NASA Technical Memorandum 110298
U. S. Army Research Laboratory Technical Report 1288
Finite-Element Vibration Analysis andModal Testing of Graphite Epoxy Tubesand Correlation Between the Data
Barmac K. TaleghaniVehicle Structures Directorate
U.S. Army Research Laboratory
Langley Research Center, Hampton, Virginia
Richard S. Pappa
Langley Research Center, Hampton, Virginia
November 1996
National Aeronautics and
Space Administration
Langley Research Center
Hampton, Virginia 23681-0001
https://ntrs.nasa.gov/search.jsp?R=19970007012 2018-01-31T20:33:22+00:00Z
Finite-Element Vibration Analysis and Modal Testing of
Graphite Epoxy Tubes and Correlation Between the Data
B. K. Taleghani* and R. S. Pappa**
NASA Langley Research Center
Hampton, Virginia
SUMMARY
Structural materials in the form of graphite epoxy composites with
embedded rubber layers are being used to reduce vibrations in rocket motor
tubes. Four filament-wound, graphite epoxy tubes were studied to evaluate
the effects of the rubber layer on the modal parameters (natural vibration
frequencies, damping, and mode shapes). Tube 1 contained six alternating
layers of 30-degree helical wraps and 90-degree hoop wraps. Tube 2 wasidentical to tube 1 with the addition of an embedded 0.030-inch-thick rubber
layer. Tubes 3 and 4 were identical to tubes 1 and 2, respectively, with the
addition of a Textron Kelpoxy elastomer. This report compares experimental
modal parameters obtained by impact testing with analytical modal
parameters obtained by NASTRAN finite-element analysis. Four test modes
of tube 1 and five test modes of tube 3 correlate highly with corresponding
analytical predictions. Unsatisfactory correlation of test and analysis results
occurred for tubes 2 and 4 and these comparisons are not shown. Work is
underway to improve the analytical models of these tubes. Test results clearlyshow that the embedded rubber layers significantly increase structural modal
damping as well as decrease natural vibration frequencies.
* Army Research Laboratory, VSD
** NASA Langley Research Center
INTRODUCTION
The Army Research Laboratory's Vehicle Structures Directorate
(ARL, VSD) has a Technology Program Annex (TPA) agreement with the
Army Missile Command (MICOM) to assess the use of layers of rubber to
increase damping in filament-wound, graphite epoxy rocket motor tubes. The
first phase of the investigation involves modeling and testing four tubes (two
with a thin rubber layer at the center of the layup and two without the rubber
layer). MICOM fabricated the tubes, performed initial dynamic tests, and
delivered their test results and the four tubes to NASA Langley. Additional
tests were performed at NASA by suspending the tubes from low-frequency
supports, mounting accelerometers, and exciting the tubes with impact loads.
Processing the accelerometer responses yielded natural frequencies, mode
shapes, and modal damping. The effects of the rubber layer was then
evaluated as was the ability of the analytical models to predict modalcharacteristics of the tubes.
DESCRIPTION OF TEST ARTICLES
The tubes (figure 1) have a 3.6-inch inside diameter, 41-inch length,
and wall thicknesses varying from 0.072 inches to 0.102 inches depending on
the layup. The filament winding process used H-IM6 graphite fibers with an
anhydride epoxy resin system, wet winding over an aluminum mandrel, and
an oven cure in a rotisserie. The cure cycle ramped from an ambient
condition to 300 degrees Fahrenheit and held for three hours to ensure
complete curing of the matrix. The cylinders were allowed to cool overnight
to room temperature, extracted from the mandrel, and then cut to length.
Four tubes (table 1) were manufactured. The baseline tube (tube 1),
depicted in figure 2, consisted of alternating layers of 30-degree helical wraps
and 90-degree hoop wraps for a total of six layers. Tube 2 is identical to tube 1with the addition of a 0.030-inch-thick layer of Kevlar-reinforced polyisoprene
rubber. The rubber layer was introduced to the cylinder by interrupting the
winding process in the middle of the layup. The rubber layer was hand laid,
trimmed, and seamed to provide a uniform thickness. The filament winding
process was then continued to complete the cylinder fabrication. Tube 3 is the
same as the tube 1 except the epoxy was modified with elastomeric copolymer
particles ranging from 0.01 to 10 microns in diameter. The concentration of
the spheres in the epoxy was 5 percent by weight. Tube 4 is the same as tube 2
except for the addition of an elastomer-modified matrix. The previously
mentioned cure cycle was used for all four tubes.
MODAL TEST METHOD
Figure la shows the test configuration. Each tube hung on soft bungee
cords to obtain free-free boundary conditions. Figure 3 shows the 4 excitation
positions and 25 accelerometer positions used in each test. Frequency
response functions (FRFs) were measured with impact excitation using a
commercial "modal testing" hammer; i.e., a hammer with an integral force
gauge. Standard test procedures generated the FRFs with exponential
response windowing and 5 ensemble averages. The data-analysis software
applied a correction term that removed the increased-damping effects of the
exponential window. Each FRF had 512 lines of resolution from 0 to 4096 Hz.
The accelerometer positions used in these tests correspond to those
used in previous tests performed at MICOM. They adequately measure radial
motion only in the x-z plane passing through the centerline of the tube.
Analysis results obtained after testing(discussed in the results section of the
report) show that many more sensors are necessary to fully measure the
vibration(modal) characteristics of the tubes up to 2000 Hz.
Figure 4 shows sample FRFs for each of the four tubes. These data are
driving-point FRFs of each tube at test point 15Z (i.e., at location 15 in the z
direction). A driving-point FRF is one in which the excitation and responseoccur at the same location and in the same direction. The data are of high
quality based on the smoothness of the curves and the regularity of the
driving-point phase angles (always between 0 and 180 degrees). A count of the
resonant peaks shows that there are at least 20 modes from 0 to 4096 Hz.
The accelerometer positions used in these tests correspond to those
used in previous tests performed at MICOM. They adequately measure radial
motion only in x-z plane passing through the centerline of the tube. Analysis
results obtained after testing (discussed in the results section of this report)
show that many more sensors are necessary to fully measure the vibration
(modal) characteristics of the tubes up to 2000 Hz.
The Eigensystem Realization Algorithm (ERA) (refs. 1 and 2) identified
structural modal parameters (natural frequencies, damping, and mode
shapes) from the FRFs. ERA is a multiple-input, multiple-output, time-
domain technique which analyzes free-decay data or impulse response
functions derived by inverse Fourier transformation of FRFs. The FRFs for
each tube were analyzed with ERA in 5 separate analyses as follows: 1) using
all 100 FRFs (4 excitations and 25 responses) simultaneously, 2) using the 25
responses for excitation 1X only, 3) using the 25 responses for excitation 15Z
only, 4) using the 25 responses for excitation 17Z only, and 5) using the 25
responses for excitation 20Y only. The best result for each mode based on the
Consistent-Mode Indicator (CMI) (ref. 1) and visual inspection of mode
shapes was selected from among the 5 analyses of each tube.
