An experimental and analytical investigation was performed to characterize damage initiation and progression along the frame/skin interface of the aft crown panel fuselage section in a commercial aircraft. The effect of manufacturing procedures on damage initiation and failure processes was addressed by evaluating five different frame/skin assemblies. Crack initiation and progression as a function of applied load and the local failure events were monitored and recorded using a high magnification closed circuit television system. For selected specimens, acoustic emission was monitored, X-radiography was performed, and fracture surface morphologies were examined via the scanning electron microscope. In addition, a pilot program on the fatigue behavior of the frame/skin test elements has been conducted. The Mode I and Mode II fracture toughness of the skin and braided materials were also determined using the double cantilever beam and the end notch flexure specimen configurations. A finite element code (VISOCRACK) was employed for simulating the types of failure observed experimentally and to predict failure initiation.
Evaluation of frame/skin bond strength and durability for advanced composite fuselage crown structures
Bewertung der Rahmen/Haut-Verbindungsfestigkeit und Dauerhaftigkeit für Endstrukturen von Flugzeugrümpfen aus hochentwickelten Verbundwerkstoffen
1994
9 Seiten, 7 Bilder, 1 Tabelle
Aufsatz (Konferenz)
Englisch
Advanced Composite Fuselage Technology
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