在基于分区求解的流固耦合数值仿真中，流体和固体求解器使用独立的网格进行计算，因而在耦合界面上网格通常是不匹配的。气动力等物理量需要在界面处进行数据传递，其守恒性及准确性严重影响着流固耦合求解的精度。为减少气动力传递的误差，本文提出了一种基于局部曲面降维和精确单元积分的数据传递方法。在该方法中，首先基于固体网格构建广义二维坐标系，然后投影流体网格，计算相交面积来获得流体单元对固体节点力的贡献。数值算例表明该方法能够实现各种类型的非匹配网格之间精确且高效的数据传递。相比于传统方法，该方法能够保证力的完全守恒，实现接近零误差的气动力传递，且气动力分布更为光滑，力矩的误差可降低一个量级以上。最后，通过Rotor67转子、STCF4标准涡轮和Hirenasd机翼的流固耦合数值模拟对比了不同数据传递方法对流固耦合仿真结果的影响，计算结果表明本文所提出的界面数据传递方法对于固体变形和气动阻尼的计算更为准确。

In numerical simulations of fluid-solid coupling based on partitioned method, the fluid and solid solvers utilize independent grids for computations thus the grids are typically non-matching at the coupling interface. Physical quantities such as aerodynamic forces need to transfer between the interface, which conservation is essential to the accuracy of the simulation solutions. In order to reduce the error of aerodynamic force transfer, this paper proposes a data transfer method based on local surface degradation and accurate cell integration. In this method, a generalized two-dimensional coordinate system is initially constructed based on the solid mesh. Subsequently, the fluid mesh is projected, and the intersection area is calculated to determine the contribution of the fluid cells to the solid nodal force. The method has been demonstrated to be effective in achieving accurate and efficient data transfer between non-matching meshes of varying types. In comparison to the traditional method, the proposed method can essentially ensure the comprehensive conservation of force, facilitate near-zero error aerodynamic force transfer, and result in a smoother aerodynamic force distribution. Additionally, the error of the moment can be reduced by more than one order of magnitude. Finally, the influence of different data transfer methods on the fluid-solid coupling results are evaluated through the simulations of rotor67, STCF4 standard turbine and Hirenasd wing which indicate that the interface data transfer approach proposed in this paper is more precise in calculations of solid deformation and aerodynamic damping.