Problem 1.5 A component of a composite rocket motor case is subject to a state of stress o₂ = 10 MPa, oy = 5MPa, Ozy = 2.5 MPa. Use the material data for Carbon/Epoxy (AS4-3501-6) in Table 1.3. Using "principal stress design," compute: (a) The optimum fiber orientation.
Problem 1.5 A component of a composite rocket motor case is subject to a state of stress o₂ = 10 MPa, oy = 5MPa, Ozy = 2.5 MPa. Use the material data for Carbon/Epoxy (AS4-3501-6) in Table 1.3. Using "principal stress design," compute: (a) The optimum fiber orientation.
Elements Of Electromagnetics
7th Edition
ISBN:9780190698614
Author:Sadiku, Matthew N. O.
Publisher:Sadiku, Matthew N. O.
ChapterMA: Math Assessment
Section: Chapter Questions
Problem 1.1MA
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A component of a composite rocket motor ease is subject to a state of stress o_x = 10 MPa, o_y = 5 MPa, o_xy = 2.5 MPa. Use the material data for Carbon/Epoxy (AS4-3501-6) in Table 1.3. Using "principal stress design", compute:
a. The optimum fiber orientation.
Transcribed Image Text:Problem 1.5
A component of a composite rocket motor case is subject to a state of stress o = 10 MPa, oy = 5 MPa,
ozy = 2.5 MPa. Use the material data for Carbon/Epoxy (AS4-3501-6) in Table 1.3. Using "principal stress
design," compute:
(a) The optimum fiber orientation.
![Table 1.3: Typical properties of unidirectional (carbon-fiber) composites, obtained
from product literature and other sources, some values estimated for broad class of
materials, 14
Density [g/cc]
Longit. Modulus [GPa]
Transv. Modulus [GPa]
Shear Modulus [GPa]
Poisson's ratio
Poisson's ratio
Longit. Tens. Str. [MPa]
Transv. Tens. Str. [MPa]
L. Compr. Str. [MPa]
T. Compr. Str. [MPa]
Shear Str. [MPa]
Shear Str. [MPa]
Ult. L. Tens. Strain [%]
Ult. T. Tens. Strain [%]
Ult. L. Comp. Strain [%]
Ult. T. Comp. Strain [%]
Ult. Shear Strain [%]
Toughness Mode I [J/m²]
Toughness Mode II [J/m²]
Longit. CTE [ppm/°C]
Transv. CTE [ppm/°C]
Stress-free Temp. [°C]
L. Moist. Exp. [ppm]
T. Moist. Exp. [ppm]
Fiber Vol. Fraction
Void Content
Fiber Misalignment [deg]
Ply Thickness [mm]
tr(Q) [GPa]
G' (GPa)
P
1.6
E₁
138
E₂
10.2
G12
5.7
V12
0.28 0.3
V23
0.4
Fit 1950
F2t
48
Fle
1480 1360
F2c
200
Fe
79
F4
Elt
€2t
Ele
AS4/ AS4/ AS4/ IM6/ IM6/ SE84 T700/
3501-6 APC2 3502 PEEK 3501-6
RS-36
[21]
PEEK
[39]
[39,40] [41] [42]
1.58
1.57
1.56
126
133 160.6
11
9.3
8.2
6.6
3.74 4.14
1.38
0.436
1.175
€20 2
2
You
Gie 220
G₁1c
01
Sa
tk
-1
02 26
SFT 177
B₁
0
B₂
0.2
V₁
0.6
0.34
0.31
0.46 0.45
2070 1778.8 2337.3 2379 2751 2200
86
53.5
46.9
992.73 1000
638 238.5
186
102
150
1.45
0.88
1.67
1.85
1700
2000
0.5
30
143
5.1
189
570
-0.89
119
31
0.61
0.005 0.001
2.74
1.24 1.46
0.55
0.6
1.62 0.8 0.95 0.95
960
23
208
0
46.7
0.59 0.55
0.002
1.7
1.52
0.125 0.125 0.139
0.125
151.1 160.6 150.9 177.9
26.34
"Ultimate. Also called "strain-to-failure."
