07-01ChapGere.0003

# 07-01ChapGere.0003 - from the fuselage of an airplane is...

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Solution 7.2-4 Plane stress (angle u ) SECTION 7.2 Plane Stress 427 x O 84.2 MPa u 5 48 8 118.2 MPa 20.2 MPa y s x 5 42 MPa s y 52 140 MPa t xy 52 60 MPa u 5 48 8 52 118.2 MPa 52 84.2 MPa s y 1 5 s x 1 s y 2 s x 1 5 20.2 MPa t x 1 y 1 52 s x 2 s y 2 sin 2 u 1 t xy cos 2 u s x 1 5 s x 1 s y 2 1 s x 2 s y 2 cos 2 u 1 t xy sin 2 u Problem 7.2-5 Solve the preceding problem if the normal and shear stresses acting on element A are 7,500 psi, 20,500 psi, and 4,800 psi (in the directions shown in the figure) and the angle is 30° (counterclockwise). Solution 7.2-5 Plane stress (angle u ) A 4,800 psi 20,500 psi 7,500 psi x O 14,520 psi u 5 30 8 3,660 psi 9,340 psi y s x 5 7,500 psi s y 52 20,500 psi t xy 52 4,800 psi u 5 30 8 52 3,660 psi 52 14, 520 psi s y 1 5 s x 1 s y 2 s x 1 52 9,340 psi t x 1 y 1 52 s x 2 s y 2 sin 2 u 1 t xy cos 2 u s x 1 5 s x 1 s y 2 1 s x 2 s y 2 cos 2 u 1 t xy sin 2 u Problem 7.2-6 An element in plane stress
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Unformatted text preview: from the fuselage of an airplane is subjected to compressive stresses of magnitude 25.5 MPa in the horizontal direction and tensile stresses of magnitude 6.5 MPa in the vertical direction (see figure). Also, shear stresses of magnitude 12.0 MPa act in the directions shown. Determine the stresses acting on an element oriented at a clockwise angle of 40° from the horizontal. Show these stresses on a sketch of an element oriented at this angle. 12.0 MPa 6.5 MPa 25.5 MPa A-PDF Split DEMO : Purchase from www.A-PDF.com to remove the watermark...
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## This note was uploaded on 09/20/2009 for the course COE 3001 taught by Professor Armanios during the Spring '08 term at Georgia Tech.

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