 Open Access
 Total Downloads : 197
 Authors : Nacerddine Djermane, Lahbari Noureddine
 Paper ID : IJERTV4IS080145
 Volume & Issue : Volume 04, Issue 08 (August 2015)
 Published (First Online): 09092015
 ISSN (Online) : 22780181
 Publisher Name : IJERT
 License: This work is licensed under a Creative Commons Attribution 4.0 International License
Investigation into the Low Amplitude Steady Vibration of a Steel Frame Model
Nacerddine Djermane1 & Lahbari N. 1Civil Engineering Department, Oum El Bouaghi University, ALGERIA
Abstract – The main object of this investigation is to determine the mode shapes and frequencies of the structure theoretically and experimentally to compare and analyze the measured and predicted values. At first, static and dynamic tests are made on samples of elements of the model in order to determine the properties of these elements and to validate the accuracy of the measurements taken on the model. Vibration records of the model subject to a low amplitude harmonic force are obtained with an automatic instrumentation connected to a microcomputer. The first few resonant frequencies and corresponding mode shapes are determined by performing consecutive tests at different levels of the model.
The specific damping capacity at each floor level is determined from the experimental results.
Preceding the experimental program, the theoretical values of the vibration modes and frequencies of the structure are calculated with the finite element program.
Finally, comparison between various theoretical and experimental values are studied and the correct resonant frequencies and mode shapes are assigned to the structure for further vibration studies
Keywords: Structure Steel Low Amplitude Vibration Construction Finite Element Method.
INTRODUCTION
In the analysis of linear structures, it is convenient to distinguish between the static and dynamic components of the applied loading to evaluate the response to each type of loading separately, and then to superpose the two response components to obtain the total effect.
In practice, the purpose of using scaled models (plastic, aluminum, steel material) is to investigate static and dynamic behavior of any structure which enables the designer to achieve an optimum design before the construction of the full size structure. Therefore, before any complex structure is built, simple tests can be made on a scale model to determine resonant frequencies, mode shapes, static and dynamic displacements and stresses for various input forces. Thus, informations are reviewed from several investigations to show that an understanding of material properties, model design and fabrication techniques, and instrumentation capabilities is required before a structural model test should be planned [1, 2, 3].
In fact, for dynamic testing purposes, major improvements have been seen in the availability, ease of operation, and reliability of basic instrumentation. Systems based on transducers, magnetic tape recorders, digital computers
processing have made it possible to handle immensely large quantities of data.
In addition, the development of specialized devices makes it possible to monitor dynamic tests much more effectively. A major step forward has been the development of computers that it make possible to carry out many elaborate structural response calculations during tests.
It is intended, in this paper, to study the experimental behavior of a framed steel model subjected to harmonic excitation with low amplitude.
A brief description of the model fabrication and the instrumentation used for the tests is given.
Tests at different levels of the structure have been carried out in order to determine the dynamic characteristics which define the real behavior of the structure.
Dynamic structural model
A dynamic structural model is defined as a physical system that will duplicate the dynamic characteristics of a prototype to the extent that measurements can be made on the model to predict the behavior of the prototype. The model does not have necessarily to be a scaled duplicate, but it is necessary to make sure that the model characteristics are valid representation of how the full sized prototype will perform.
When the model is constructed of material different from the prototype, their frequency relationship is as stated by the following equation [4]:
(1)
Where:
Lm and Lp represent the model and prototype dimensions; fm and fp represent the model and prototype frequencies;
Cm and Cp represent the longitudinal velocity of sound in the model and in the prototype.
For steel prototype, Cp is a constant, but Cm for the visco elastic material of the model is a function of Section frequency and temperature.
The model constructed for this study does not necessarily duplicate the dynamic characteristics of a real building prototype. However, it is especially made for the purpose of studying the dynamical behavior of framed structure.
The dimensions and size of the elements are chosen and scaled according to a standard structural building, in order to make the model be had more or less as a real structure. In order to arrive at the necessary dimensions of the model, steps have been followed:
DIMENSIONS : in mm 

SCALE OF THE MODEL : 1/9 

758 

12 257 12 257 12 

12 

460 
680 

12 
Z 

PERSPECTIVE VIEW OF THE MODEL 

the first step is to consider a four story full sized steel, building with the following dimensions: Longitudinal dimension: 8m
Transversal dimension: 7m
Total height: 14m with 3.50m floor height.

