Recently a feasibility study on the application of aerospace ARALL (Aramid Aluminum Laminates) in the A320 fuselage was performed. This study, limited to fuselage section 13/14, indicates that a weight reduction of 26 percent can be obtained by using GLARE for the fuselage skin and stringers. No reinforcements are needed at the locations of the stringers. Whether reinforcements at the locations of the joints are necesary in the fuselage design in GLARE is investigated by performing static and fatigue tests on two highly loaded joints. The material properties of the skin (GLARE-3 consisting of three layers of 0.2 mm aluminum 2024-T3 and two layers of 0.25 mm crossply glass prepeg) are discussed and compared with those of aluminum 2024-T3. The decisive loading data for the joints is given, and the type of rivets to be applied to the joints is chosen. The strength of the chosen rivets in the GLARE-3 skin material is determined. The choice of the splice plate material and the geometry of the joints are discussed. Conclusions about the joints of the A320 fuselage design in GLARE are drawn.
Design and Testing of a Circumferential and Longitudinal Joint of the A320 Fuselage Section 13/14 in Glare
1990
64 pages
Report
No indication
English
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