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Make a sketch (not to scale) of the deformed shape of a beam subject to a positive bending moment Mx and positive axial load Nx.
Compute the reduced stiffness and compliance matrices, and the intralaminar shear stiffness and compliance matrices .
Compute the stress vector at x = y = z = 60/47 using Cauchy's law.
Make a sketch (not to scale) of the deformed shape of a beam subject to a positive bending moment Mx. Make sure your drawing shows the thickness of the beam.
Compute the extensional [A], coupling [B], and bending stiffness [D] matrices of a bimetallic (copper and aluminum) strip.
Derive the middle-surface strains and curvatures. Derive the strain functions as a function of x, y, and z.
Derive the seven stress resultants integrating over the thickness of a laminated plate with N = 3, t1 = t2 = t3.
All laminae are 1.0 mm thick. Comment on the coupling of the constitutive equations for each case.
Comment on the relative magnitude of the coefficients as the number of laminae increases.
Compute the middle-surface strains ?0x, ?0y, ?0xy, and the curvatures ?x, ?y, ?xy for the following load cases.
Demonstrate that an angle-ply laminate has A16 = A26 = 0 using an example laminate of your choice.
Indicate why some values are continuous or discontinuous and state which locations through the thickness this occurs.
Given e0x = e0y = ?0xy = 0 and ?x = 1.0 m-1, ?y = 0.5 m-1, ?xy = 0.25 m-1, compute the strains (in laminate coordinates) at z = -1.27 mm in the laminate.
Consider the results and comment on which values are lower or upper bounds to the real value of each elastic property.
A composite sample plus its container weights 50.182 grams before burn-out and 49.448 grams after burn-out. The container weighs 47.650 grams.
Carbon(T300)-vinyl ester with Vf = 0.55. If actual data of Poisson's ratio for either fiber or matrix is not available, take ?f = 0.22, and/or ?m = 0.38.
Estimate F1t and F2t of carbon-epoxy IM7-8552 with Vf = 0.5 and negligible void content.
The data has been obtained experimentally for a composite based on an unidirectional carbon-epoxy prepreg .
Complete the table below with the contracted notation symbols for the component of stress and strain shown in the table.
Give an approximate value for the compressive strength of an Al-Boron composite with Vf = 0.4. Aluminum 2024 has E = 71GPa, Poisson = 0.334.
Compute the tensile strength for the composite of Problem 1 assuming that all the fibers have the same tensile strength.
Calculate the transverse tensile strength of AS4-3501-6 using the properties of Problem.
Using the Mohr-Coulomb failure criterion, calculate the strength ratio R for a unidirectional lamina of glass-epoxy.
Explain contracted notation for stresses and strains. Define the plane stress assumption used in the context of laminated composite materials?