The second step is to scale the dimensions of the building and the applied loads at 1/15, in order to find the assigned dimensions to the experimental model.
The characteristics of the mild steel used for structural elements (columns and plates) are:

mass density: 7850kg/m3
6
6
229
229
8
8
229
229
8 940
8 940
227
227
8
8
0
X
0
X
200 200
200 200
12
257
12
257
12
12
460
12
750
680

Youngs modulus: E=2.0E11N/m2

Poissons ratio: 0.3

Thickness of plates:

1st
rd
and 2nd
th
floors: 8mm
Elevation B of The Model

3 and 4 floors: 6mm.


Section of columns: solid section 12x12mm
A block of reinforced concrete is built up to support the model frame and make it rigid at base.
All the details are given in figure 1 and table1 and table2:
Table 1: Elements of the model
Elevation A of The Model
Figure 1: Model characteristics Instrumentation
The dynamic response of the model is recorded with an automatic instrumentation system connected to a microcomputer. The block diagram showing the connections between the different instruments necessary for the tests is shown in figure 2 and figure 3.
C O L U M N S AND P L A T E S (M I l d s t e e l) 

TYPE 
Elements 
Dimension (mm) 
Thick ness (mm) 
Quantity 

a 
b 

COLUMNS 
b a 
1072 
200 
12×12 
6 

l=a+b=127 2 

PLATES 
b 
a 
54 6 
456 
6 
2 

a b 
54 6 
456 
8 
2 

R E I F O R C E M E N T (M I l d 
st eel) 

// to X axis 
a b 
630 
150 
Diameter (mm) 
4 

10 

// to Y axis 
a b 
630 
150 
Diameter (mm) 
4 
Synthesizer function generator
Power amplifier
Electrodynami c vibrator
Charge amplifier
Force transducer
Phase meter
Cathode ray oscilloscope
SPECIMEN
Micro computer
Table2: Composition of the concrete used for the base of the model
ELEMENT 
WEIGHT (kg) 
1. coarse aggregate 
114.24 
2. sand 
68.34 
3. cement 
44.88 
4. water 
18.84 
Strength of the concrete after 7 days 
47.5N/mm2 
Scanner (multiplexer)
Charge amplifier
Digital voltmeter
Accelerometer
PRINTER
Figure 2: Block diagram of instrumentation
Figure 3: Instrumentation and experimental model
9 Gradient f
p
f2 f1 p2 p1
…
13 f f L3
5 1 n n1
10 pn pn1
14
6 2 Where:
48EI
(2)
11
15 ZY
7 3
X
12
16
8 4 6
Figure 4: Force input location
Static and dynamic properties of plates and columns samples
Before the model can be used with confidence for the evaluation of its vibration characteristics, the accuracy and validity of the measurements must be established by means of static and dynamic tests on samples of structural elements, such as plates, beams and columns.
For static tests, concentrated loads are applied to the elements in the vertical direction by means of small weights which are required for getting accurate results. The deflections are measured with a mechanical deflection (fig.3). To obtain accurate static data, deflections should be measured several times for the same loading conditions. The static modulus of elasticity of samples is determined. For dynamic tests, the dynamic modulus of elasticity and internal damping are interest and in particular the effects of vibration frequency on these properties are important. Internal damping is of concern because a high value of this quantity may distort the vibration and make the excitation difficult. The three lowest frequencies are determined for the samples. Internal material damping is obtained by measuring the width of the resonant frequency curve or by measuring the log decrement of forced vibration after the harmonic excitation is applied, as recorded on the magnetic oscilloscope.