MODAL AND TRANSIENT RESPONSE ANALYSIS
Finite-Element Model
The MSC/NASTRAN (ref. 3) finite-element model is shown in
figure 5. The model consisted of 1312 equally spaced quadrilateral elements,
1328 nodes, and 7968 degrees of freedom. The CQUAD4 isoparametric
membrane-bending plate element was used to model the tubes. The model
incorporated 16 elements around the circumference and 83 elements along
the length. Lumped masses were added as individual point masses located at
designated nodes of the finite-element model to account for the weight of the
instrumentation (figure 6). As shown in figure 6, 3 triple-axis accelerometers
(weighing 22 grams each) were located at the ends of the tube, (b) 15 single-
axis accelerometers (weighing 2 grams each) were placed 5 inches apart on
each side of the longitudinal axis of the tubes, and (c) 1 single-axis
accelerometer was located on top. Accelerometers were modeled as point
masses and were not offset from the structural nodes. The CONM2
NASTRAN mass element was used for the point masses.
The Integrated Design Engineering Analysis Software, I-DEAS, (ref. 4)
was used for pre-and post-processing. A universal file translator transferred
3
the mesh information into the NASTRAN environment to create the bulk
data deck file for finite-element analysis. Table 2 shows the material
properties for the analysis. A NASTRAN MAT8 material card defined
orthotropic material properties for isoparametric shell elements. Lacking
precise knowledge of the constituent materials, the authors used data given
by Tsai (ref. 5). The density in table 2 is the weight of the tube divided by the
volume of the tube. A separate material card was developed for the layer of
rubber. The rubber properties also appear in table 2.
Eigenvalue Analysis.
The analysis of the composite tubes presented here was performed
using version 68 of the MSC/NASTRAN commercial finite-element analysis
computer code. MSC/NASTRAN Solution Sequence 103 was used to analyze
the model. Mode shapes and frequencies were calculated in
MSC/NASTRAN using the Lanczos method (ref. 3). It was decided to
determine all modes with frequencies up to 2000 Hz.
Direct Transient Response Analysis
Transient response analysis allows for studying and optimizing the
effect and the location of the rubber layer within the composite cylinder. The
following result is presented to serve as a baseline for future work on
investigating the damping effects of the rubber layers in these tubes.
Direct transient response analysis allows the computation of the
general dynamic response of a structure. This method performs a numerical
integration on the complete coupled equations of motion, as follows:
[M]{£} + [C]{,_} + [K]{x}
--{o}
={f} (1)
where:
[M] = Mass Matrix
[C] = Damping Matrix
[K] = Stiffness matrix
}_l = Forcing function= Acceleration vector
{._} = Velocity vector
{X} = Displacement vector
Ix,,} =Initial displacement vector
4
The first bending vibration mode of frequency 09 was used as an initial
displacement condition {X 0 } of the structure. A FORTRAN program was
written to set the nodal displacements in the NASTRAN input data deck
equal to a scaled value of the mode shape. A time-displacement plot of one of
the degrees of freedom which is located on the top of the tube (node 10374) is
shown in figure 7a and 7b.
In NASTRAN, the damping matrix[C] is, in general, comprised of
several matrices. In the present situation only the modal damping factors
were known from the testing. Therefore, the damping matrix used in direct
transient response calculations was:
[C]_- [K](D
where:
g = twice the modal damping factor
RESULTS
Test Results
Measured frequencies and damping factors are given in table 3. Thesame set of 15 modes occurs for each tube. The mode designations are as
follows:
nB-Z
nBR
Love
The nth bending mode in the Z direction.
The nth breathing mode (n = axial direction half-wave
count).Love modes can be described as ovalization of cross
section at right (R-Love) and left (L-Love) ends of thetubes. These modes are discussed in more detail on
pg.315 of ref. 6.
Modes with CMI values (ref.1) of at least 80 percent are identified with
high accuracy and are highlighted with bold type in table 3. Modes with high
Modal Phase Collinearity (MPC) values (ref. 1) exhibit classical normal-mode
behavior. Low MPC usually indicates identification inaccuracy rather than
physical non-normal mode behavior. Table 3 shows that the tubes with a
rubber layer (tubes 2 and 4) have considerably higher material damping than
those without the rubber layer (tubes 1 and 3).
Figures 8 through 11 show the experimental mode shapes for tubes 1 through
4, respectively. These wireframe plots show motions only at the 255
accelerometer positions used in the test. The measurements were made
mostly in the Z direction (figure 3) and only motion in this direction isunderstandable. Additional sensors at other circumferential locations are
necessary to fully measure the modal characteristics.
Figure 12 shows the numerical correlation of the mode shapes for various
pairs of tubes using the Modal Assurance Criterion (MAC) (ref. 7). The size of
each rectangle plotted in figure 12 is proportional to the corresponding MAC
(0 - 100%). Pairs of modes with MAC values of at least 70 percent are
darkened for emphasis. This is an indication that the mode shapes are not
affected by the rubber layer.
Analysis Results
Analytical and experimental results were obtained for all 4 tubes.
NASTRAN analysis determined 32 modes for tubes 1 and 3, and 134 modes
for tubes 2 and 4 that included the rigid body modes in the frequency range of
0-2000 Hz. The increase in number of modes for tubes 2 and 4 is attributed to
the increase in flexibility of the tubes with the rubber layer.
The correlated mode shapes and corresponding analysis frequencies of
tubes 1 and 3 are shown in figure 13a-13e. The modes consist of one Love
mode, three bending modes, and one breathing mode. The 3-D modes give a
better understanding of the complexity of the dynamic behavior of the tubes.
Although a large number of modes were predicted by NASTRAN, no modescorrelated for tubes 2 and 4. Since there is no correlation between the
experimental data and analytical results for tubes 2 and 4 at the present time,
only the correlation results for tube 1 and tube 3 will be discussed.
Correlation of Test and Analysis Results
In this work, the Modal Assurance Criteria (MAC) (ref. 7) was chosen
for correlation purposes. Each analysis mode shape is correlated with each
test mode shape as follows:
(j)]2MAC - (3)
v/2T(j)tp2(jj,,l "-
where:
_1= Analysis mode shape
_2 = Test mode shape
6
The MAC is a scalar value between zero and one that measures
similarity of mode shapes. Values above 0.70 indicate a good match between
the compared modes.
Figures 14a and 14b show the numerical correlation of the mode shapes
using MAC for tubes 1 and 3, respectively.The size of each rectangle is
proportional to the corresponding MAC (0-100%). Pairs of modes with MAC
values of at least 70 percent are darkened for emphasis. The analytical mode
shapes which have a MAC value with the test results of at least 70% are
plotted in figures 13a-13e. The test mode shapes for all the tubes are plotted in
figures 8 - 12. Modes with high correlation include bending, breathing, and
Love modes.
