FIELD: electronics.
SUBSTANCE: invention relates to icing detection systems. Method of icing conditions detecting in aircraft flight involves, that processing unit determines actual power (Wr), developed by gas turbine engine, and theoretical power (Wt), which said gas turbine engine can theoretically develop. Theoretical power (Wt) is defined depending on theoretical model, which represents power depending on gas turbine engine gas generator rotation speed. Processing unit determines difference (ε) between said actual power (Wr) and said theoretical power (Wt). Processing unit generates alarm signal for warning on icing conditions presence, when said difference (ε) of power exceeds predetermined power threshold (SP) during time exceeding time threshold (STPS), and when temperature (T0) outside aircraft is within from lower temperature threshold (SINF) to upper temperature threshold (SSUP).
EFFECT: invention makes it possible to automatically determine presence of icing conditions during flight.
18 cl, 2 dwg