"Calculated in Section 6.5 using properties listed above.
161 124.3 135
8.14 10.3
9.65
5.2 4.49 4.4
0.3
0.32 0.34
-0.09
28.8
271
1752
0.65
1180 1900
1.2
I
I
I
1.63
1.41
0.28 0.312
182 142.3 155.4
30.06 30.53 36.99 36.24 27.53 30.48
"ppm=10-6.](/v2/_next/image?url=https%3A%2F%2Fcontent.bartleby.com%2Fqna-images%2Fquestion%2F5842debd-c7e0-436d-83d9-66a4971dddbf%2F6d380bc5-b677-404c-917a-8ba5ef367e08%2F3hys45v_processed.png&w=3840&q=75)
Transcribed Image Text:Table 1.3: Typical properties of unidirectional (carbon-fiber) composites, obtained
from product literature and other sources, some values estimated for broad class of
materials, 14
Density [g/cc]
Longit. Modulus [GPa]
Transv. Modulus [GPa]
Shear Modulus [GPa]
Poisson's ratio
Poisson's ratio
Longit. Tens. Str. [MPa]
Transv. Tens. Str. [MPa]
L. Compr. Str. [MPa]
T. Compr. Str. [MPa]
Shear Str. [MPa]
Shear Str. [MPa]
Ult. L. Tens. Strain [%]
Ult. T. Tens. Strain [%]
Ult. L. Comp. Strain [%]
Ult. T. Comp. Strain [%]
Ult. Shear Strain [%]
Toughness Mode I [J/m²]
Toughness Mode II [J/m²]
Longit. CTE [ppm/°C]
Transv. CTE [ppm/°C]
Stress-free Temp. [°C]
L. Moist. Exp. [ppm]
T. Moist. Exp. [ppm]
Fiber Vol. Fraction
Void Content
Fiber Misalignment [deg]
Ply Thickness [mm]
tr(Q) [GPa]
G' (GPa)
P
1.6
E₁
138
E₂
10.2
G12
5.7
V12
0.28 0.3
V23
0.4
Fit 1950
F2t
48
Fle
1480 1360
F2c
200
Fe
79
F4
Elt
€2t
Ele
AS4/ AS4/ AS4/ IM6/ IM6/ SE84 T700/
3501-6 APC2 3502 PEEK 3501-6
RS-36
[21]
PEEK
[39]
[39,40] [41] [42]
1.58
1.57
1.56
126
133 160.6
11
9.3
8.2
6.6
3.74 4.14
1.38
0.436
1.175
€20 2
2
You
Gie 220
G₁1c
01
Sa
tk
-1
02 26
SFT 177
B₁
0
B₂
0.2
V₁
0.6
0.34
0.31
0.46 0.45
2070 1778.8 2337.3 2379 2751 2200
86
53.5
46.9
992.73 1000
638 238.5
186
102
150
1.45
0.88
1.67
1.85
1700
2000
0.5
30
143
5.1
189
570
-0.89
119
31
0.61
0.005 0.001
2.74
1.24 1.46
0.55
0.6
1.62 0.8 0.95 0.95
960
23
208
0
46.7
0.59 0.55
0.002
1.7
1.52
0.125 0.125 0.139
0.125
151.1 160.6 150.9 177.9
26.34
"Ultimate. Also called "strain-to-failure."
"Calculated in Section 6.5 using properties listed above.
161 124.3 135
8.14 10.3
9.65
5.2 4.49 4.4
0.3
0.32 0.34
-0.09
28.8
271
1752
0.65
1180 1900
1.2
I
I
I
1.63
1.41
0.28 0.312
182 142.3 155.4
30.06 30.53 36.99 36.24 27.53 30.48
"ppm=10-6.
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