For tube 1, four modes matched between test and analysis as shown in
table 4. The right side love mode had the best correlation. The measured and
predicted frequencies were 688 Hz and 523 Hz, respectively. The mode shape
is shown in figure 13a. The MAC value of 0.93 indicated that the mode
shapes are practically identical. The first breathing mode had a MAC value of
0.89 and measured and predicted frequencies of 808 Hz and 637 Hz,
respectively. The mode shape is shown in figure 13b. The third result was
the second breathing mode with measured and predicted frequencies of 845
Hz and 788 Hz, respectively. The mode shape is shown in figure 13c. Thisresult had a correlation factor of 0.91. For the fourth mode, the measured
frequency is 2195 Hz and the respective frequencies of the analysis mode is1926 Hz. The correlation factor is 0.87. This mode is the third bending shown
in figure 13d.
Tube 3, had five modes that correlated between the analysis and test
results as shown in table 5. The first mode that correlated had a test frequency
of 724 Hz and analysis frequency of 523 Hz. The correlation factor or MACvalue was 0.94 and the mode was the R-love shown in figure 13a. The next
mode that correlated with a MAC value of 0.89 had test and predicted
frequencies of 854 Hz and 637 Hz, respectively. The mode type was the first
breathing shown in figure 13b. The third mode was the second breathing
mode shown in figure 13c. The MAC value of this correlation was 0.89 and
the test and predicted frequencies were 893 Hz and 788 Hz. The fourth mode
had a test frequency of 1100 Hz and analysis frequency of 1142 Hz. The MACvalue was 0.76 and the mode was the third breathing mode shown in figure
13d. The fifth test mode had a frequency of 2305 Hz and analysis frequency of
1926 Hz. The MAC value was 0.82 shown in figure 13e.
Test results were obtained and used to evaluate the effect of the rubber
layer. Table 6 shows the comparison of matched mode shapes and their
respective frequencies for tube 3 without the rubber layer and tube 4 with the
rubber layer. There were 15 modes not including the rigid body modes thatmatched between these two tubes. The best correlation (with frequencies of
474 Hz and 433 Hz, respectively) was mode 1. The MAC values ranged from
0.99 to 0.61. The largest difference in frequencies occurred between modes no.
7
12 of tube 3 having a frequency of 2517 Hz and tube 4 having a frequency of
1866 Hz. The frequencies for tube 4 were generally lower than for tube 3 on
the other hand damping values in tube 4 were higher than that in tube 3 due
to the presence of the rubber layer in table 6. The experimental frequencies
and damping values are summarized in table 3.
CONCLUDING REMARKS
This report described test and analysis results obtained for four graphite
epoxy missile tubes, two having an embedded layer of rubber. The rubber
layer significantly increased the damping of the structure which reduces
vibration during operation. Measured modal damping factors (percent of
critical damping) of the tubes without the rubber layer were approximately
0.5%, increasing to approximately 2-3% for the tubes with the rubber layer.
The embedded rubber layer also caused natural frequencies of the modes to
decrease by approximately 10-20%.
Modal tests were performed using 25 accelerometer locations. These
accelerometer locations adequately measured the motion only in a single
plane passing through the centerline of the tube. Subsequent NASTRAN
analytical predictions showed that additional measurement locations are
necessary to fully characterize the complex motion of the tubes in the
frequency range of interest (0-2000 Hz).
NASTRAN finite-element analysis predicted 26 elastic modes below 2000 for
the tubes without the rubber layer (tubes 1 and 3) and 128 elastic modes below
2000 Hz for tubes with the rubber layer (tubes 2 and 4). The large increase in
modes is attributed to increased flexibility of the tubes having the rubber
layer. Based on the 25 available measurements, 4 of the NASTRAN modes oftube 1 and 5 of the NASTRAN modes of tube 3 correlated highly with the test
results. Unsatisfactory test-analysis correlation occurred for all modes of tubes
2 and 4. It may be necessary to perform additional tests with more
measurement locations in order to resolve the discepancies between test and
analysis due to the complex nature of the (predicted) mode shapes.
REFERENCES
1. Pappa, R. S., Elliott, K. B., Schenk, A, Consistent-Mode Indicator for the
Eigensystem Realization Algorithm, J. Guidance, Control, and Dynamics,
Vol. 16, No. 5, Sept. 1993, pp. 852-858.
2. Pappa, R. S., Eigensystem Realization Algorithm User's Guide for
VAX/VMS Computers, Version 931216, NASA TM-109066, May 1994.
3. MSC/NASTRAN Handbook for Composite Analysis, The MacNeal-
Schwendler Corporation, 1993.
4. I-DEAS Test Data Analysis User's Guide, Structural Dynamics Research
Corporation, 1990.
5. Tsai, S. W., Composite Design - 1985, Think Composite, Dayton, OH, 1985.
6. Belvin R.D., Formulas For Natural Frequency and Mode Shape, Kreiger
Publishing Co., Malabar, FL, 1984.
7. Ewins, D.J., Modal Testing: Theory and Practice, John Wiley and Sons
Inc., New York NY, 1984.
Table 1
Tube Configurations
Tube 1
Tube 2
Tube 3
Tube 4
Alternating layers of 30-degree helical wraps and 90-degree
hoop wraps for a total of six layers.
Same as first tube with the addition of a 0.030-inch-thick
layer of Kevlar-reinforced polyisoprene rubber.
Same as first tube, except the matrix was modified with an
elastomer*.
Same as second tube, except the matrix was modified with
an elastomer*.
Matrix formulation for tubes 1 and 2:
1. Shell Epon 826 (diglycidal ether of bisphenol A)
2. CIBA GEIGY RD-2 (diluent)
3. CIBA GEIGY 906 (nadic methyl anhydride)
4. Pacific Anchor chemical company Imicure EMI-24
100 grams
10 grams
90 grams
1.5 grams
* Matrix Formulation for tubes 3 and 4:
1. Shell Epon 826 (diglycidal ether of bisphenol A) 60 grams
2. CIBA GEIGY RD-2 (diluent) 10 grams
3. CIBA GEIGY 906 (nadic methyl anhydride) 90 grams
4. Pacific Anchor chemical company Imicure EMI-24 1.5 grams
5. Textron Kelpoxy G293-100 (75% 828, 25% Acrylonitrile) 40 grams
10
Table 2.
MATERIAL PROPERTIES
Tube Configuration
Inside radius = 1.841 in
Thickness(without the layer of rubber) = 0.072 in
Tube length = 41 in
Tube weight(without the layer of rubber) = 2.416 lb
Composite structure properties
E, = 29.44x106 psi
E 2= 1.624 xl06 psi
G_2=1.218 xl06 psi
(_ =1.218 xl06 psi
G2:=1.218 xl06 psi
V_2=0.32
/9=1.9913 xl0-_lb/in 3
Rubber properties
E_=450 psi
E 2 = 450 psi
Gl2 =200 psi
(_: =200 psi
C2_ =200 psi
V12=0.49
/9=0.89 xl0 -4 lb/in 3
11
Table 3.
