FIELD: transport.
SUBSTANCE: invention relates to aircraft engineering, particularly, to control over at least one resistive heating element 1 incorporated with turbojet nacelle deicing system. It differs from know designs in that it includes the steps whereat parameters of external flight conditions are received from aircraft central control unit 6 and definition of heat model corresponding to flight conditions. Depending upon selected heat model required electric power 4 is fed to said resistive heating element.
EFFECT: optimised consumption of electric power, higher reliability.
11 cl, 3 dwg
