ERRATA for "Introduction to Composite
Materials Design—Second Edition"
Ever J. Barbero, CRC, 2007, ISBN 978-1420079159
Updated April 27, 2011
Note: In addition to corrections for typos, this file includes comments that attempt to clarify and enhance the existing content in the book as well as highlight new code and examples as they become available in the Website.
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Page |
Where it reads |
Correction |
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xxxiii |
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xxxiv , insert |
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nT Transverse Poisson’s ratio |
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xxxv , insert |
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Fmc Apparent matrix tensile strength |
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xxxv , insert |
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Fms Apparent matrix shear strength |
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12, footnote |
[27] |
[242] |
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16, last line before Ex. 1.6 |
[27] |
[242] |
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24, Table 1.3 |
Transverse Poisson’s ratio n12 |
Transverse Poisson’s ratio n23 |
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25, Table 1.4, footnote |
G23=2.8—5.9… |
c G23=2.8—5.9… |
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38, 3rd paragraph in Sect. 2.4 |
…and a fiberglass backing… |
…and sometimes a fiberglass backing… |
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40, line 6 in Sect. 2.4.2 |
…the textile tread,… |
…the textile thread… |
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66, Table 2.7 |
above 3 |
- |
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66, Table 2.7 |
above 4.5 |
- |
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97, end of sect. 4.1.5 |
…orthotropic material. |
…orthotropic material: E1, E2, E3,
G12, G13, G23, n12, n13,
n23. |
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97, end of sect. 4.1.6 |
…five constants. |
…five constants: E1, E2, G12, n12, n23. |
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103, Sect. 4.2.4, above (4.34) |
The strength of material approach… |
The mechanics of materials approach… |
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112, (4.69) 3rd and 4th eq. |
˝ C*44 |
1/4 C*44 |
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112, (4.69) |
Add a 6th equation |
C44=(C22-C23)/2 |
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114, Ex. 4.4 |
technique |
techniques |
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114, Solution Ex. 4.4 |
a=60 10-6 |
a=30 10-6 |
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116, end of 3rd line in Sect. 4.4 |
…from bulk properties. |
…from bulk properties (see Table 2.5 and Sect. 2.2.1). |
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121, second line from top |
Since 2.9 does not list… |
Since Table 2.9 does not list… |
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130, penultimate line |
…to be a=0.8/4=0.2 mm. |
…to be a0=0.8/4=0.2 mm. |
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152, Ex. 5.1 |
The out of plane shear modulus G23=Gm=0.385 GPa. |
n23=0.385. |
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152, Solution Ex. 5.1 |
Q44*=0.385 GPa |
Q44*=4.112 GPa |
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179, 1st line after 1st eq. |
and at q=55o |
and at q=-55o |
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179 |
Example 5.1, p. 152 |
Example 5.1, p. 152, with n23=0.385 |
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179 |
Q44*=0.385 GPa |
Q44*=4.122 GPa |
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Q44*(1)=2.669 Q45*(1)=1.599 Q55*(1)=1.505 |
Q44*(1)=3.90 Q45*(1)=-0.15 Q55*(1)=4.01 |
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179 |
Q44*(2)=2.669 Q45*(2)=-1.599 Q55*(2)=1.505 |
Q44*(2)=3.90 Q45*(2)=0.15 Q55*(2)=4.01 |
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179 |
H44=2.82 H55=1.59 H45=0 |
H44=4.13 H55=4.24 H45=0 |
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184, Sect. 6.3.4, above (6.26) |
…material; and for each 0-lamina there is a complementary 90-lamina also of the same thickness and material. By… |
…material. By… |
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209, below the Table, RHS of 1st eq. (forces) |
10-3 |
N/mm |
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209, below the Table, RHS of 2nd eq. (moments) |
10-3 |
N |
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209, 3rd text line |
Middles surface |
Middle surface |
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210, 2nd paragraph, 7th line |
…angle is 55. Therefore… |
…angle is 55o.
Therefore… |
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212, above the 3rd eq. from bottom |
With the load having a COV of 20%,… |
With the load having a COV of 30%,… |
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241, Sol. Ex. 7.6 |
For Glass—Epoxy, form Table 1.3, F2t=40. |
For Glass—Epoxy, form Table 1.3, F2t=40 MPa. |
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242, Ex. 7.7, 3rd paragraph, 4th line |
N={3500,7000,0} has and a… |
N={3500,7000,0} has a… |
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258, 2nd paragraph in Sect. 7.5 |
The theoretical SCF relates… |
The theoretical SCF, Kt, relates… |
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259, after (7.61) |
The notch sensitivity… |
For isotropic materials, the notch sensitivity… |
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259, end of paragraph after (7.61) |
…laminate type. |
…laminate type, and it can be larger than one (see Fig. 7.18). |
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261, line above (7.69) |
That is sy=F0 at… |
That is, sx=F0 at… |
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261, line after (7.7) |
a0 is the characteristic |
d0 is the characteristic |
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262, line above (7.74) |
Using (7.63) and… |
Using (7.73) and… |
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270, line 7 |
…onto the broken fiber (8.2). |
…onto the broken fiber (Figure 8.2). |
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271, (8.7) |
(m e F1tm)-1 |
[m e (F1t)m]-1 |
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283, after (8.36) |
delta Dirac |
Kronecker delta |
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303, (9.24) |
All zero subscripts, |
,must be superscripts as in (9.23) |
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304, (9.26) |
All zero subscripts, |
,must be superscripts as in (9.23) |
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326, Sect. 9.9 |
(CSM, Figure 2.3). |
(CSM, Figure 2.2). |
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327, (9.64) |
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Note that for CSM, |
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341, Sect. 10.1.1, line 2 |
Carpet plot of Ex (Figure 6.8). |
Carpet plot of Ex (Figure 6.8).1 Footnote 1. Not Exb because the flanges are subjected to predominantly tensile or compressive stress resultants. |
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References
for this Errata
[*1] Barbero, E. J., Finite
Element Analysis of Composite Materials (2007), CRC Press, Boca Raton FL http://www.mae.wvu.edu/barbero/feacm/index.html
Please e-mail additional corrections to http://www.mae.wvu.edu/barbero/
Contributors to this page & Users of the Book
Corrections have been made
thanks to the helpful contributions from:
·
Joaquin
Gutierrez, West Virginia University
·
Fernando Cosso, West Virginia University
·
Any Others??