Statics and Mechanics of Materials (5th Edition)

5th Edition

ISBN: 9780134382593

Author: Russell C. Hibbeler

Publisher: PEARSON

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Chapter 14.11, Problem 118P

The principal strains at a point on the aluminum fuselage of a jet aircraft are ϵ 1 = 780 ( 10 − 6 ) and ϵ 2 = 400 ( 10 − 6 ) . Determine the associated principal stresses at the point in the same plane. E_al = 10(10³) ksi. v_al = 0.33. Hint: See Prob. 14–109.

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Chapter 14.11, Problem 117P

Chapter 14.11, Problem 119P

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Chapter 14 Solutions

Statics and Mechanics of Materials (5th Edition)

Ch. 14.3 - In each ease, the state of stress x, y, xy...Ch. 14.3 - Given the state of stress shown on the element,...Ch. 14.3 - Determine the normal stress and shear stress...Ch. 14.3 - Prob. 2FP Ch. 14.3 - Determine the equivalent state of stress on an...Ch. 14.3 - Prob. 4FP Ch. 14.3 - The beam is subjected to the load at its end....Ch. 14.3 - Prob. 6FP Ch. 14.3 - Prove that the sum of the normal stresses x+y=x+y...Ch. 14.3 - Determine the stress components acting on the...

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The principal strains at a point on the aluminum fuselage of a jet aircraft are ϵ 1 = 780 ( 10 − 6 ) and ϵ 2 = 400 ( 10 − 6 ) . Determine the associated principal stresses at the point in the same plane. E al = 10(10 3 ) ksi. v al = 0.33. Hint: See Prob. 14–109.

Solution Summary: The author calculates the plane stress at the point on the aluminum fuselage of a jet aircraft.

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Chapter 14 Solutions