Measured Frequencies and Damping of Tubes 1- 4
(a) TUBE 1
Mode
Natural
Frequency,Hz
459
DampingFactor,
6BR
%
0.26
1.51
CMI, %
98
9
MPC, %
991B-Z
2B-Z 1158
3B-Z 2195 0.63 93
17
99
974B-Z 2298 0.57 89
5B-Z 2387 0.69 90 99
6B-Z 2542 91 96
96 98
0.78
0.857B-Z 2754
R-Love 688 0.55 94 99
L-Love 726 0.52 97 99
1BR 808 0.20 98 99
2BR 845 0.46 95 98
3BR 1045 2.53 8 25
4BR 1430 1.84 64 70
5BR 1964 1.60 89 99
1.22 32 652489
(b) TUBE 2
Mode
Natural
Frequency,Hz
431
DampingFactor,
%
0.32
CMI, % MPC, %
1B-Z 98 100
2B-Z 1184 5.08 5 32
3B-Z 1606 3.02 49 88
4B-Z 1674
5B-Z 1801
6B-Z 1958
7B-Z 2229
R-Love 555
L-Love 575
1BR 691
2BR 741
2.83
2434
3BR
74 9O
2.77 60 86
2.14 50 96
1.99 17 78
2.79 67 84
2.73 88 93
3.28 89 98
2.27 94 99
4BR
5BR
473.14
6BR
61911
1377 2.65 72 86
1745 2.86 28 72
1.73 80 94
12
Mode
1B-Z
2B-Z
3B-Z
Natural
Frequency,Hz
474
1178
2305
4B-Z 2424
5B-Z 2517
6B-Z
7B-Z
R-Love
L-Love
1BR
2BR
3BR
4BR
5BR
6BR
Mode
1B-Z
(C) TUBE 3
2B-Z
3B-Z
4B-Z
5B-Z
6B-Z
7B-Z
2670
2879
724
DampingFactor,
%
0.26
3.15
0.29
0.60
0.63
0.97
0.79
0.49
CMI, % MPC, %
98 99
23 39
70 92
88 93
90 96
84 92
96 99
97 99
784 1.02 79 80
854 0.18 97 98
893 0.69 83 86
1.60
2.51
1.19
1100
1490
2O64
2600 1.40
Natural
Frequency,Hz
433
(d) TUBE 4
DampingFactor,
%
0.32
1.771061
1675 2.31
1734 2.39
1865 2.39
2037 1.86
0.82
74
35
93
63
CMI, %
99
16
77
38
97
78
2258
R-Love 560 3.53
L-Love 659 2.99
1BR 712 2.17
MPC, %
100
20
38 46
72 94
52 90
85 97
24 46
9248
34 83
82 97
2BR 778 1.81 95 99
3BR 989 2.88 48 54
4BR 1332 2.06 71 78
5BR 1789 2.08 58 78
2.116BR 1969 73 96
13
Table 4.
COMPARISON OF MATCHED MODE SHAPES
AND THEIR FREQUENCIES FOR TUBE 1.
MAC
VALUE
0.93
0.89
0.91
0.87
MEASURED
FREQUENCY
688
808
845
2195
COMPUTED
FREQUENCY
523
637
788
1926
MODE
TYPE
Right-side Love
Fig. 8h / Fig. 13a
1st Breathing
Fig. 8j / Fig. 13b
2nd Breathing
Fig. 8k / Fig. 13c
3rd Bending - Z
Fig. 8c / Fig. 13d
14
Table 5.
COMPARISON OF MATCHED MODE SHAPES
AND THEIR FREQUENCIES FOR TUBE 3.
MAC
VALUE
0.94
0.89
0.89
0.76
0.82
MEASURED
FREQUENCY
724
854
893
1100
2305
COMPUTED
FREQUENCY
523
637
788
1142
1926
MODE
TYPE
Right-side Love
Fig. 10h / Fig. 13a
1st Breathing
Fig. 10j / Fig. 13b
2nd Breathing
Fig. 10k / Fig. 13c
3rd Breathing
Fig. 10I / Fig. 13d
3rd Bending - Z
Fig. 10c / Fig. 13e
15
Table 6.
COMPARISON OF MATCHED MODE SHAPES
AND THEIR FREQUENCIES FOR TUBE 3 vs. TUBE 4
MAC
VALUE
0.99
0.92
MEASURED
FREQUENCY FOR
TUBE 3
(without rubber layer)
474
724
MEASURED
FREQUENCY FOR
TUBE 4
(with rubber layer)
433
561
0.85 784 659
0.76 854 711
0.74 893 778
0.74 1490 1333
0.61 2305 1734
0.80 2424 1789
0.84 2517 1866
0.85 2670 2038
28790.75 2258
16
(a) Test Article
(All 4 tubes are similar in appearance)
41 in.
Composite layers
__ including rubber
0.072-0.102 in
Dependingon layup
(b) Geometry
Figure 1. Graphite epoxy tubes
17
F
to_tgle_ respect
90
Outside surface
+/- 30
9O
Rubber
+/- 30
9O
+/- 30
Inside surface
Figure 2. Composite layup
18
UHDEFORMED SHAPE MICOM TUBES
B 1B
1
Z x
'FY
(a) Test Location Numbers
Location:
X
Y
Z
1 2 3 4 5 6 7
X
8 9 10 11 12 13 14 15 16 17 18 20
X
X X
(b) Excitation Positions (4)
Location: 1 2 3 4 5 6 7
X
Y
Z
X
X
X X
i
X X X X X
8 9 10 11 12 13 14 15 16 17 18 20
X X
X X X
X X X X X X X X X X X
(c) Accelerometer Positions (25)
Fig. 3. Test Set-Up
19
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.............. \ .......10000 ..... • :.
.... i[/_ ..... I - • . , .... * .... * ....
.... i , . . i ...... i .... _ .... i .......... i,., I I"" :::_ I:\^/_:: :_i!!
• • • l l .... l .... o .... t .... l .... o ....
,- 1000 ..................................7" ! .... I .... I , , I .... I ........l_ ...... - ' I ........ I .... I .... I I
•° .... , , ili, !i;, ii ........, ,!::",
................ I .... l .... I .... I .... I
..... , .... t .... ! .... * .... * .... i .... D100-. . , .... , ..... , .... , .... '
l o * i i' " " I ........ I .... I ........ ! .... I .... Iiiii!iiliiill!ii!• . I . i .... l . . . l .... t .... l .... l
.......... I .... I .... I .... t .... I .... I
...... J .... o .... * .... * .... * .... * .... i
10e 5oo :o_,o 15oo ;,ooe 25oo 3B_,0 35oo 4o_e
FREGUENCY, HZ
Fig. 4b. Driving-Point FRF for Tube 2 at Position 15Z
20
a.
-ra. -gB
-18B1E5
.... I .... I . . I ........ I . , II . I i I I.... , ........ , .... , , , I
...... i • I .... i • • ° I .... i ........
