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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.
Compute the coefficients in the plate stiffness equations for a twolamina laminate with ?1 = 55°, ?2 = -55°, t1 = t2 = 0.635 mm, with material properties .
Modern communication technology has brought us Internet connectivity just about anywhere on the planet. One very useful tool has been WiFi on airplanes
Demonstrate that an angle-ply laminate has A16 = A26 = 0 using an example laminate of your choice.
Compute the stresses (laminate coordinates) at z = -1.27 mm using the results of Problem 1.
Compute the [Q] matrix of a lamina reinforced with a balanced bidirectional fabric selected from Table.
Plot the strain and stress distribution (?x and sy) through the thickness of the bimetallic analyzed in Problem 1.
Compute the volume fraction Vf as a function of the fiber diameter df and the spacing between the centers of the fibers ax and ay in the two directions.
Consider the following material called carbon-epoxy with a fiber volume fraction of 70% and E= = 379 GPa, ?f = 0.22, Em= 3.3 GPa, and ?= = 0.35.
The container weighs 47.650 grams. Compute the fiber weight fraction WF and matrix weight fraction WM.
Estimate the effect of misalignment on the compressive strength of a carbon- epoxy (AS4-3501) composite fabricated by hand lay-up of prepreg tape
Define the plane stress assumption used in the context of laminated composite materials?
Compute the transformation matrix for a lamina oriented at 45? with respect to the x-axis.
Is the cross-section under a uniaxial state of strain in the laminate coordinates? Explain the origin of each nonzero strain.
Compute the transformed reduced stiffness for the material of Exercise 1 at ? = 45? and ? = 90?.
The load factor a that can be tolerated for the lamina with optimum orientation, considering all possible modes of failure and a resistance factor Ø = 1.0.
Calculate the % change needed on the stress in Problem 1 to achieve a reliability of 99.5%.