Abstract: Based on engineering mathematical solution and finite element analysis, the aeroelastic optimization technology is developed with consideration of both the wall stability constraints and the aeroelastic constraints. The aeroelastic comprehensive optimization design is carried out for a large aspect ratio composite wing. It is shown that if the stability constraints are not considered in the aeroelastic optimization of the wing, although a smaller structural weight can be achieved, the stability requirements are often not satisfied. Compared with the aeroelastic comprehensive optimization design method with consideration of the structural instability characteristics by the finite element, the optimization with the partition instability analysis of the wing structure by engineering mathematical solutions can control the variables more accurately, further reduce the structural weight and improve the structural instability factor while satisfying various performance requirements, especially, the stability constraints.