o (MPa) 750 B F 600 A parallel Ty = 450 300 150 D C 0.01 0.02) 0.03 0.04 = 0.006 e (mm/mm) 0.023 EOC- The stress-strain diagram for an aluminum alloy that is used for making aircraft parts is shown in Fig. 3-19. If a specimen of this material is stressed to 600 MPa, determine the permanent strain that remains in the specimen when the load is released. Also, find the modulus of resilience both before and after the load application.

o (MPa) 750 B F 600 A parallel Ty = 450 300 150 D C 0.01 0.02) 0.03 0.04 = 0.006 e (mm/mm) 0.023 EOC- The stress-strain diagram for an aluminum alloy that is used for making aircraft parts is shown in Fig. 3-19. If a specimen of this material is stressed to 600 MPa, determine the permanent strain that remains in the specimen when the load is released. Also, find the modulus of resilience both before and after the load application.

Structural Analysis

6th Edition

ISBN:9781337630931

Author:KASSIMALI, Aslam.

Publisher:KASSIMALI, Aslam.

Chapter2: Loads On Structures

Section: Chapter Questions

Problem 1P

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Question

o (MPa)
750
B
-F
600
A
parallel
Ty = 450
300
150
D
€ (mm/mm)
0.01 | 0.02) 0.03 0.04
Ey = 0.006
- EOC-
O7
0.023
The stress-strain diagram for an aluminum alloy that is used for
making aircraft parts is shown in Fig. 3-19. If a specimen of this
material is stressed to 600 MPa, determine the permanent strain
that remains in the specimen when the load is released. Also, find
the modulus of resilience both before and after the load
application.

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