International Journal of Aerospace Engineering / 2018 / Article / Tab 2

Research Article

Structural Damage Detection Using Nonlinear Vibrations

Table 2

First 20 eigenfrequencies for the undamaged panel and for the three damages with their % variations.

Mode (Hz)D2, (Hz)D2, %D3, (Hz)D3, %D5, (Hz)D5, %

17.957.79−2.017.950.007.83−1.51
211.3811.37−0.0911.380.0011.380.00
323.6723.44−0.9723.670.0023.51−0.68
427.9026.67−4.4127.900.0027.60−1.08
547.7243.15−9.5847.720.0046.56−2.43
649.8248.93−1.7949.820.0049.11−1.43
772.6771.01−2.2872.58−0.1271.47−1.65
883.4373.63−11.7583.430.0080.68−3.30
987.7085.73−2.2587.57−0.1586.44−1.44
93.42
1099.2299.410.1998.89−0.3398.20−1.03
11101.1199.88−1.22101.10−0.0199.76−1.34
12101.22109.688.36100.97−0.25100.20−1.01
13114.46114.630.15114.45−0.01112.51−1.70
14117.42117.480.05115.53−1.61116.92−0.43
15118.05117.86−0.16117.70−0.30117.86−0.16
16121.78121.75−0.02121.77−0.01121.75−0.02
17121.82126.573.90121.65−0.14119.86−1.61
18128.90131.101.71128.88−0.02128.15−0.58
19137.98137.16−0.59137.68−0.22137.36−0.45
20139.43139.27−0.11139.34−0.06139.33−0.07

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