6. Airplane components often have a “stressed skin" construction, which consists of a thin sheet of aluminum in tension connected to the structure with rivets (i.e. pins that go through circular holes). a. If the aluminum skin is subject to a far-field biaxial tension of σ = 100 MPa and has a yield strength of σ = 210 MPa, will the rivet cause the sheet to yield? b. What is the strain through the thickness (z-direction) at the top-most edge of the hole? What does this mean is happening to the plate at that point? c. If a crack of length a = 1 mm forms at the side of the hole, will the plate fracture? How about if the crack is a = 3 mm? Take the aluminum to have a fracture toughness of K₁c = 15 MPa√m, and take the geometric stress concentration factor to be Y = 1.12. 50 = a
6. Airplane components often have a “stressed skin" construction, which consists of a thin sheet of aluminum in tension connected to the structure with rivets (i.e. pins that go through circular holes). a. If the aluminum skin is subject to a far-field biaxial tension of σ = 100 MPa and has a yield strength of σ = 210 MPa, will the rivet cause the sheet to yield? b. What is the strain through the thickness (z-direction) at the top-most edge of the hole? What does this mean is happening to the plate at that point? c. If a crack of length a = 1 mm forms at the side of the hole, will the plate fracture? How about if the crack is a = 3 mm? Take the aluminum to have a fracture toughness of K₁c = 15 MPa√m, and take the geometric stress concentration factor to be Y = 1.12. 50 = a
Elements Of Electromagnetics
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Author:Sadiku, Matthew N. O.
Publisher:Sadiku, Matthew N. O.
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Problem 1.1MA
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Question
![6. Airplane components often have a “stressed skin" construction, which consists of a thin sheet of
aluminum in tension connected to the structure with rivets (i.e. pins that go through circular holes).
a. If the aluminum skin is subject to a far-field biaxial tension of σ = 100 MPa and has a yield
strength of σ = 210 MPa, will the rivet cause the sheet to yield?
b. What is the strain through the thickness (z-direction) at the top-most edge of the hole? What does
this mean is happening to the plate at that point?
c. If a crack of length a = 1 mm forms at the side of the hole, will the plate fracture? How about if
the crack is a = 3 mm? Take the aluminum to have a fracture toughness of K₁c = 15 MPa√m,
and take the geometric stress concentration factor to be Y = 1.12.
50
=
a](/v2/_next/image?url=https%3A%2F%2Fcontent.bartleby.com%2Fqna-images%2Fquestion%2F1720cd77-2294-45a6-8b70-43447dc02920%2Fb238108e-b762-4076-9793-72c34760a362%2F8barl3k_processed.png&w=3840&q=75)
Transcribed Image Text:6. Airplane components often have a “stressed skin" construction, which consists of a thin sheet of
aluminum in tension connected to the structure with rivets (i.e. pins that go through circular holes).
a. If the aluminum skin is subject to a far-field biaxial tension of σ = 100 MPa and has a yield
strength of σ = 210 MPa, will the rivet cause the sheet to yield?
b. What is the strain through the thickness (z-direction) at the top-most edge of the hole? What does
this mean is happening to the plate at that point?
c. If a crack of length a = 1 mm forms at the side of the hole, will the plate fracture? How about if
the crack is a = 3 mm? Take the aluminum to have a fracture toughness of K₁c = 15 MPa√m,
and take the geometric stress concentration factor to be Y = 1.12.
50
=
a
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