A structural plate component of an engineering design must support 207 MPa in tension. If aluminium alloy 2024-T851 is used for the application, calculate the the largest internal flaw size that this materials can support. given Y=1 ,K1c =26.4
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A structural plate component of an engineering design must support 207 MPa in tension. If aluminium alloy 2024-T851 is used for the application, calculate the the largest internal flaw size that this materials can support. given Y=1 ,K1c =26.4
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- The frame of a space shuttle type vehicle must have a high yield strength and high stillness, and the most important design factor is weight. Of all the materials presented in this chapter, what material might be the most suitable for the frame of a space shuttle? Assume that there will be both tensile and compressive stresses. For a space shuttle, cost is not a limiting factor. (a) You can eliminate entire classes of materials from consideration with a brief statement about their unsuitability. (b) What material has the highest specific yield strength? Give the yield strength, specific gravity, specific yield strength, elastic modulus, and specific elastic modulus for this material. (c) What material has the highest specific elastic modulus? Give the yield strength, specific gravity, specific yield strength, elastic modulus, and specific elastic modulus for this material. (d) Compare the materials with the highest specific yield strength and highest specific elastic modulus for suitability in the space shuttle frame. (C) Discuss the suitability of the top-rated material for this design from the viewpoint of the ability to produce a frame.A 7075-T651 alloy is used in a structural component in an airplane. The component must not fail when subjected to a stress of 250 MPa. Several surface flaws have been detected on the component. What is the largest (deepest) surface flaw that could be permitted with the 250 MPa maximum stress? Use data from Table 1 and assume this component geometry and loading condition result in a Y value of 1.25. Yield Strength KI Material MPa ksi MPa√m ksiVin. Metals Aluminum alloy (7075-T651) 495 72 24 22The stress-strain relation of an aluminum alloy bar having a length of 2 m and a diameter of 10 mm is expressed by the equation 3 1 + 8 = 70,000 where o is in MPa. If the rod is axially loaded by a tensile force of 20 kN and lhen unloaded, whal is the permanent deformation of the bar?
- Task (3) you are asked to perform tensile test on specimens of two different materials (A and B) and you obtained the stress-strain diagram of the two specimens as shown in Figure 2: 400 350 300 250 Material A 200 150 100 50 0.02 0.04 0.06 0.08 0.1 0.12 0.14 0.16 0.18 Strain (mm/mm) 50 Material B 30 20 10 0.02 0.04 0.06 0.08 0.1 Strain (mm/mm) Figure 2: Tensile Test Analysis Stress (MPa) Stress (MPa)The assembly shown is composed of a steel shell and an aluminum core that has been welded to a rigid plate. The gap between the plate and the steel shell is 1- mm. If the assembly's temperature is reduced by 180°C, determine (a) the final axial stresses in each material and (b) the deflection of the rigid bar. To support your response, draw a deformation diagram with appropriate labels. Use the following properties: Aluminum core Steel shell Diameters (mm) d = 15 mm do = 30 mm d₁ = 20 mm E (GPa) 70 200 2 m a (/°C) 22 x 10-6 12 x 10-6The assembly is composed of a steel shell and an aluminum core that has been welded to a rigid plate. The gap between the plate and the aluminum is initially 1- mm. If the assembly's temperature is reduced by 180°C, determine (a) the final axial stresses in each material and (b) the deflection of the rigid bar. To support your response, draw a deformation diagram with appropriate labels. Use the following properties: Aluminum core Steel shell Diameters (mm) d = 15 mm do = 30 mm d₁ = 20 mm E (GPa) 70 200 2 m a (/°C) 22 x 10-6 12 x 10-6
- (a) the modulus of elasticity in GPa for the Aluminum B) the proportional limit in MPa for the Aluminum C) the ultimate strength in MPa for the Aluminum D) Ductility of material based on percent elongationSketch the stress–strain behavior of steel, and identify different levels of strength. What is a typical value for yield strength of mild steel? What is theeffect of increasing the carbon content in steel on each of the each of thefollowing items?a. Yield strengthb. Modulus of elasticityc. DuctilityA structural component in the shape of a flat plate 24.3 mm thick is to be fabricated from a metal alloy for which the yield strength and plane strain fracture toughness values are 533 MPa and 22.0 MPa-m1/2, respectively. For this particular geometry, the value of Y is 1.3. Assuming a design stress of 0.4 times the yield strength, calculate the critical length of a surface flaw. What formulas do i use ? And how do i use them?
- In the figure below, a stainless steel wire is supporting a weight, W. The Yield Strength and Young’s Modulus for stainless steel (Grade 304) is 205 MPa and 190 GPa, respectively. What is the maximum weight, W, in kN that can be supported by the wire if the allowable deformation is 1.3 mm? What is the safety factor relative to the Yield Strength at this allowable deformation condition?In the figure shown below, determine: 1) The final temperature if the normal stress at aluminium is Oal = = -90 MPa and the initial temperature 20°C. 2) The final length of the aluminium member. Aluminum Bronze A=1800mm2 A=1500mm2 E=105GPA E=73GPA a=23.2x10-6/°C a=21.6x10-6/°C Gap=0.5mm 0.35m 0.45m(b) (i) A tensile test specimen made from 0.4% C steel has a circular cross section of diameter d mm and a gauge length of 25 mm. When a load of 4500 N is applied during the test, the gauge length of the specimen extends to 25.02 mm. If the Young's Modulus of the steel is 199 GPa, calculate the diameter of the tensile test specimen used. 4