<p>A novel integrated active–passive de‑icing system combining electro-impulse and superhydrophobic coating is proposed to meet the future needs of advanced civil aircraft for low-energy, high-efficiency de-icing solutions. Aiming at the simulation and analysis requirements of the composite de-icing system prototype, a unified simulation framework and process are proposed, based on the de-icing mechanism of electro-impulse and the low adhesion characteristics of super-hydrophobic coatings. A multi-mechanism damage model for ice fracture and ice/skin interface debonding was developed, considering aerodynamic loads to simulate the de-icing process and residual ice morphology more accurately. The simulation results show improved consistency with experimental data compared to previous studies, achieving a more than 40% reduction in calculation time and a 20.6% reduction in relative error compared to traditional models. Furthermore, models of the composite de-icing system were established for the CHN-T2 wing leading edge structure. A parameter‑space study, including electro-impulse load, ice/skin adhesion strength, and coil installation position, was analyzed to understand their effects on the de-icing performance. These findings provide crucial insights into the development and engineering application of novel active–passive de-icing systems for advanced civil aircraft.</p>