Impact induced damage is ofter of main concern for aeronautic structures. The aircraft can undergo low velocity impacts during the assembly stage and during its operative life. Delamination and other damage mechanisms, such as matrix cracks, fibre-matrix debonding and fiber breakages can be the consequence of impact events with foreign objects under in service conditions and maintenance operations. Dam-ages induced by low velocity impacts can be hardly detected by visual inspections because they often are confined deeply in the laminate thickness. Hence the use of expensive and time consuming non-destructive techniques such as ultrasonic tests, can be required. In order to prevent catastrophic events, as a consequence of impacts, designers usually increase the structural safety margins thereby increasing the weight of the aircraft. In the frame of the present work, in order to quantify the influence of impact events on the load carrying capability of complex composite structures, specific advanced numerical techniques are used to take into account the skin-stringer debonding phenomena arising in stiffened composite panels as a consequence of low velocity impact events.
A NUMERICAL STUDY ON LOW VELOCITY IMPACT INDUCED DAMAGE IN STIFFENED COMPOSITE PANELS
RICCIO, Aniello;
2013
Abstract
Impact induced damage is ofter of main concern for aeronautic structures. The aircraft can undergo low velocity impacts during the assembly stage and during its operative life. Delamination and other damage mechanisms, such as matrix cracks, fibre-matrix debonding and fiber breakages can be the consequence of impact events with foreign objects under in service conditions and maintenance operations. Dam-ages induced by low velocity impacts can be hardly detected by visual inspections because they often are confined deeply in the laminate thickness. Hence the use of expensive and time consuming non-destructive techniques such as ultrasonic tests, can be required. In order to prevent catastrophic events, as a consequence of impacts, designers usually increase the structural safety margins thereby increasing the weight of the aircraft. In the frame of the present work, in order to quantify the influence of impact events on the load carrying capability of complex composite structures, specific advanced numerical techniques are used to take into account the skin-stringer debonding phenomena arising in stiffened composite panels as a consequence of low velocity impact events.I documenti in IRIS sono protetti da copyright e tutti i diritti sono riservati, salvo diversa indicazione.