.... I ..... I , , I , . I .... I .... I.... I .... I .... I • • , • • • i .... I .................. , .... , .......... I .... :
t::i ........................1BOBB. . . . . , . . . , .... , .......... '! i :::: i/II:: V:V i] __ i "." "." i !it . , l ..............
........... i .... i .... I .... I• . . . i . . i .... , .... i .... i
::; i .............. I .... I .... I1BBB- , t .• ' ' t ........ I .... I .... I
i.-,i .... ' " ° ' ' .... i .... I .... I
• . , • ...... I .... I .... I .... I.... • ....... i " i i....... t .... I .... I .... I .... I .... I .... I
. lii /ii i iiiii iii!iiiiili........... I .... I .... I .... I .... I .... I
• I .... I .......... , i I I
......... I .... I .... I I I............... i .... i .... I ....
I_B ' .... ' .... '......... , t i
• " " I ............ I .... I .... I .... I .... I• . I ..... I .... I .... * .... , .... I .... I
...... I .... I .... , .... i . . •• , I .... I .... I .... I .... I .... I .... I ....
. . l .... i .... i .... i .... , .... i .... i .... i
2B0 500 1000 1508 2000 250;} 30;_0 3500 4B00
FREQUENCY, HZ
Fig. ,Ic. Driving-Point FRF for Tube 3 at Position 15Z
IIilllllillllIIIllllllllllllilllliIilllllIIIIIIl llllIllllIlllllllIlllllllllIIIlllllll
- o-I : : i i i I-18B
1E5_
.............. : : ; i '
.......... i .... i .... i .... Ii i I i
.... I .... I .... , .... i .... I .... i
.... i .... I .... I .... i .... i .... I .... I• . i ..... * .... , .... i .... i .... i
]_ I I , I I .... I .... i• " I , I I........ I .... I .... i .... I .... I .... t
i ..... I .... i .... i .... I .... I .... tI I . . . . . t .... I
, i i
........ I .... I .... I ' I I
IBI_ ' .... ' .... ' .... ' .... ' .... ' .... ' .... '
• i i
.......... I .... I .... I .... I .... I .... I
.......... I .... I .... n .... i .... o .... I
t .... I .... I .... : .... Ii i i
.......... I ........ I .... I .... I .... I
.............. I .... , .... I .... t .... l• . I .... I .... t .... i .... I .... i
i i I
1{_ ' ' '0 5_i_ 1;};}IB 15BB 2001a ;_5iBO 3_00 35B0 4B_
FREQUENCY, HZ
Fig. 4d. Driving-Point FRF for Tube 4 at Position ISZ
21
Figure 5. Finite Element Model
22
ACCELEROMETERS
D [3 [3 D [3 ©7777177777177777717773777777 77
.77 1777377777717777771777 77777 77771777777 777777 I _n77777737777777777_7717771_ 17177777777777777177777377777777777717777777777777
177777n777777177777777771771777777777_1_777177777777777777777 37777777777777177777N_7777777777777177777717771737777_777777777777777777777 7777777777777717777777
--r7_........................... r7_.......r_-.....-_D
FINITE ELEMENT MODEL
O = TRIPLE AXIS ACCELEROMETERS
_7 = SINGLE AXIS ACCELEROMETERS
Figure 6. Accelerometer locations and coordinate system.
23
O4
mr-,---,,-- m
,-, Q2d
Im QO
-02
-O4
O00 004 008
(sec)
Figure 7a. Transient Response for node 10374 in y-direction.
bending mode decay
Q10_6
First
3qg'_
L
Figure 7b. Location of the node 10374 on the Finite Element model
24
FREQUENCY, HZ " 459 CMI, X " 97.50
DAMPING, X - 8.Z63 MPC, X - 59.38
1 9
Z
Fig. 8a. 1st Bending Mode of Tube 1 (Mode IB-Z)
iilOilliillllOlllllllll ll IIIJlliill I iliJl I llllJllilllJ II ililollllllllliOOlllliOJllllOl
FREQUENCY, HZ - 1150 CMI, _ - 8.90
DAMPING, _ • 1.509 MPCo _ - 17.04
: ..... 5-_ .... -_-.... __ 7
Fig. 8b. 2nd Bending Mode of Tube 1 (Mode 2B-Z)
25
FREQUENCY, HZ ° 2195 CMI, _ ° 92.94
DAMPING, _ - @.632 MPC, % ° 9e.?e
Fig. 8c. 3rd Bending Mode of Tube 1 (Mode 3B-Z)
FREQUENCY, HZ • ZZ98
DAMPING, _ - e.574
CMI, _ = 89.38
MPC, _ • 96.87
2 6
1 _ _ 5 7 9
Z
Fig. 8d. 4th Bending Mode of Tube 1 (Mode 4B-Z)
26
FREQUENCY, HZ " 2387
DAMPING, _ = 0.686
CMI, _ - 89.99
MPC, X - 98.84
Fig. 8e. 5th Bending Mode of Tube 1 (Mode 5B-Z)
FREQUENCY, HZ • 2542
DAMPING, _ - 8.77B
CMI, _ - 91.e9
MPC, _ - 96.83
Z
Fig. 8f. 6th Bending Mode of Tube 1 (Mode 6B-Z)
27
FREQUENCY, HZ - 2754DAMPING, X • 0.847
CMI, X " 95.52
MPC, X - 98.41
4 6 82 9
Z
Fig. 8g. 7th Bending Mode of Tube 1 (Mode 7B-Z)
28
FREQUENCY, HZ " 68B
DAMPING, _ - 0.548
CMI, _ - 93.71MPC, _ " 98.78
9
1 2 3 4 S 6 7___ I
Z
Fig. 8h. Rightside Love Mode of Tube 1 (Mode R-Love)
FREQUENCY, HZ • 726
DAMPING, X • 0.5Z4
CMI, _ - 97.08
MPC, X = 99.18
7 8 9
Fig. 8i. Leftside Love Mode of Tube 1 (Mode L-Love)
29
FREQUENCY, HZ - 808
DAMPING, _ - B.ZBB
CMI, X - 98.B9
MPC, X - 99.37
4 5
Fig. 8j. 1st Breathing Mode of Tube 1 (Mode 1BR)
j_i_ii_ii_i_iii_ii_ii_i_iii_j__ii_ii_ij_ii_ii_i_ii_ji_i
FREQUENCY, HZ - 845 CMIo X • 94.58
DAMPING, X - B.459 MPC, X - 97.93
2 3 _ 4 9
....
