Tensor Equations-Material and Structures-Assignment, Exercises of Structures and Materials

This is assignment for Material and Structures course. To cover following points, Prof. Aparijita Singh assigned this task at Andhra University to engineering students: Tensor, Equations, Succint, Notation, Assumptions, Strain, Compatibility, Design, Load, Capability, Aircraft, Yield

Typology: Exercises

2011/2012

Uploaded on 07/26/2012

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16.20 Handed Out: Lecture 5
Due: Lecture 9
HOME ASSIGNMENT #1
Warm-Up Exercises
Write out the following tensor equations in full:
(Note: these equations do not necessarily have any real meaning)
1.
G
i
= l
αβ
M
αβ
n
i
2.
A
ij
= Q
ijkl
τ
k
x
l
(for i = 2, j = 3)
3.
a
mn
u
n
+ f
m
= 0
t
4.
1
E = 2 σ
αβ
ε
αβ
5.
σ
23
= l
2m
l
3n
˜
σ
˜ ˜˜ mn
Practice Problems
6. Write out the succinct tensor equation that describes the following notation:
H
1
C
111
C
122
2C
112
M
11
H
2
= C
211
C
222
2C
212
M
22
H
3
C
311
C
322
2C
312
M
12
Note any assumptions that you had to make (if any).
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16.20 Handed Out: Lecture 5 Due: Lecture 9 HOME ASSIGNMENT # Warm-Up Exercises Write out the following tensor equations in full: ( Note: these equations do not necessarily have any real meaning)

  1. (^) G i =^ lαβMαβni
  2. (^) A ij =^ Qijklτk xl (for i^ =^ 2,^ j^ =^ 3)
  3. amn ∂un + fm = 0 ∂t
  4. 1 E = 2 σαβ εαβ
  5. σ 23 = l 2m l 3n˜^ ˜ σ^ ˜ ˜ mn Practice Problems
  6. Write out the succinct tensor equation that describes the following notation:

H 1  C 111 C 122 2C 112 M 11 

H 2  =^

C

211

C

222

2C

212

M 22 

H

C

311

C

322

2C

M

Note any assumptions that you had to make (if any). docsity.com

16.20 Home Assignment #1 Page 2 Fall, 2002

  1. The following is the tensorial form of the strain compatibility equations: ∂ 2 εnk +

2 εml −

2 εnl −

2 εmk = 0 ∂ ym∂ yl ∂ yn∂ yk ∂ ym∂ yk ∂ yn∂yl Write one useful equation represented by this generic form. Convert this equation to engineering notation as well. Application Tasks

  1. An aerobatic airplane has a key structural part of the empennage designed to undergo a design limit load of 7550 N at the operational maximum g- capability of the aircraft of 4.2 g. This part is made of a material with a yield stress of 250 MPa and an ultimate stress of 350 MPa. The static tests on this part made at the factory showed an ultimate margin of safety of 18.2% on this part. During training exercises, a g-meter shows that the pilot pulled a maneuver of 4.6 g. Upon review of the information from this exercise, the maintenance chief of the company that owns the plane needs to determine whether the plane can continue to be safely flown. Give your answer/thoughts in this regard with appropriate calculations as evidence. docsity.com