STATIC TESTS
The characteristics of the steel samples are given in table 3.
According to the consecutive loads applied to the structural samples are the corresponding measured deflections (table 4).
The elastic modulus is calculated using:
n: number of measurements.
Section (mm2)
Length (mm)
2nd Mt area (mm4)
Deflection (m)
Weight (kg)
Columns
L=885
1
7854
Slabs
L=570
0.644
7846
The values of the elastic modulus are shown in table 4.
Table 3: Characteristics of the plates and columns.
LOADING
(Newton) p
C O
L
U
M
N S
S L
A
B
S
Deflection
(mm)
Gradient
Deflection
(mm)
Gradient
10
20
30
40
50
60
70
80
90
100
110
120
130
140
150
160
0.40
0.83
1.23
1.63
2.02
2.40
2.80
3.22
3.67
4.07
4.50
4.90
5.33
5.74
6.15
6.56
0.043
0.040
0.040
0.038
0.038
0.040
0.042
0.045
0.040
0.043
0.040
0.043
0.041
0.041
0.041
0.44
0.92
1.38
1.83
2.29
2.74
3.20
3.65
4.13
4.58
5.02
5.47
5.926.38
6.83
7.26
0.048
0.046
0.045
0.046
0.045
0.046
0.045
0.048
0.045
0.044
0.045
0.045
0.046
0.045
0.043
Average
gradient
0.041
0.045
Static elastic modulus
(N/m2)
2.0383E11
2.0032E11

DYNAMIC TESTS
Columns
The three lowest resonant frequencies and the corresponding damping capacities are determined for the column from a series of dynamic tests. Thus, a longitudinal harmonic excitation is applied to the simply supported column element.
From equation 3 given below for the longitudinal vibration of uniform beams the three resonant frequencies are calculated for the element and compared with the experimental values.
w n E [5] (3)
n L
Where:
wn: circular frequency L: length of the bar
E: elastic modulus (from static tests) : density of the material
The three lowest resonant frequencies are calculated using eq(3) therefore;
1stmode:
a 22.4 for1st mod e a 61.7 for 2nd mod e
a 121.0 for3rd mod e
L: length of the sample
E: elastic modulus (from static tests)
w
1 L
E f 1 E
1 2L
: density of the material
Experimental results
The various model measurements are taken with a constant
2ndmode: (4) force input at a given frequency range, and the resonant
2
w2 L
E f 1 E
2 L
frequency is the frequency corresponding to the maximum receptance of the structure in that range. For a given test, each resonant frequency is checked twice, by changing the
3rdmode :
w 3
3 L
E f 1 E
3 2L
force input value. The resonance test is carried out for sixteen force locations: figure 4:
– eight locations in the X direction of the model;
On the other hand, from a series of dynamic tests on the element subjected to a longitudinal harmonic excitation, the three lowest resonant frequencies and the corresponding specific damping capacities are obtained.
A program is written to read the experimental data and give the results of the tests carried out of the sample.
PLATES
A transversal dynamic force is applied to the simply supported sample of plate. The following equation for the transverse vibration of a uniform beam gives the values of the lowest resonant frequencies:
– eight locations in the Y direction of the model.
For each test (i.e each force location), six resonant frequencies are found within the range 10 110 Hz. Table
4 gives the summary of the experimental resonant frequencies with the corresponding maximum receptances for the sixteen tests.
The results in table 4 show that the values of the 2nd, 4th, 5th, and 6th frequencies obtained are predominantly constant irrespective of the number and direction of test. The first and third resonant frequencies, however, can be seen to differ slightly. The explanation may lie in that the mode
w a
n L2
Where:
EI
rad/sec (5)
A
shape obtained due to the test in a particular direction exhibits a major portion of the displacement in that direction, with possibly slight displacement in the perpendicular direction..
Table 4: Results of experimental tests
TEST NÂ° 
1st resonant frequency 
2nd resonant frequency 
3rd resonant frequency 
4th resonant frequency 
5th resonant frequency 
6th resonant frequency 

Freq. in Hertz 
Max. receptance m/N 
Freq. in Hertz 
Max. receptance m/N 
Freq. in Hertz 
Max.recepta nce m/N 
Freq. in Hertz 
Max. receptance m/N 
Freq. in Hertz 
Max.recepta nce m/N 
Freq. in Hertz 
Max. receptance m/N 