Fig. 8k. 2nd Breathing Mode of Tube 1 (Mode 2BR)
3O
FREQUENCY, HZ I 1845
DAMPING, _ • 2.529
CMI, _ = ?.7g
MPC, _ = 25.17
2 3 7 8
Fig. 81. 3rd Breathing Mode of Tube 1 (Mode 3BR)
llllllll__llllllllllllllllllll_llll_lllllllllllllllll_llll_lllll_llllllllll_ll_lll_lll
FREQUENCY, HZ • 1430
DAMPING, X i 1.844
CMI, _ " 63.86
MPC, _ = 78.12
2 6 9
__ _ ......... 5 _7 .......
Fig. 8m. 4th Breathing Mode of Tube 1 (Mode 4BR)
31
FREQUENCY, HZ - 1964
DAMPING, _ - 1.598
CMI, _ - 89.B8
MPC, _ - 98.7Z
5 8
Z
Lx
Fig. 8n. 5th Breathing Mode of Tube 1 (Mode SBR)
iii_ij__ii_i_i_j_ii_i_iiii_i_j_j_iij_jjiij_iii_iii_ii
FREQUENCY, HZ • 24B9
DAMPING, _ - 1.Z19
CMI, X • 31.09
MPC, X - 65.Z6
2 4 7 9
-- _ -- m -- .... -- ----
Fig. 80. 6th Breathing Mode of Tube 1 (Mode 6BR)
32
FREQUENCY, HZ " 431
DAMPING, _ - B.B2B
CMI, _ - 98.26
MPC, _ - 99.81
1 9
I T I-
L -Ji m --J ..... -_
Fig. 9a. 1st Bending Mode of Tube 2 (Mode 1B-Z)
iiii_j_iii_i_ii_i_iii_iiiiii_iii_i_i_ji_iiiji_ijiiim_iii_i_iii_
FREQUENCY, HZ - 1184 CMI, _ - 5.83
DAMPING, X - 5.Q78 MPC, _ - 32.05
9
n--- z .... 3 ..... 4 s ___6._ .... _7 .... 8
1 -----_Y-...._---__"
Z
Lx
Fig. 9b. 2nd Bending Mode of Tube 2 (Mode 2B-Z)
33
FREQUENCY, HZ ° 1606 CMI, _. o 48.75
DAMPINGj _ - B.010 MPC, _. ° 88.BB
2 8
.... _,__ ..... _ ..... :
Fig. 9c. 3rd Bending Mode of Tube 2 (Mode 3B-Z)
FREQUENCY, HZ - 1674
DAMPING, X - 2.BZ5
CMI, _ - 74.01
MPC, _ - 90.Z2
Fig. 9d. 4th Bending Mode of Tube 2 (Mode 4B-Z)
34
FREQUENCY, HZ - 1881 CMI, X " 59.56
DAMPING, X - 2.766 MPC, X - 85.67
Fig. 9e. 5th Bending Mode of Tube 2 (Mode 5B-Z)
FREQUENCY, HZ • 1958 CMIo _ - 50.35
DAMPING, _ - 2.139 MPC, _ - 95.48
Z 4 7 9
Fig. 9f. 6th Bending Mode of Tube 2 (Mode 6B-Z)
35
FREQUENCY, HZ • 22Z9 CMIo _ - 17.01
DAMPING, _ • 1.987 MPC, _ o 78.38
1 2 4 6 8
Z
Fig. 9g. 7th Bending Mode of Tube 2 (Mode 7B-Z)
36
FREQUENCY, HZ = 555 CNl, _ - 67.20
DAMPING, X - 2.7B6 MPC, X = 84.1B
1 2 __ B .... 4 .... 5 .... iS Z i
Z
Fig. 9h. Rightside Love Mode of Tube 2 (Mode R-Love)
FREQUENCY, HZ • 575 CMI, X = 88.16
DAMPING, X • 2.731 MPC, X - 92.60
2
3 4
m
5 6 7 e .... .9
z
Fig. 9i. Leftside Love Mode of Tube 2 (Mode L-Love)
37
FREQUENCY, HZ - 691
DAMPING, _ - B.28e
CMI, _ - 88.87
MPC, _ " 98.Z6
Fig. 9j. 1st Breathing Mode of Tube 2 (Mode 1BR)
FREQUENCY, HZ o 741
DAMPING, _ - Z.ZTe
CMI, _ = 93.53
MPC, _ - 98.93
2 3 4 9
Fig. 9k. 2nd Breathing Mode of Tube 2 (Mode 2BR)
38
FREOUENCY, HZ - 911DAMPING, X - 3.136
CMI, _ - 46.76
MPC, _ - 61.13
Fig. 91. 3rd Breathing Mode of Tube 2 (Mode 3BR)
ii_i_iiiiijii_iiii_iiiiiiiii_j_i_i_i_i_i_ii_i_i_iii_ii_ii_iji_iiiij
FREQUENCY, HZ - 1377
DAMPING, _ - 2.654
CMI, _ - 72.41
MPC, _ - 85.74
6 9Z 2 __3 __4___ 5 7 .......
Fig. 9m. 4th Breathing Mode of Tube 2 (Mode 4BR)
39
FREQUENCY, HZ " 1745
DAMPING, _ • 2.eSe
CMI, _ - 27.56
MPC, X - 71.56
Z
Fig. 9n. Sth Breathing Mode of Tube 2 (Mode SBR)
i o oo o omillllllJlllilll lllllJ ilililllllll ililll lilll illllllllillllllllllilll lilillJlll
FREQUENCY. HZ - Z434DAMPING, _ • 1.727
CMI, X • 80.29MPC, X - 93.67
2 71 4
5 9
1
Fig. 90. 6th Breathing Mode of Tube 2 (Mode 6BR)
40
FREQUENCY, HZ " 474 CMI, _ - 97.74
DAMPING, _ - 0.260 MPC, _ ° 98.90
1 9
1 -1 T 7
Z
Fig. 10a. 1st Bending Mode of Tube 3 (Mode 1B-Z)
FREQUENCY, HZ - 1178 CMI, _ ° 22.76
DAMPING, _ • 3.151 MPC, _ ° 39.42
9
Fig. 10b. 2nd Bending Mode of Tube 3 (Mode 2B-Z)
41
FREQUENCY, HZ - 2305
DAMPING, _ - 8.291
CMI, _ - 78.01
MPC, _ - 9Z.89
2 3 7 8
1 !!
.... 1 ..... 1 ..... 1 _ _
Fig. 10c. 3rd Bending Mode of Tube 3 (Mode 3B-Z)
FREQUENCY, HZ - Z4Z4
DAMPING, _ - 8.597
CMI, _ - 88.48
MPC, _ - 93.38
Z 6
1
1
Fig. 10d. 4th Bending Mode of Tube 3 (Mode 4B-Z)
42
FREQUENCY, HZ i 2517
DAMPING, _ " 8.629
CMI, X " 90.36
MPC, X " 96.B6
2 5 8
1 - "4-
Fig. 10e. 5th Bending Mode of Tube 3 (Mode 5B-Z)
_i_i_iiiii_iii__iii_iii_ii_ii_ii_iiiii_i_
FREQUENCY, HZ • 2670
DAMPING, X - 0.965
CMI, X - 84.29
MPC, _ - 91.57
2 4 7
i --3r-- 5 ----6-- -'Or---- 9
I
Fig. 10f. 6th Bending Mode of Tube 3 (Mode 6B-Z)
43
FREQUENCY, HZ - Z879 CMI, _ - 95.55DAMPING, X • B.TBE MPC, _ - 98.9.4
4 6 8Z 9
Fig. 10g. 7th Bending Mode of Tube 3 (Mode 7B-Z)
44
FREQUENCY, HZ ° 724 CMI, _ ° 96.64
DAMPING, _ ° 0.489 MPC, _ = 98.93
9
/T1 2 3 4 5 6 _/_ 1
F-] .....Jill....
