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Distributed Sensing of Carbon-Epoxy Composites and Filament Wound Pressure Vessels Using Fiber-Bragg GratingsMultiple Fiber Bragg-gratings are embedded in carbon-epoxy laminates as well as in composite wound pressure vessel. Structural properties of such composites are investigated. The measurements include stress-strain relation in laminates and Poisson's ratio in several specimens with varying orientation of the optical fiber Bragg-sensor with respect to the carbon fiber in an epoxy matrix. Additionally, fiber Bragg gratings are bonded on the surface of these laminates and cylinders fabricated out of carbon-epoxy composites and multiple points are monitored and compared for strain measurements at several locations.
Document ID
20030060669
Acquisition Source
Marshall Space Flight Center
Document Type
Conference Paper
Authors
Grant, J. (NASA Marshall Space Flight Center Huntsville, AL, United States)
Kaul, R. (NASA Marshall Space Flight Center Huntsville, AL, United States)
Taylor, S. (NASA Marshall Space Flight Center Huntsville, AL, United States)
Myer, G. (NASA Marshall Space Flight Center Huntsville, AL, United States)
Jackson, K. (NASA Marshall Space Flight Center Huntsville, AL, United States)
Osei, A. (Oakwood Coll. Huntsville, AL, United States)
Sharma, A. (Alabama Agricultural and Mechanical Univ. Normal, AL, United States)
Date Acquired
August 21, 2013
Publication Date
January 1, 2003
Subject Category
Instrumentation And Photography
Meeting Information
Meeting: SPIE''s Smart Structures and Materials Conference
Location: San Diego, CA
Country: United States
Start Date: March 2, 2003
End Date: March 6, 2003
Sponsors: International Society for Optical Engineering
Distribution Limits
Public
Copyright
Other

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