Numerical analysis with experimental data of the joint of fuselage with main landing gear and wing‐strut, of a two‐seat aircraft built with composites

An analysis of the strut‐to‐fuselage and main‐landing‐gear‐to‐fuselage joint is realized in order to evaluate the zones with a high probability of failure. The whole section is analyzed using the finite element method in order to estimate static resistance behavior, therefore it becomes necessary to create a numerical model of the section, to measure the mechanical properties of the C‐Ep composite material, and to calculate the loads applied onto the section. The section is digitized with photogrammetry. Mechanical characterization is achieved with instrumented standardized tensile tests. Results of the analysis show that the zones with higher probability of failure are found around the wing strut and the fuselage joint, with a safety factor higher than necessary even for the most critical condition, and lower in comparison with the average safety factor used on aircrafts built mostly with metals. POLYM. COMPOS., 36:1072–1083, 2015. © 2015 Society of Plastics Engineers