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Proceedings Paper

Strain monitoring of a composite wing
Author(s): Joseph Strathman; Steve E. Watkins; Amardeep Kaur; David C. Macke
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Paper Abstract

An instrumented composite wing is described. The wing is designed to meet the load and ruggedness requirements for a fixed-wing unmanned aerial vehicle (UAV) in search-and-rescue applications. The UAV supports educational systems development and has a 2.1-m wingspan. The wing structure consists of a foam core covered by a carbon-fiber, laminate composite shell. To quantify the wing characteristics, a fiber-optic strain sensor was surface mounted to measure distributed strain. This sensor is based on Rayleigh scattering from local index variations and it is capable of high spatial resolution. The use of the Rayleigh-scattering fiber-optic sensors for distributed measurements is discussed.

Paper Details

Date Published: 20 April 2016
PDF: 9 pages
Proc. SPIE 9803, Sensors and Smart Structures Technologies for Civil, Mechanical, and Aerospace Systems 2016, 980346 (20 April 2016); doi: 10.1117/12.2219363
Show Author Affiliations
Joseph Strathman, Missouri Univ. of Science and Technology (United States)
Steve E. Watkins, Missouri Univ. of Science and Technology (United States)
Amardeep Kaur, Missouri Univ. of Science and Technology (United States)
David C. Macke, Missouri Univ. of Science and Technology (United States)


Published in SPIE Proceedings Vol. 9803:
Sensors and Smart Structures Technologies for Civil, Mechanical, and Aerospace Systems 2016
Jerome P. Lynch, Editor(s)

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