A composite beam is made of two brass [E = 110 GPa] bars bonded to two aluminum [E = 71 GPa] bars, as shown. The beam issubjected to a bending moment of 260 N-m acting about the z axis. Using a = 10 mm, b = 85 mm, c = 20 mm, and d = 55 mm, calculate(a) the maximum bending stress in the aluminum bars.(b) the maximum bending stress in the brass bars.2AluminumCAluminumAnswers:(a) Jal=Brass-(b) Obr=iibBrass(2(2MPaOMPaE

Bending moment=260Nm a=10mm b=85mm c=20mm d=55mm

A composite beam is made of two brass [E = 110 GPa] bars bonded to two aluminum [E = 71 GPa] bars, as shown. The beam is ubjected to a bending moment of 260 N-m acting about the z axis. Using a = 10 mm, b = 85 mm, c = 20 mm, and d = 55 mm, calcul a) the maximum bending stress in the aluminum bars. b) the maximum bending stress in the brass bars. Aluminum C Aluminum Answers: Brass (a) Jal= i (b) abr= y i b Brass a d a MPa MPa

A composite beam is made of two brass [E = 110 GPa] bars bonded to two aluminum [E = 71 GPa] bars, as shown. The beam is ubjected to a bending moment of 260 N-m acting about the z axis. Using a = 10 mm, b = 85 mm, c = 20 mm, and d = 55 mm, calcul a) the maximum bending stress in the aluminum bars. b) the maximum bending stress in the brass bars. Aluminum C Aluminum Answers: Brass (a) Jal= i (b) abr= y i b Brass a d a MPa MPa

Materials Science And Engineering Properties

1st Edition

ISBN:9781111988609

Author:Charles Gilmore

Publisher:Charles Gilmore

Chapter6: Introduction To Mechanical Properties

Section: Chapter Questions

Problem 6.3P: Compare the engineering and true secant elastic moduli for the natural rubber in Example Problem 6.2...

See similar textbooks

Similar questions

The data in Table 1.5.3 were obtained from a tensile test of a metal specimen with a rectangular cross section of 0.2011in.2 in area and a gage length (the length over which the elongation is measured) of 2.000 inches. The specimen was not loaded to failure. a. Generate a table of stress and strain values. b. Plot these values and draw a best-fit line to obtain a stress-strain curve. c. Determine the modulus of elasticity from the slope of the linear portion of the curve. d. Estimate the value of the proportional limit. e. Use the 0.2 offset method to determine the yield stress.
A composite beam is made of two brass [E = 97 GPa] plates bonded to an aluminum [E = 72 GPa] bar, as shown. The beam is subjected to a bending moment of 2420 N-m acting about the z axis. Assume b=64 mm, d1=36 mm, d2=13 mm. Determine: (a) the maximum bending stresses opy,Gal in the brass plates and the aluminum bar. (b) the stress in the brass obrj at the joints where the two materials are bonded together. Brass (2) d2 Aluminum (1) Brass (2) dz b Answers: (a) obr = i MPa, oal = i MPа. (b) Obrj MPa.
A copper strip (Ec= 105 GPa) and an aluminum strip (Ea = 75 GPa) are bonded together to form the composite beam shown. Knowing that the beam is bent about a horizontal axis by a couple of moment M= 33 N-m, determine the maximum stress in the aluminum strip and in the copper strip. Aluminum Copper 24 mm 6 mm 6 mm The maximum compressive stress in the aluminum strip is The maximum tensile stress in the copper strip is MPa. MPa (include a negative sign).
A copper strip (Ec= 105 GPa) and an aluminum strip (Ea = 75 GPa) are bonded together to form the composite beam shown. Knowing that the beam is bent about a horizontal axis by a couple of moment M = 32 N-m, determine the maximum stress in the aluminum strip and in the copper strip. Aluminum Copper 24 mm 6 mm 6 mm The maximum compressive stress in the aluminum strip is -51.22 MPa (include a negative sign). The maximum tensile stress in the copper strip is 60.67 MPa.
A flat bar of aluminum alloy 25 mm wide and 5 mm thick is placed between two steel bars each 25 mm wide and 10 mm thick to form a composite bar 25 mm x 25 mm as shown. The three bars are fastened together at their ends when the temperature is 15℃. Find the stress in each of the materials when the temperature of the whole assembly is raised to 55 ℃.Steel: Es = 200 GPa; Coefficient of expansion = 1.2x10^-5/℃.Aluminum: Eal = 200/3 GPa; Coefficient of expansion = 2.3x10-5/℃.
A composite beam is made of two brass [E = 96 GPa] plates bonded to an aluminum [E = 62 GPa] bar, as shown. The beam is subjected to a bending moment of 2260 N-m acting about the z axis. Assume b=53 mm, d1=48 mm, d2=14 mm. Determine:(a) the maximum bending stresses σbrσb⁢r, σalσa⁢l in the brass plates and the aluminum bar.(b) the stress in the brass σbrjσb⁢r⁢j at the joints where the two materials are bonded together.
The composite bar shown is firmly attached to unyielding supports. An axial load P= 200 kN is applied at 20°C. Assume a = 11.7 um/(m °C) for steel and 23.0 um'(m °C) for aluminum. Find the reaction at the left support. a. find the reaction at the left supportb.find the stress at the steelc. find the stress at the aluminum
PROBLEM 6/6 F = 520 kN Determine the stress in each aluminum and steel bars after 0.2 mm F = 520 kN is applied. Note that a gap of 0.2 mm exist before the external load is Steel 280 mm applied and bars has equal distance with each other. Neglect the weight at the flat form. A = 1100 mm? E = 200 Gpa Steel Aluminum A = 2500 mm2 %3D E = 70 GPa %3D
a) Determine the force P (in kN) required to stretch the Aluminum bar by 3mm. B) Determine the final width and thickness of the Aluminum bar. (1)
The composite bar is firmly attached to unyielding supports. The bar is stress-free at 60° F. Compute the stress in each material after the 50-kip force is applied and the temperature is increased to 120° F. Use a = 6.5 x 10-6/°F for steel and a = 12.8 x 10-0/°F for aluminum. Aluminum Steel A = 2 in.2 E = 10 × 10° psi A = 3 in.2 E = 29 × 106 psi 50 kips -15 in. 10 in.
An aluminum alloy [E = 73 GPa; v = 0.33; a= 23.0 x 10-6/°C] plate is subjected to a tensile load P. The plate has a depth of d = 250 mm, a cross-sectional area of A = 6900 mm², and a length of L = 5.9 m. The initial longitudinal normal strain in the plate is zero. After load P is applied and the temperature of the plate has been increased by AT = 50°C, the longitudinal normal strain in the plate is found to be 2400 με. Determine: (a) the magnitude of load P. (b) the change in plate depth Ad. L Answer: (a) P = i (b) Δd = KN mm
An aluminum alloy [E = 74 GPa; v = 0.33; a = 23.0 x 10-6/°C] plate is subjected to a tensile load P. The plate has a depth of d = 265 mm, a cross-sectional area of A = 5300 mm², and a length of L= 4.2 m. The initial longitudinal normal strain in the plate is zero. After load P is applied and the temperature of the plate has been increased by AT = 57°C, the longitudinal normal strain in the plate is found to be 2920 με. Determine: (a) the magnitude of load P. (b) the change in plate depth Ad. L P Answer: (a) P = i (b) Δd = i kN mm