Static Aeroelastic Optimization Design and Verification of Composite Wing with Large Sweep Angle

Abstract

This paper analyses the reasons for the serious drop in lift after the deformation of the large sweep angle aircraft. It is determined that the lift loss is mainly related to the sweep angle and the bending deformation amount of the wing, and also determined that the inevitability of the lift loss according to the traditional composite layering method. Drawn on the successful experience of aviation aircraft design, the optimization method of stiffness tailoring for aircraft wing and the rounding treatment method for optimized composite layer are proposed. With a composite aircraft as the object, the optimized design, processing and ground test verification of the wing are completed. Studies have shown that, after the stiffness tailoring optimization design, the maximum bending deformation is almost constant (2% increase), and the deformation difference between the front and the rear edge is reduced by 80%. After optimization, it not only satisfies the design requirements of pure bending deformation, reduces the lift loss from 32% to about 4%, but also reduces the structural weight by 12%. The research results have a certain guiding significance for the subsequent aircraft designing.