04.2 - Aerostructures Design, Structural Dynamics, Aeroelasticity
A-BASIS AND B-BASIS BUCKLING ALLOWABLES FOR AN AIRCRAFT COMPOSITE WING
R.A.S. Cardoso¹, M.S. Reis¹, L.P.S. Ferreira, FEMTO-ST, France; M.P. Alves¹, S.K. Ha, Hanyang University, South Korea; C.A. Cimini Jr.¹; ¹Federal University of Minas Gerais, Brazil
This paper aims to establish an approach to determine A-Basis and B-Basis buckling allowables for an aircraft composites wing. A CNN (Convolutional Neural Network) is trained using data from Monte Carlo simulations of a Finite Element model. A surrogate statistical model is then generated to define the A-Basis and B-Basis allowable bending/torsion buckling strength of the composites wing.