Results of test programs conducted to obtain structural performance information essential to the design of long-life composite aircraft structure are presented. Static, fatigue, and fracture tests were conducted on T300/5208 and T300/5209 graphite/epoxy laminate specimens which were representative of full-scale strength-designed laminates. Results showed that static tensile and compressive strength are significantly degraded by discontinuities and impact damage. Laminates with representative fiber damage are relatively insensitive to cyclic tensile loadings, however, cyclic compressive loading results in finite fatigue lives. Impact damage which caused barely visible fiber failure was found to reduce fatigue performance below that defined for an open hole. The graphite/epoxy laminates tested were found to be fracture sensitive. Laminate stacking sequence was found to have a significant influence on fracture strength and failure mode. (Kursetz)
Designing for integrity in long-life composite aircraft structures
Konstruktion von Flugzeugbauteilen aus Verbundwerkstoffen fuer einen zuverlaessigen Langzeitbetrieb
FATIGUE OF FILAMENTARY COMPOSITE MAT. ASTM SYMP. ; 636 ; 228-247
1976
20 Seiten, 14 Bilder, 6 Quellen
Aufsatz (Konferenz)
Englisch
VERBUNDWERKSTOFF , FASERVERSTAERKUNG , FLUGZEUGBAU , BAUTEIL , FLUGZEUGZELLE , FLUGZEUGSTEUERWERK , FLUGZEUGRUMPF , TRAGWERK , CARBONFASERVERSTAERKTER KUNSTSTOFF , STATISCHE FESTIGKEIT , STOSSLAST , DYNAMISCHE BELASTUNG , ERMUEDUNGSFESTIGKEIT , ERMUEDUNGSBRUCH , STOSSFESTIGKEIT , ZUGFESTIGKEIT , LANGZEITVERHALTEN , ZEITSTANDVERSUCH , VERSUCHSMETHODE , MESSWERTVERARBEITUNG
Monitoring Integrity of Composite Aircraft Components
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Monitoring Integrity Of Composite Aircraft Components
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