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Proceedings Paper

Identifying delamination in an experimental composite UAV wing subject to ambient gust loading
Author(s): Jonathan M. Nichols; Stephen T. Trickey; Mark Seaver; Daniel L. Pecora
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Paper Abstract

Vibration-based structural health monitoring has largely considered applied excitations as the primary means of inducing structural vibration. Here we consider how ambient vibrations might be used to assess the level of damage in a composite UAV wing. The wing consists of a foam core and a carbon fiber skin. We subject the wing to various amounts of impact damage in order to cause internal delaminations. The wing is then excited using a gust loading waveform in an effort to simulate the forcing the wing is expected to see in flight. We then use a probabilistic description of the structure's dynamics to assess the level of damage-induced nonlinearity in the wing. The approach is capable of making the diagnosis in the absence of a representative baseline data set from the "healthy" wing.

Paper Details

Date Published: 15 March 2006
PDF: 7 pages
Proc. SPIE 6177, Health Monitoring and Smart Nondestructive Evaluation of Structural and Biological Systems V, 617704 (15 March 2006); doi: 10.1117/12.659241
Show Author Affiliations
Jonathan M. Nichols, Naval Research Lab. (United States)
Stephen T. Trickey, Naval Research Lab. (United States)
Mark Seaver, Naval Research Lab. (United States)
Daniel L. Pecora, Naval Research Lab. (United States)


Published in SPIE Proceedings Vol. 6177:
Health Monitoring and Smart Nondestructive Evaluation of Structural and Biological Systems V
Tribikram Kundu, Editor(s)

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