Prediction of vibration response of aircraft panel covered with macro fiber composite patches

The traditional finite element model has the problems of high computational cost，more black-box operation，and lack of independent intellectual right. The analytical method is used to study the prediction of the vibration response of aircraft wall panels with macro fiber composite（MFC）patches under basic harmonic excitation. Based on classical laminate plate theory，electro mechanical coupling constitutive equations，and the energy method，the analytical model of the MFC-panel system under basic harmonic excitation is established. By employing velocity feedback control method and modal superposition principle，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 predictive results are extensively validated through the integration of literature data and experimental data obtained from a vibration testing system that is assembled. The results show that，compared to the literature results，the maximum deviation in the calculation of natural frequencies by the proposed model is less than 2%. Additionally，the maximum error in predicting the first two order resonance responses by the model is less than 8.6 %，and both of them are within an acceptable range.