Vibrational analysis of an aircraft winglet by use of pulsed-laser holographic interferometry

Michele Arturo Caponero; Alberto De Angelis

doi:10.1117/12.140443

2 March 1993 Vibrational analysis of an aircraft winglet by use of pulsed-laser holographic interferometry

Michele Arturo Caponero, Alberto De Angelis

Proceedings Volume 1732, Holographics International '92; (1993) https://doi.org/10.1117/12.140443
Event: Holographics International '92, 1992, London, United Kingdom

Abstract

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.

Citation Download Citation

Michele Arturo Caponero and Alberto De Angelis "Vibrational analysis of an aircraft winglet by use of pulsed-laser holographic interferometry", Proc. SPIE 1732, Holographics International '92, (2 March 1993); https://doi.org/10.1117/12.140443

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