Proceedings PaperVibrational analysis of an aircraft winglet by use of pulsed-laser holographic interferometry
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The work done in order to perform a vibrational analysis of an aircraft winglet is presented. The analysis was intended to acquire general purpose structural information, and to define the best location for accelerometers to be used in subsequent vibration fatigue tests. The winglet was mounted on a platform driven by an electromagnetic shaker and thus excited in order to simulate on-flight stressing; induced deformations were detected by pulsed holographic interferometry. Different stress conditions were tested while the shaker was vibrating at frequencies in the 30 - 1500 Hz range and with accelerations in the 0.5 - 2.0 g range.