Improving aircraft composite inspections using optimized reference standards Page: 12 of 13
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Boeing Carbon Uniaxial (Step Wedge
Sandia Carbon Weave (12" X 12" Plat
(Resonance - High Frequency)
_ /
,0 4
01 4
S/ " 8
----1-
loi nus
.008" -
(niax' i)
Sendia_-
n
we aveNotes:
)
1. Nulled on 0.008' thick Boeing
specimen and 0.010" Sandia
specimen.
2. Setup:
a) gain=14dB
b) frequency = 313KHz
c) rotation = 180*
d) H POS = 40%
V POS = 20%
3. Thickness range is from .008" thru
0.260".1
2
3
4
5
6
7
8
9
10
11
12
13
14
15
16
17
18.025"
.033"
.042-
.050"
.058'
.066"
.075"
.083
.100
.125"
.141"
.166
.183
200
224'
232"
241
.249'Figure 8: Comparison of Resonance Response Curves for Similar
Carbon Reference Standards - High Frequency, High Gain
Carbon Weave
Comparison Samples
(Resonance - High Frequency)
Notes:
- u-- 1. Nulled on 0.020" thick carbon weave
U owr section.
- 2. Setup:
a) gin-l4dB
b uency = 313KHz
- c) rotation = 150
d)HPOS=50%
V POS = 20%
5 3. Thickness range is as follows:
- -- null 0.020
-a 1 0.030
' . _2 0.040
3 0.050
4 0.060
--5 0.070
No 6 0.080
No bulk x 7 0.090
8 0.100
9 0.110
-- 10 0.120
Figure 9: Comparison of Resonance Response Curves for Similar
Carbon "Aircraft Structures" - High Frequency, High Gain
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Roach, D.; Dorrell, L.; Kollgaard, J. & Dreher, T. Improving aircraft composite inspections using optimized reference standards, article, October 1, 1998; United States. (https://digital.library.unt.edu/ark:/67531/metadc711418/m1/12/: accessed April 24, 2024), University of North Texas Libraries, UNT Digital Library, https://digital.library.unt.edu; crediting UNT Libraries Government Documents Department.