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Assume that the standard deviation of fiber misalignment remains constant at the production value of 1.41 degrees.
Give an approximate value for the compressive strength of an Al-Boron composite with Vf = 0.4. Aluminum 2024 has E = 71GPa.
Design a composite cylindrical pipe of radius a = 1.0 m full of water. Assume the pipe is simply supported every 4.0 m and it is free to expand along.
Determine the factored moment capacity ØMn of the rectangular section subjected to interior environmental exposure with an initial deformation .
Determine the FRP area and the bending strength corresponding to the balanced strengthening configuration.
Calculate the maximum distributed load intensity "w" that a simply supported beam of length L = 5 m is able to carry.
Design the FRP for a simply supported beam with length L = 7 m. The external uniform dead and live loads are: wDL = 11.25 N/mm (Dead), and wLL = 13.25.
A cantilever beam with an interior exposure condition is subjected to a concentrated end force Vu = 2.88 × 105 N.
Design a non slender circular column with six vertical rebars and circumferential rebar cage, subjected to a factored ultimate loading Vu = 3.78 × 106 N.
strengthened member with n = 3 layers of carbon-epoxy FRP with properties f’fu= 3, 800 MP a ,e’fu= 0.0161, tf = 0.5 mm.
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 (Figure ) 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.
Perform the new design for a reliability of 99.5% assuming the load and strength variability are represented by Cs = 0.2, CF = 0.3.
Select a material, laminate stacking sequence, and thickness, to carry a uniformly distributed load p = 172 kP a.
Compute the critical edge load NxCR for a plate simply supported around the boundary, with length a = 2 m (along x).
Design the panel (skin and stiffeners) with a load factor of 2.5 and a resistance factor 0.4 on the first ply failure strength.
Design a spherical pressure vessel with a radius a = 0.5 m and internal pressure p = 10 MP a with variability Cp = 0.15 .
Optimize the cylindrical tank of Example 1 for minimum weight by changing the laminate configuration but not the material.
Design a circular cylindrical tank with closed ends subjected to an internal pressure p = 1.0MP a.
Compute the stress resultants on the dome. The dome intended to cover communication equipment.
A laminate of undisclosed configuration subjected to undisclosed load has a reported first ply failure (FPF) strength ratio R = 0.5.
Re-design the structure in Example 1 avoiding thick clusters of plies and taking into account in-situ strength. Use tt = 1.2 mm and ?23 = 0.38.
Consider a symmetric laminated beam with three laminae of equal thickness. The top and bottom laminae are made out of steel.
For A = B = C = 0.001, Q = R = 2, a = ß = p, x = y = 1/2, t = 0.002, evaluate and plot the strain as a function of the thickness coordinate z.