To monitor in-flight damage and reduce life-cycle costs associated with CFRP composite aircraft, an autonomous built-in structural health monitoring (SHM) system is preferred over conventional maintenance routines and schedules. This thesis investigates the use of ultrasonic guided waves and piezoelectric transducers for the identification and localization of damage/defects occurring within critical components of CFRP composite aircraft wings, mainly the wing skin-to-spar joints.
Structural Diagnostics of CFRP Composite Aircraft Components by Utrasonic Guided Waves and Built-In Piezoelectric Transducers
2006
242 pages
Report
No indication
English
Utrasonic signal enhancement by resonator techniques
TIBKAT | 1973
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