Design test of electro- impulse de-icing system of an aircraft

This paper describes B-S model and the principle of electro-impulse de-icing (EIDI) system of an aircraft which use electromagnetic force to remove the ice. A finite element analysis model of the EIDI system is established, and the peak current, the magnetic field and the transient pulse force are separately calculated. Meanwhile, without changing circuit, the factors which may influence deicing such as discharging voltage, capacitor and skin-to-coil gap are studied. The results indicate that the greater discharging voltage, larger capacitance and smaller skin-to-coil gap, the larger peak impulse force in the same circuit. It means the de-icing result will be better under the conditions of these parameters. Then a ground EIDI test is proposed for application of B-S model, which predicts effective ways for EIDI system to remove ice.