FIELD: aviation.
SUBSTANCE: invention relates to anti-acing systems of aircrafts. Anti-icing system of composite aircraft aerodynamic surfaces comprises a system of temperature control sensors, wire connection to aircraft power supply system lined on to outer surface out of the aircraft covering, and electric heating element. Element of carbon fibre is built in outer surface of the aircraft covering in parallel to the line of maximum icing of aerodynamic surface front edge.
EFFECT: possibility to even heating of aircraft outer surfaces in places prone to icing.
1 cl, 2 dwg
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