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The methods discussed here are mainly elaborated by the evaluation of modal data due to the great potential of their application.
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Model validation based on experimental modal data is often not possible due to the high modal density that aircraft fuselage structures exhibit in this frequency range.
The basic concept of finite element model updating is that the measured and analytical modal data are unlikely to be equal due to the presence of noise in the measurements and model inadequacies (Lee and Eun 2009).
The method provides significant improvement in damage localization and ability to tolerate measurement noise on natural frequency shifts due to damage over similar localization methods that use only open-loop modal data.
Otherwise, modal data will be complex quantities.
The extracted modal data from experimental modal testing are usually complex values.
In general, modal data are obtained through either experimental or operational modal testing (Ewins 2000; He and Fu 2001).
On the other hand, measured modal data from experimental models are usually complex data.
Thus, initial properties of the laboratory frame are calculated using the real measured modal data.
Modal data is psychoacoustically meaningful and can be easily edited to extract, mix, or modify modes.
Tables 4 and 5 indicate the initial modal data of undamaged frame.
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