The wing bears most of the aerodynamic load in the composite solar UAV (Unmanned aerial vehicle) structure and provides the main lift for the aircraft. In this paper

the parameterized FEA (Finite element analysis) model and GA (Genetic algorithm) are used to optimize the size of solar composite wing structure

Abaqusis integrated on the Isight platform to construct an optimization environment

and the model for structural optimization is established

the optimization model minimizes the weight of the composite wing underthe multi-criteria constraints

and takes the size and position parameters of the J-shaped wing beam as the design variables

and considering the constraints such as stress

displacement and Cai Wu coefficient

the mass of the optimized wing decreased by 11.83% comparing with the initial design. The results show that by using the current optimization method can significantly reduce the structural mass of the wing

and can effectively and accurately obtain the optimal structural layout of the solar UAV wing.