Y DIRECTION 
1 2 3 4 5 6 7 8 
. 11.2 11.2 11.3 11.3 11.2 11.3 11.3 
2.97E4 1.13E4 2.52E5 1.25E4 1.57E4 6.33E5 5.25E5 
18.1 18.0 18.0 18.0 18.0 18.2 . 
5.25E4 3.57E4 9.67E5 2.31E5 . 1.50E5 1.69E5 . 
33.8 33.6 33.6 33.8 33.5 33.9 33.8 33.8 
1.53E5 . 7.62E5 4.44E5 7.07E5 1.53E5 4.72E5 . 
52.1 52.2 51.9 51.6 52.3 . 52.2 52.2 
1.08E4 1.52E6 6.97E5 2.59E5 4.71E6 . 3.83E6 2.16E6 
71.5 71.0 71.5 71.9 72.0 79.1 72.0 
1.56E6 3.16E6 .. 1.94E6 1.43E6 2.59E6 2.57E7 1.39E6 
101.8 102.0 102.0 102.0 101.8 101.8 101.4 101.8 
6.68E6 8.10E6 6.22E6 3.58E6 4.90E6 1.65E5 6.18E6 5.24E6 
X DIRECTION 
9 10 11 12 13 14 15 16 
12.2 12.3 12.0 12.0 12.2 12.1 12.0 12.0 
4.18E4 2.93E4 1.77E4 7.94E5 4.02E4 1.86E4 1.78E4 6.51E5 
18.2 18.2 18.2 18.0 18.3 18.2 18.2 18.3 
2.86E4 3.09E4 2.23E4 1.25E4 2.65E5 1.94E5 2.41E5 8.46E6 
36.0 36.0 35.8 35.7 36.0 36.0 35.7 35.8 
6.79E5 9.41E6 5.15E5 4.05E5 3.94E6 9.73E6 5.01E5 4.38E5 
51.8 52.2 51.8 51.8 52.2 52.2 52.2 52.2 
5.43E5 1.05E5 5.06E5 3.92E5 2.72E6 1.60E6 4.39E6 7.85E7 
71.8 71.7 72.5 71.8 72.0 71.6 72.5 71.8 
2.54E6 3.59E6 6.73E7 4.46E6 2.21E6 3.83E6 4.91E7 9.15E6 
101.5 101.6 101.5 101.6 101.5 101.4 101.4 101.4 
3.78E6 7.39E6 6.65E5 3.38E6 2.41E6 6.16E6 5.80E6 5.23E6 
8.00E5
Receptance (m/N)
6.00E5
4.00E5
2.00E5
0.00E+0
Test nÂ°7
40.00 80.00 120.00
Frequency (Hz)
1.60E4
Receptance (m/N)
1.20E4
8.00E5
4.00E5
0.00E+0
Test nÂ°12
40.00 80.00 120.00
Frequency (Hz)
Experimental results of damping capacity
Observations on the dynamic behaviour of the experimental model show that the specific damping capacity is affected by the level of excitation and the resonant frequency used to calculate that damping.
Test number 
First res. freq. 11.2 Hz 
Second res. freq. 18.2 Hz 
Third res. freq. 33.8Hz 
Fourth res. freq. 52.2 Hz 
Fifth res. freq. 71.5 Hz 
Sixth res. freq. 101.5 Hz 

