Mass evaluation for load carrying structures of aircraft wing

Based on the load carrying factor, a new dimensionless criterion of load carrying factor coefficient with the theory of variable full stress and finite element method (FEM) is proposed to support structrual mass evalution with higher accuracy at the initial stages of airframe design. The approach's application strategies in modern aircraft structures with stringer skin are presented. Five delta wings with same configurations and different load carrying structures are evaluated their strucural mass by the load carrying factor coefficient. The results showed that, at the initial stages of airframe design, different load carrying structures could be evaluated, and their absolute mass could be estimated more precisely utilizing the approach presented.