The application of virtual testing technology for aircraft structural strength can effectively verify the rationality of physical test designs and predict the dynamic responses of physical tests. The primary step in this process is rigid-flexible coupling dynamics modeling, which encompasses the modeling of both the rigid lever loading system and the flexible aircraft body. To address the issue of the heavy workload involved in designing the lever loading system, a parametric design approach is adopted, combining MATLAB and Adams to establish a rigid model of the lever loading system that is adjustable in parameters and data-driven. Using the finite element software HyperWorks, the Craig-Bampton method is applied to construct a flexible body model based on Adams software. Finally, coupling interactions are created to connect the flexible body with the rigid model of the lever loading system, achieving rigid-flexible coupling dynamic modeling of aircraft loads based on Adams.