Y D I R E C T I O N X DIR E CT IO N 
1 
0.035 
0.037 
0.024 
0.112 
0.024 

2 
0.112 
0.070 
0.070 
0.060 
0.105 
0.062 

3 
0.112 
0.071 
0.037 
0.073 
0.062 

4 
0.112 
0.069 
0.037 
0.049 
0.110 
0.031 

5 
0.111 
0.037 
0.012 
0.105 
0.025 

6 
0.056 
0.069 
0.037 
0.111 
0.019 

7 
0.111 
0.051 
0.037 
0.024 
0.112 
0.025 

8 
0.111 
0.056 
0.036 
0.110 
0.025 

12.2 
18.2 Hz 
36.0 Hz 
52.2 
71.5 
101.5 

Hz 
Hz 
Hz 
Hz 

9 
0.052 
0.069 
0.024 
0.070 
0.019 

10 
0.051 
0.069 
0.024 
0.066 
0.012 

11 
0.105 
0.069 
0.049 
0.104 
0.019 

12 
0.105 
0.035 
0.024 
0.070 
0.037 

13 
0.051 
0.034 
0.012 
0.088 
0.019 

14 
0.105 
0.073 
0.024 
0.105 
0.025 

15 
0.105 
0.035 
0.024 
0.052 
0.025 

16 
0.105 
0.035 
0.024 
0.088 
0.012 
Table 5: Values of damping capacity from different tests
Figure 5: Resonant frequencies
On the other hand, in some tests, the resonant frequencies do not appear at all, as indicated by the broken lines in table 4. This may be due to the non linear behavior of the structure in certain modes of vibration.
Figures 5 show roughly the set of the resonant frequency curves found from four different tests in the range 10 110 Hz.
The tests are carried out again for sixteen locations figures 1 et 2 in order to determine the mode shapes corresponding to the experimental resonant frequencies previously found. For each test location and for each resonant frequency, the tests are carried out with a constant force. Some tests have revealed that in some locations of the vibrator, it is possible to excite clearly some of the desired modes. This may be partly due to the fact that the vibrator is located too close to one of the nodal points of the desired mode and partly due to interference from other modes (Table 6 and figure 6).
MODE SHAPE 1
MODE SHAPE 2
Experimental disp.
Frame
MODE SHAPE 7
MODE SHAPE 9
Figure 6: Experimental mode shapes
The main problems in gaining sufficient information from forced vibration tests are:

to locate the vibration exciter far enough away from nodal points of the desired modes;

to locate the vibration exciter such that interference between the response of modes that have frequencies close together is eliminated.
In order to locate approximately the mode that could be excited at a given frequency and force input, the accelerometer is placed consecutively at 30 different nodes of the model for each test as shown in figure 1. The duration of placing the accelerometer at each mode is about 15 seconds which is thought to be sufficient to record the response at each node.
For each node, the phase angle is recorded at the same time with the amplitude of vibration in order to determine at which frequencies the translational modes are excited and at which frequencies the tensional modes are excited.
Table 5 shows that the damping is relatively high for the first and fifth resonant frequencies; the damping values vary between 0.052 and 0.112. Then they start to decrease for the second and third resonant frequencies where they vary between0.035 and 0.070. Finally, the fourth and sixth resonant frequencies give the lowest damping values, which are acceptable for defining the dynamic behaviour of the model in terms of damping capacity. These values vary between 0.012 and 0.062 depending on the level of excitation.
Mathematical model
The steel model is made of two different elements which are the columns and plates.
Among the three commonly used element geometries for the thick plate (figure 7), the 17 node element is chosen. Four different mathematical models are considered for analysis of the dynamic behavior of the structure with different finite element discretization.
Frequencies and mode shapes are determined for the following mathematical models:

Model with 118 nodes, 8 plate elements and 24 beam elements

Model with 190 nodes, 16 plate elements and 24 beam elements

Model with 214 nodes, 8 plate elements and 120 beam elements

Model with 286 nodes, 16 plate elements and 120 beam elements
2
10 3
14 11
3
9
1
5
13 12
4 18 3
2
10 3
14
9
1
17 5
13 12
11 4 18
Table 6: Results obtained for the model with 118 nodes.
7 15
2
8 16
9
17
CASE
MODE NUMBER
CIRCULAR FREQUENCY
(rad/sec)
FREQUENCY (Hz)
PERIOD
(sec)
TOLERANCE
RIGID BASE
1
115.60
18.39
0.0544
0.3406E15
2
115.60
18.39
0.0544
0.3405E15
3
138.20
22.00
0.0454
0.3331E15
4
331.60
52.78
0.0190
0.2210E09
5
332.00
52.83
0.0189
0.1453E14
6
396.80
63.15
0.0158
0.4410E12
7
505.10
80.38
0.0124
0.1729E07
8
506.70
80.64
0.0124
0.2817E12
9
604.90
96.27
0.0104
0.1625E09
10
613.60
97.66
0.0102
0.3007E05
11
619.40
98.58
0.0101
0.4389E11
12
670.30
106.70
0.0094
0.3014E08
13
675.60
107.50
0.0093
0.2833E08 14
677.80
107.90
0.0093
0.6798E08
15
682.30
108.60
0.0092
0.1055E05
16
738.50
117.50
0.0085
0.2135E15
PINNED BASE
1
74.76
11.90
0/0840
0.00
2
74.76
11.90
0.0840
0.1627E15
3
89.34
14.22
0.0703
0.2279E15
4
277.20
44.12
0.0227
0.0
5
277.40
44.15
0.0226
0.1891E15
6
331.70
52.80
0.0189
0.1322E15
7
475.00
75.61
0.0132
0.3869E15
8
476.30
75.80
0.0132
0.2566E15
9
568.90
90.54
0.0111
0.1349E15
10
606.00
96.44
0.0104
0.4029E06
11
611.00
97.25
0.0103
0.3897E15
12
670.20
106.70
0.0094
0.1613E09
13
675.30
107.50
0.0093
0.2361E07
14
677.30
107.80
00093
0.1458E08
15
681.60
108.50
0.0092
0.2812E04
16
728.70
116.00
0.0086
0.4385E15
7 115 8
10 3
14 11
3
5
13 12
4 18
19 20
7 15 8
Figure 7: Commonly used element geometries (18 Node element, 17 Node element and 20 Node element)
For each model, the structure is assumed with:

