Skew Bending of Aircraft Fuselage Panels with “L” and “C” Stringers Mounted by Hybrid Joint / Ukośne Zginanie Poszycia Samolotu Z U Sztywnieniami Typu “L” I “C”, Mocowanymi Za Pomocą Złącza Hybrydowego

Abstract

Skew bendIng of aIrcraft fuSelage panelS wIth "l" and "c" StrIngerS mounted by hybrId joInt Ukośne zginanie poszycia samolotU z Usztywnieniami typU "l" i "c", mocowanymi za pomocą złącza hybrydowegoA section of fuselage skin with dimension 30 x 200 mm was subjected to numerical study and loaded by skew bending (Fig. 3). The thickness of the skin was 0,6 mm, the length of a leg of an angle "L" profile stringer was 12 mm with 1mm thickness. The angle of inclination α of the load plane to the skin plane varies in the range from 10° to 90° with 10° increment. The elastic -plastic material model of D16T aluminum alloy was used in simulations of the fuselage skin as well as for "L" and "C" profile stringers. In the material model description damage of aluminum alloy was taken into account. An adhesive layer with thickness of 0,1mm was modeled using cohesive elements with the failure mode depending on the shear strength and the tensile strength.The paper presents a comparative analysis of the considered structural elements with application of the unsymmetrical "L" profile or the symmetrical "C" profile with the same cross section area.All numerical studies were performed in Abaqus program. Finally, one can conclude that the stiffness of the structural element with application of the symmetrical "C" profile stringer is stronger, whereas the mechanical response of both versions of the hybrid joint significantly depends on the angle of load inclination α.