Fig. 10h. Rightside Love Mode of Tube 3 (Mode R-Love)
i_iiiij_iii_i_i_ii_i_i_i_ii_i_iii_i_ii_ii_i_i_ii_ii_i_
FREQUENCY, HZ • 784 CMI, _ o 79.21
DAMPING, _ • 1.019 MPC, _ - 80.20
_ii 4- _ ___ 7 .... e_ ....
Fig. 10i. Leftside Love Mode of Tube 3 (Mode L-Love)
45
FREOUENCY, HZ - 854
DAMPI_Go _ - 0.102
CMI, _ - 97.17I'IPC, _ = 98.24
4 5
3_
14 .-------
Fig. 10j. 1st Breathing Mode of Tube 3 (Mode 1BR)
FREQUENCY, HZ - 893
DAMPING, _ • 0.608
CMIo _ - 83.45
MPCo _ - 86.37
Fig. 10k. 2nd Breathing Mode of Tube 3 (Mode 2BR)
46
FREQUENCY, H2 - IIB0
DAMPING, X - 1.598
CMI, X - 73.97MPC, _ = 76.79
Z 3 7 8
1 e
Z
Fig. 101. 3rd Breathing Mode of Tube 3 (Mode 3BR)
_i_l_i__ii_i_i_i_ii_l__i_llli_i_iiii_
FREQUENCY, HZ - 1490
DAMPING, X • Z.506
CMI, _ " 35.86
MPC, _ " 37.6Z
2 6 9
___5 ...... _ .... _ ....
1. _ __ ____ I 1_ - 1 ...... 1__ 1 -1
Fig. 10m. 4th Breathing Mode of Tube 3 (Mode 4BR)
47
FREQUENCY, HZ " 2864
DAMPING, _ - 1.185
CMI, _ - 92.98
MPC, _ - 97.49
Fig. 10n. 5th Breathing Mode of Tube 3 (Mode 5BR)
FREQUENCY, HZ - 26_e
DAMPING, _ * 1.B95
CMI, _ • 62.75
MPC, _ - 77.54
Fig. 10o. 6th Breathing Mode of Tube 3 (Mode 6BR)
48
FREQUENCY, HZ " 433DAMPING, _ - 0.320
CMI, X - 98.62MPC, X - 99.64
1 9
B 8
Z
Fig. 11a. 1st Bending Mode of Tube 4 (Mode 1B-Z)
i_ii_iiii_i_i_m_iiji_iii_i_i_j_ii_i_ii_ii_iii_i_iiiij_ii
FREQUENCY, HZ - 1061 CMI, _ - 16.35
DAMPING, X - 1.767 MPC, _ - 20.33
9
2 3= _4 _ s _ 6__.__3 .... D
- _ r------- - -- -- |
Fig. Ub. 2nd Bending Mode of Tube 4 (Mode 2B-Z)
49
FREQUENCY, HZ - 1675DAMPING, % " Z.3B5
CMI, X " 37.83
MPC, X - 45.79
2
3 _4 .... _ ,_-_
Z
Fig. Uc. 3rd Bending Mode of Tube 4 (Mode 3B-Z)
FREQUENCY, HZ - 1734
DAMPING, _ - 2.389
CMI, X - 72.3B
MPC, X - 94.23
2 6
1 ........ -- .......
1
Fig. lld. 4th Bending Mode of Tube 4 (Mode 4B-Z)
5O
FREQUENCY, HZ - 1865
DAMPING, _ - 2.B9e
CMI, _ - 52.49
MPC, _ - 90.2B
Fig. Ue. Sth Bending Mode of Tube 4 (Mode SB-Z)
FREQUENCY, HZ ° 2837
DAMPING, _ - 1.858
EMI, _ - 85.85
MPC, _ - 96.65
Fig. llf. 6th Bending Mode of Tube 4 (Mode 6B-Z)
51
FREQUENCY, HZ - 2258
DAMPING, _ • 0.823
CMI, _ - 23.91
MPC, _ • 45.71
2 4 6 8
Z
Fig. llg. 7th Bending Mode of Tube 4 (Mode 7B-Z)
52
FREQUENCY, HZ - 568
DRMPING, _ - 3.532
CMI, _ - 47.7Z
MPC, _ - 9Z.16
9
8
1 2 3 4 5 6 7
,I-:t....:i.........
Fig. llh. Rightside Love Mode of Tube 4 (Mode R-Love)
FREQU£NCY, HZ • 659 CMI, _ - 34.46
DAMPING, X - 2.99e MPCo _ m 83.B9
2
..... :I :I.... ........:I--1 ..................
Fig. 11i. Leftside Love Mode of Tube 4 (Mode L-Love)
53
FREQUENCY, HZ o 712
DAMPING, _ • 2.167
CMI, _ - 82.28
MPC, _ - 96.69
7
Fig. llj. 1st Breathing Mode of Tube 4 (Mode 1BR)
FREQUENCY, HZ - 778
DAMPING, _ - 1.8B8
CMI, _ - 95.31
MPC, _ - 98.55
3 4
Fig. 11k. 2nd Breathing Mode of Tube 4 (Mode 2BR)
54
FREQUENCY, HZ - 989
DAMPING, _ - 2.878
CMI, _ - 48.37
MPC, _ - 53.96
2 3 7 8
Fig. Ul. 3rd Breathing Mode of Tube 4 (Mode 3BR)
_iiiii_i_i_iiii_i_i_iij_i_i_iiii_iiij_i_i_iiii_iii_iii
FREQUENCY, HZ - 1332
DAMPING, _ - 2.055
CMIo _ - 78.53MPCo _ - 77.54
Fig. llm. 4th Breathing Mode of Tube 4 (Mode 4BR)
55
FREQUENCY, HZ - 1789 CMI, _ - 57.92
DAMPING, _ - Z.080 MPC, _ - 77.81
2 5 8
I _ 1 ___,
Fig. lln. 5th Breathing Mode of Tube 4 (Mode 5BR)
_iii_ii_iii_i_ij_iii_i_ii___ii_i_i_iii_
FREQUENCY, HZ - 1969 CMI, _ - 72.59
DAMPING, _ • 2.188 MPC, _ - 95.86
2 - ,_ 7 9
Z
b__x
Fig. 11o. 6th Breathing Mode of Tube 4 (Mode 6BR)
56
2434
2229
1958
N
1745
I 1674
NI 16E6
1377
U
Z 1184W
O 911
L 741
691W
975
555
431
[]
I--1
. r-1.
r-1
D
[_
O
[]
[]
$ m | = - ,r
TEST FREQUENCY, HZ - TUBE 1
Fig. 12a. Correlation of Tube 1 and Tube 2 Mode Shapes
I i i i I i lilillll I I I J I I Ill J illliliillil iO llillil I llliOii I iilllll J 0 I III lillili I lllliil 0 I OI
2879
2670
Z6EO
W Z517
2424
i 2305
N2064
1490
U
Z 1178W
0 11BB
893
854W
704
?24
474
i.
