Based on the large-scale parallelized structured grid Reynolds-Averaged Navier-Stokes (RANS)solver PMB3D and the fluid-solid coupling FSC3D, a simulation technology for aircraft aeroelasticity is established. Derivation and construction of the aero-structural coupled adjoint system are carried out by using the parallel adjoint equation solver PADJ3D. The decoupling of the coupled adjoint system is realized by delaying the adjoint variables of each discipline. The influence of various disciplines is represented by the form of the forcing term at the right end of the equation. The cross derivatives of each discipline equation are transferred through a loosely coupled form, the adjoint equations for various disciplines can be solved independently,and the efficient solution of the structure adjoint equation based on LDLT method is further realized. The gradient information of a typical flexible wing of the passenger plane is solved and compared with differential results taking aeroelastic effects into account. The numerical results and the lagged adjoint expression show that the lagged coupling is more conducive to preserving the original program structure and the modularization of the program, the accuracy of the gradient calculation fully meets the requirements of aerodynamic optimization design. The simulation technology proposed can provide research basis and technical support for aero-structural multidisciplinary optimization design of flexible wing.
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