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Detection and Characterization of Imperfections in Composite Pressure VesselsThe thermographic evaluation of composite structures for delaminations, disbonds, inclusions, porosity and microcracking has proven to be a valuable asset in the field of nondestructive testing. Coupling large area coverage, variable sensitivity and minimal surface contact with a photographic type image representation of structural anomalies; thermography has become a primary inspection method for composite structures. Thermography works well for locating both surface and subsurface defects in most composite systems ranging in thickness of up to 0.25 inch (0.64 cm) or more. The thermographic method for inspection of composite structures typically involves applying an external source of heat to the structure and then recording the changes in the surface heat profile manifested by embedded defects or by material property variations. If these temperature variations are large enough and an infrared camera with sufficient sensitivity is used, then the material or structural abnormality can be detected and referred back to its source. Interpreting the information given in a thermogram, can be a difficult task under ideal circumstances and extremely challenging in a real world setting. Variables including depth, thermal conductivity, orientation and size of the abnormality can all have a great influence on how its heat pattern will be seen by the imager. The work discussed in this paper illustrates how the microstructure of several commonly found defects in composite structures relate to their thermographic image counterpart. Two test cases are studied herein, including a large graphite/epoxy RP-1 fuel tank and a graphite composite cryogenic fuel feedline. The structures used in this study were designed to serve as manufacturing proof of concept specimens and to undergo hydroburst testing to verify manufacturing practices and structural design. Prior to hydrostatic testing the structures underwent 100% thermographic evaluation to ensure that no manufacturing or handling damage was present. Due to a large inclusion found in the feedline, it was pulled from service and dissected without performing the hydroproof The thermographic indications found in the RP-1 tank were below critical limits so it underwent a complete hydroproof loading series and finally a hydroburst. Following the hydroburst samples were cut from the tank in regions where thermography had located damage before the test. These regions were thermographically and then were cross-sectioned and photomicrographed.
Document ID
20010048745
Acquisition Source
Marshall Space Flight Center
Document Type
Abstract
Authors
Walker, James L.
(NASA Marshall Space Flight Center Huntsville, AL United States)
Russell, Samuel S.
(NASA Marshall Space Flight Center Huntsville, AL United States)
Munafo, Paul M.
Date Acquired
August 20, 2013
Publication Date
January 1, 2001
Subject Category
Composite Materials
Meeting Information
Meeting: Composite Materials: Testing, Design, and Acceptance Criteria: ASTM STP 1416
Location: Phoenix, AZ
Country: United States
Start Date: March 26, 2001
End Date: March 27, 2001
Sponsors: American Society for Testing and Materials
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.

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