Abstract:Based on flexibility aeroelastic analysis method, the structural optimization method of electric aircraft composite wing considering aeroelastic load was studied in this paper. The aerodynamic load of the wing was calculated by the doublet lattice method considering the airfoil camber, and compared with the CFD results to verify its accuracy. With the ply orientation angle and percentage as the variables, the minimum structural weight as the objective, the strength and the composite material processability as constraints, the genetic algorithm was used to optimize the wing structure. In the strength calculation, the aeroelastic load correction caused by the deformation of the wing was considered. Finally, the accuracy of the simulation results was verified by a static experiment. The research shown that the wing root bending moment, shear force and torque of the straight wing have increased after considering the aeroelastic load, and an appropriate wing structure stiffness can be designed to meet the requirements of strength design and achieve weight reduction, based on this optimization method.