The electro-impulse de-icing system (EIDI) is a mechanical de-icing system that guarantees the safe flight of the aircraft under icing weather conditions. It owns many merits such as high reliability and low energy consumption. To solve the problem of the small de-icing area under single-channel, a dual-channel EIDI system model is proposed. The electro-magnetic field and de-icing results of the dual-channel EIDI system are investigated. Comparisons of de-icing results between simulations and experiments on the flat aluminum plate are also made. Furthermore, the de-icing research is carried out with a real wing structure by varying the excitation time and magnitude of impulse load. Simulation results of the electro-magnetic field show that the maximum of the density of electro-magnetic force always appears at the midpoint of the inner and outer radius of coils. The excitation of the two coils is independent and can be decoupled. The de-icing results illustrate that the de-icing rate increases with the striking intervals and impulse load. The load multiple (LM) should be selected between 1.5 and 3 for the dual-channel EIDI system for energy optimization. In addition, it is advisable to distribute the impulse loads with the largest possible difference on both sides when the LM is 1–3.

Aircraft icing seriously jeopardizes flight safety. The design of aircraft anti-icing/de-icing systems requires a thorough understanding of the adhesion between the ice and the substrate. In this research, an experimental device that can be housed within a wing is designed and constructed. Simulation analysis of the interfacial stresses is performed, which reveals that increasing the load and the interface size led to a deterioration in the uniformity of stresses at the interface. In addition, the ice layer does not undergo cohesive damage during the tests. The normal ice adhesion strength is evaluated in an icing wind tunnel using the methodology outlined in this paper. Glaze ice exhibits an increase in normal adhesion strength at lower temperatures, whereas the trend is reversed for rime ice. The minimum adhesion strength occurs near the medium volume diameter (MVD) of 30 µm. Furthermore, the normal strength is significantly enhanced by increase in wind speed and surface roughness, as well as by surface painting. The adhesion strength of aluminum substrates to ice is greater compared to titanium and stainless steel. Compared to shear adhesion strength, normal adhesion strength is less sensitive to various influencing factors. The proposed experimental framework provides precise measurement of normal adhesion strength of impact ice in the icing wind tunnel.