In order to predict the characteristics of the vibration–acoustic coupling of an aircraft model, the finite element method–boundary element method of dynamic model (FEM-BEM dynamic model) is established. The numerical calculations and experiments of the structural vibration acceleration responses and the sound pressure levels in the model cabin under the strong noise excitations are carried out in the low and middle frequency area. By comparing the results of experiments and simulations, it’s found that the structural vibration responses and the sound pressure responses mainly distribute in the range of low and medium frequency, in which the simulated and experimental results also match each other well. This indicates the established finite element/boundary element vibration–acoustic coupled dynamic model and the calculation method proposed in this study are feasible.
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