During the flight of an aircraft， it may encounter various ice coverage situations. To study the impact of different ice coverage situations on the ice removal effect of the piezoelectric de-icing system， a combination of finite element simulation and cold environment ice removal experiments is adopted. In the ultrasonic frequency range， the research is conducted on the ice removal frequency， the material selection of the vibration source piezoelectric device， as well as the influence of parameter changes such as ice coverage situations （icing area， segmentation form， thickness） on the piezoelectric ice removal effect on the structural surface. The results show that under the layout method of piezoelectric ceramics in this paper， the 20.4 kHz excitation frequency has the best ice removal effect， and it can completely remove the ice on the structural surface within 90 s. In addition， the ice removal effect of different piezoelectric materials increases with the increase of the piezoelectric coefficient of the vibration source piezoelectric material. Changing different ice coverage situations can lead to an increase in the number of ice segments， a change in the icing area （increasing along the length direction or decreasing along the width direction）， and a reduction in the ice thickness， all of which will increase the shear stress value at the ice interface and shift the ice removal frequency accordingly.