TEST FREQUENCY, HZ - TUB[ 1
Fig. 12b. Correlation of Tube 1 and Tube 3 Mode Shapes
57
2258
2037
1969
w 1BG5m-'1 1"/'09I-
I 1734
NT 1875
>_ 1332UZ 11161No _9w
L 770
in 712w
_- 659
560
433
[]m,03°
m.
[]• F].
[--Ii
03.
i
TEST FREQUENCY, HZ - TUBE 1
Fig. 12c. Correlation of Tube 1 and Tube 4 Mode Shapes
2079
2870
2_0m
W 2517m-J 2424I-
t 2305
N"1" 2064
>." 1490U
7" 1178w
O 1100UJre'6. 093
U] 854L,J
t- 704
724
474
[]i.o []
03
[3
D
[]
[] 13
[3
TEST FREQUENCY, HZ - TUBE Z
Fig. 12d. Correlation of Tube 2 and Tube 3 Mode Shapes
58
2258
2037
1969
1865
1789
I 1734
NI 1675
1332
U
Z llml
N0 _9U
L 778
712W
859
56g
433
o
D I--].I-7=
n
DI-7=
• r'-].
r-q.
D
[-1
TEST FREQUENCY, HZ - TUBE 2
Fig. 12e. Correlation of Tube 2 and Tube 4 Mode Shapes
2258
2037
1969
W 1885
1789
I 1784
NI 1675
>_ 1332
U
Z 1_1W
0 989W
L 778
m 712W
659
568
433
[]
[] m.
IE.
o
[]
[]El
[-1.
EE
• T _ • ffl m m D • tft • I_- m m I_
TEST FREQUENCY, HZ - TUBE B
Fig. 12f. Correlation of Tube 3 and Tube 4 Mode Shapes
59
Figure 13a - Computed Right side Love Mode for
tubes 1 and 3 (Frequency = 523 Hz)
6O
Figure 13b - Computed 1st Breathing Mode for
tubes 1 and 3 (Frequency = 637 Hz)
61
I
Figure 13c - Computed 2nd Breathing Mode for
tubes 1 and 3 (Frequency = 788 Hz)
62
Figure 13d - Computed 3rd Breathing Mode for
tubes I and 3 (Frequency = 1142 Hz)
63
Figure 13e-Computed 3rd Bending Mode
for tube 3 (Frequency = 1926 Hz)
64
.-4
Wm
I
P'4T
L)7"LODOi.in,i.
k_b--
2754
2542
2489
2387
2298
2195
1964
1430
115B
1045
845
808
726
688
459
I° I[]
[] . D. o °
Ii .fl: n n,
• ° a i
, o E3D
DOo o
] .....
i
o
o ,
II.
: n n _ .n
i
ANALYSIS FREQUENCY, HZ - TUBE 1
14a Test - Analysis Correlation for Tube 1
('n
6J
I--
I
NT
uZW
0
6_
W
2879
2670
2600
2517
2424
2305
2064
1490
1178
1100
893
B54
784
724
474
I.
o ID
I
0 0
o
D 8 . =
I
[] []
II. o
[]
o
• _ _ _ * n n * n J _ l ,
ANALYSIS FREQUENCY, HZ - TUBE 3
14b Test - Analysis Correlation for Tube 3
Figure 14. Modal Assurance Criterias for tube1 and 3
65
REPORT DOCUMENTATION PAGEFormApprovodOMB No. 0704.0188
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!1. AGENCY USE ONLY (Leave blank) 2. REPoHI DATE 3. REPORT TYPE AND DATES COVEHEEm
November 1996 Technical Memorandum
4. TITLE AND SUBTITLE 5. FUNDING NUM_FFIS
Finite-Element Vibration Analysis and Modal Testing of Graphite Epoxy WU 522-11-41-01
Tubes and Correlation Between the Data
s. AUTHOR(S)
Barmac K. Talaghani
Richard S. Pappa
7. PERFORMING ORGANIZATION NAMELS) AND ADDRESS(F-S)
NASA Langley Research CenterHampton, VA 23681-0001 andVehicle Structures Directorate
U.S. Army Research LaboratoryNASA Langley Research Center, Hampton, VA 23681-0001
II. SPONSORING / MONITORING AGENCY NAME(S) AND ADE_ESS(ES)
National Aeronautics and Space Administration
Washington, DC 20546-0001 and
U.S. Army Research LaboratoryAdelphi, MD 20783-1145
II. P_=_orT'._:.=::_ OR_--_-I_-_..ATIONREPORT NUMBER
10. SPONSG ;"-,,_G I MONITORINGAGENCY REPORT NUMBER
NASA TM - 110298
AFtL-TR- 1288
11. SUPPLEMENTARY NOTES
12L DISTRIBUTION I AVAILABILITY STATEMENT
Unclassified - Unlimited
Subject Category 39
Availability: NASA CASI, (301) 621-0390
12b. _j_HI_UTION CODE
13. ABSTRACT (Maximum 200 words)
Structural materials in the form of graphite epoxy composites with embedded rubber layers are being used toreduce vibrations in rocket motor tubes. Four filament-wound, graphite epoxy tubes were studied to evaluate the
effects of the rubber layer on the modal parameters (natural vibration frequencies, damping, and mode shapes).Tube 1 contained six alternating layers of 30-degree helical wraps and 90-degree hoop wraps. Tube 2 wasidentical to tube 1 with the addition of an embedded 0.030-inch-thick rubber layer. Tubes 3 and 4 were identical
to tubes 1 and 2, respectively, with the addition of a Textron Kelpoxy elastomer. This report compares
experimental modal parameters obtained by impact testing with analytical modal parameters obtained byNASTRAN finite-element analysis. Four test modes of tube 1 and five test modes of tube 3 correlate highly with
corresponding analyitcal predictions. Unsatisfactory correlation of test and analysis results occurred for tubes 2and 4 and these compariSOns are not shown. Work is underway to improve the analytical models of thesetubes. Test results clearly show that the embedded rubber layers significantly increase structural modal
damping as well as decrease natural vibration frequencies.
14. SUBJECTTERMS
Composite MaterialsVibration Analysis
Modal Testing
Finite Element Model
17. SECURITY CLASSIFICATION
OF REPORT
Unclassified
18. SECURITY CLASSIFICATIONOF THIS PAGE
Unclassified
NSN 7540-01-280-5500
11}. SECUHi_V CLASSIFICATIONOF ABSTRACT
lS. NUMBER OF PSn;:_
66
16. PRICE CODE
A04
20. LIMITATION OF ABSTRACT
Sl&_-,_:-_ Form 26 (l_v. 2-09)Prelcnl_d by ANSI Sld Z3_ 18
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