unit cell (RUC) for 4/2/1 weave counting along the x-direction.
Recalculate the tow elastic properties E1, E2, G12, G23, ?12, ?23 of weave type 1 in Table.
Calculate the compliance matrix [S] in laminate coordinates at x = aw/4, y = af/2, for the fill and warp tows of sample type 5 in Table.
Compute the [Q] matrix of a lamina reinforced with a balanced bidirectional fabric selected from Table
Compute the curvature of the bimetallic in Problem 1 when it is subjected to a change of temperature ?T = 10 °C.
Plot the strain and stress distribution (?x and sy) through the thickness of the bimetallic analyzed in Problem.
For each of the following laminates, specify the laminate type. Note that a laminate may have more than one characteristic.
For each of the laminates described in Table, specify if they are balanced and/or specially orthotropic.
Compute the laminate moduli (Ex, Ey, Gxy, and ?xy) and the laminate bending moduli (Ex, Ey, Gxy, and ?bxy) for the laminate .
How much does the load need to be increased/ decreased to avoid first ply failure, assuming all components are increased/ decreased proportionally?
Determine the strength ratio R at the bottom surface of the laminate.
The minimum value of strength ratio R thus obtained corresponds to the last ply failure (LPF), i.e., RLP F .
Determine the value of the forces Nx, Ny, Nxy, Mx, My, Mxy required to produce a curvature ?x = 0.00545 mm-1, ?y = -0.00486 mm-1.
Compute the [A], and [D] matrices (neglect shear deformations) for the intact laminate. Each lamina is 2.5 mm thick.
Nx = -1000 N/mm all other zero. Why is the strength ratio different from case(a) ?