STRESS ANALYSIS AND VERIFICATION TEST OF COMPOSITE FUSELAGE PANEL MECHANICALLY FASTENING

Abstract

Abstract: A static test was designed to verify the composite fuselage panels mechanically-fastening design and analysis method. Stress analysis was carried out by experience formula and finite element modeling respectively. As shown by the test results, the mechanically fastening design can sustain the limited load and ultimate load. The theoretical strain complies with the test strain. Load ratio carried by the fasteners calculated by test data is in line with the experience data. The damage load level in the test was higher than the predicted level given by theoretical analysis, demonstrating that the selected method is rational and conservative.

Key words: carbon fiber reinforced plastic (CFRP), fuselage panel, mechanically fastening, stress analysis, verification test

CLC Number:

TB332

ZHANG Xu, WANG Hou-bing, YU Zhen-bo, HU Hai-wei. STRESS ANALYSIS AND VERIFICATION TEST OF COMPOSITE FUSELAGE PANEL MECHANICALLY FASTENING[J]. Fiber Reinforced Plastics/Composites, 2019, 0(7): 85-91.

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