Thermal Inspection of a Composite Fuselage Section Using a Fixed Eigenvector Principal Component Analysis Method

A composite fuselage aircraft forward section was inspected with flash thermography. The fuselage section is 24 feet long and approximately 8 feet in diameter. The structure is primarily configured with a composite sandwich structure of carbon fiber face sheets with a Nomex(Trademark) honeycomb core...

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Bibliographische Detailangaben

Hauptverfasser:	Zalameda, Joseph N., Bolduc, Sean, Harman, Rebecca
Format:	Tagungsbericht
Sprache:	eng
Schlagworte:	Composite Materials Instrumentation And Photography
Online-Zugang:	Volltext bestellen
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