A predictive study is conducted on the vibration response of aircraft wall panels with Macro Fiber Composite (MFC) patches under basic harmonic excitation. Based on classical laminate plate theory, electromechanical coupling constitutive equations, and the energy method, an analytical model of the MFC-panel system under basic harmonic excitation is established. By employing velocity feedback control and modal superposition principles, the vibration response of the structure system before and after active control under such an excitation load is successfully solved. The analytical model and its prediction results are extensively validated through the literature data and experimental data obtained from a vibration testing system that is assembled. The research results indicate that, compared to the literature results, the maximum deviation in the calculation of natural frequencies by the proposed model does not exceed 2 %. Additionally, the maximum error in predicting the first two order resonance responses by the model is less than 8.6 %, with both of them being within an acceptable range. The analytical model and response prediction method presented in this study provide a new approach and analytical tool for analyzing and evaluating the dynamic mechanics and vibration control performance of MFC-panel structures.