Laminated metal-polymeric materials in structural elements of aircraft

Abstract

Design, manufacture, and test results are presented for laminated metal-polymeric hybrid fragments of a wing panel made of high-strength aluminum-lithium alloy V-1469T1 and of single-directed laminated aluminum fiberglass SIAL-1-1R. It is shown that the principle “material–technology–structure” can be implemented, and we demonstrate it by example of designing the fragment of a hybrid wing panel beginning from choosing the optimal structure material for the stringer and the structure of hybrid skin and finishing by testing large-sized structure-like samples. We show that the results of strength calculations for fragments of the hybrid wing panel demonstrate good convergence according to static and repeated static tests of panel fragment. Calculations are performed according to different methods, including the finite element method. We show that the hybrid structures are better than the traditional structures made of aluminum alloys according to weight efficiency, which can run up to 10%, and according to bearing capacity, which can run up to 20%.