Discussion: • Dfleulties in testing brittle materials • Advantages of stress-strain diagram. • Sources of error you expect in the experiment. • Define the term strain hardening and explain in which stage in the stres strain diagram it occurs, what are its reasons, and its effects on maerid properties? . Compare bethween the britle and ductile fracture

Discussion: • Dfleulties in testing brittle materials • Advantages of stress-strain diagram. • Sources of error you expect in the experiment. • Define the term strain hardening and explain in which stage in the stres strain diagram it occurs, what are its reasons, and its effects on maerid properties? . Compare bethween the britle and ductile fracture

Elements Of Electromagnetics

7th Edition

ISBN:9780190698614

Author:Sadiku, Matthew N. O.

Publisher:Sadiku, Matthew N. O.

ChapterMA: Math Assessment

Section: Chapter Questions

Problem 1.1MA

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Discussion : • Difficulties in testing brittle materials. • Advantages of stress - strain diagram. • Sources of error you expect in the experiment. • Define the term strain hardening and explain in which stage in the stress- strain diagram it occurs, what are its reasons, and its effects on material properties? • Compare between the brittle and ductile fracture. fr in te
Figure 5 shows a failure assessment diagram (FAD) from the R6 calculator spreadsheet. (a) Make a copy sketch of the FAD in Figure 5, and indicate the regions of brittle fracture and plastic collapse. (2 mark (b) Using Figure 5, calculate the reserve factor on load. Explain how you obtained your answer. (4 mark. (c) Indicate on your sketch the effect on the FAD if: (i) a residual stress were present in the vicinity of the crack (ii) the crack length were increased (iii) the toughness of the material were improved. (3 + 3 + 3 = 9 marks Plate in tension - through-thickness edge crack 1.2 08- 0 76. 0 81 *06- 20 46. 0 48 04- 02- 0O 02 04 0.6 0.8 10 1.2 1.4 1.6 L, Figure 5 FAD for Question 6
Example (6): A tensile specimen with a 12 mm initial djameter and 50 gage Jength reaches maximum load at 90 kN and fractures at 70, kN. minimum diameter at fracture is 10 mm. Determine the engineering stre maximum load (the ultimate tensile strength) and the true frācture stress?. what is the value of true and engineering strain at fråcture?
For a piece of copper alloy, a standard stress test was applied to it, the following data was collected, from which a stress-strain diagram must be generated, where as data it is known that the initial diameter of the element is 0.505in. The analysis must include the following: 1.Modulus of Elasticity and modulus of resilience. 2.Percentage of elongation. 3.Percentage of area reduction. 4.Real and engineering stress at fracture. It is known that after the specimen fractures, its dimensions in terms of length and diameter are 3.014 and 0.374in, respectively.
1. Give an example of a creep plot for some material. From the creep plot, determinea. the steady-state creep rate and (b) the rupture lifetime.2. Describe the mechanism of crack propagation for both ductile and brittle modes offracture.
What are the importance of fracture toughness (KIC) and fatigue crack growthrate (da/dN) in design?
Consider the engineering stress-strain curves for three materials labeled A, B, and C below. Qualitatively, put the materials in the order in terms of largest-to- smallest strain hardening and Ductility. Stress B Strain
Is the maximum normal stress theory useful to predict the accurate failure of brittle material?
Suppose that a wing component on an air- craft is fabricated from an aluminum alloy that has a plane strain fracture toughness of 40 MPaVm (36.4 ksi Vin.). It has been deter- mined that fracture results at a stress of 365 MPa (53,000 psi) when the maximum internal crack length is 2.5 mm (0.10 in.), For this same component and alloy, compute the stress level at which fracture will occur for a critical in- ternal crack length of 4.0 mm (0.16 in.).
In designing a ceramic part for a jet engine, to ensure that the part does not fail, we plan to ensure that the maximum applied stress is only one-third of the yield strength. The yield strength of this CMC part for a jet engine is 520 MPa, and its plane strain fracture toughness is 5.5 MPa√?. We utilize a nondestructive test to find any internal faults that are longer than 1.27 mm. Does our non-destructive test have the requisite sensitivity if Y = 1.4? Explain.
A component made of 7075-T6 aluminum alloy has an edge crack of 1.4 mm in length. Plane strain fracture toughness of this alloy is given as 27 MPaym. Geometrical factor of the crack is given as 1.2. (a) If this alloy is subjected to uniaxial tensile stress of 380 MPa, determine whether sudden brittle fracture occurs or not. (b) Calculate the maximum allowable crack size for this component in order not to be failed in brittle manner under a stress of 1000 MPa
(a) A core sample having length to diameter ratio of 2.5 experienced a strain of 0.94 after being stretched. If the core had an initial length of 8 cm and was able to withstand a load of 500 N before breaking, calculate: The resulting length before failure The tensile strength (b) If the core sample above is subjected to a uniaxial compression test resulting in load, axial deformation and circumferential deformation of 350 N, 1.5 and 0.47 respectively at failure, calculate: The uniaxial compressive strength, σc The Young’s modulus, E The Poisson’s ratio,μ