rigid joints at the base

Pinned joints at the base.

The highest frequency found for each model is the frequency which corresponds to the fourth tensional mode. All the frequencies beyond that mode are not taken into account in this analysis. Table 6 gives the summary of the frequency results of the one mathematical model for the selected mode shapes.
Among the four mathematical models, the one whose values most converge with the experimental results is chosen for comparison (model having 118 nodes).
From figure 8, it can be seen that most of the deflected shapes of the experimental selected mode seem to be convergent with the deflected shapes of the corresponding analytical modes.
MODE SHAPE 1
MODE SHAPE 2
Experimental disp.
Analytical disp.
Frame
MODE SHAPE 7
MODE SHAPE 9
Figure 7: Experimental and analytical mode shapes [6]
CONCLUSION
The major objective of this study has been to evaluate the dynamic characteristics of the experimental model, such as frequencies and mode shapes.
From an extensive series of resonances tests on the model, it has been found that an extremely accurate speed control of the vibration exciter is needed to fully define the response of the structure. Thus, observation of the dynamic behavior of the model during the tests has shown that the resonant frequencies and mode shapes may be affected by the location of the excitation.
The final experimental frequencies of the model are: 11.2Hz, 12.2 Hz, 18.2 Hz, 33.8 Hz, 36.0 Hz, 52.2 Hz,
71.2 Hz, and 101.5 Hz.
The experimental results have also shown that the specific damping capacity is affected by the level and direction of the excitation. The damping capacity is also frequency dependant, i.e the higher the frequency, the lower the damping value, except for the frequency 71.5 Hz where the damping is slightly higher than expected.
The highest values of damping have varied between 7% and 11.2%.
The lowest values have varied between 5% and 1.2%.
On the other hand, the analytical study of the model using the iteration method which has not taken into account the torsional modes, has shown that the resonant frequencies calculated for the translational modes converge well with the corresponding frequencies calculated for the finite element model.
The mathematical analysis has given more detailed results of the frequencies and mode shapes, i.e translational modes, torsional modes and slab vibration modes. However the frequency results are seen to differ slightly from one mathematical model to another, depending on the number of beam and plate elements.
Furthermore, for the three lowest modes of vibration, the frequencies of the pinned frame at base are found to be almost 35% lower than the frequencies of the rigid frame at base. The difference in percentage decreases from mode to another until the values become identical in the fourth modes.
The theoretical and experimental results are compared together. From these results it can be seen that some of the measured frequencies such as 11.2 Hz, 12.2 Hz, 52.2 Hz,

Hz and 101.5 Hz converge much better with the frequencies calculated for the model having 118 nodes and pinned base. The structure, therefore, behaves as pinned at the base for these frequencies.
Further research
Further extension of this investigation may include an experimental and analytical dynamic study of the model by:

using vertical bracing system between floors;

using horizontal bracing at base level between columns to make the structure behave rigidly at the base;

using more than one vibrator at the same time at different locations, to excite the model and therefore determine possibly the missing modes and frequencies found by analytical work;

taking into account the vibration of plates.

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G.B.WARBURTON, Dynamical behavior of structures,
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C.F.BEARDS, Structural vibration analysis: modeling,analysis and damping of vibrating structures, Ellis Horwood, J.Wiley and Sons.

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RAY R., GRAIG J. Structural dynamics: An introduction to computer methods

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