FIELD: transport; heating.
SUBSTANCE: method is based on principle of measuring aerodynamic heating temperature difference on front surfaces of at least two blade sections spread over blade length. Increase of temperature difference evidence of icing on blade section with lesser radius of rotation, decrease of temperature difference evidence of icing of sections with lesser and wider radius of rotation. Optimal quantity of controlled points on blade surface and distance between them is chosen in each specific case depending on helicopter type, rotor diameter, and rated number of revolutions.
EFFECT: registration of icing event immediately on rotor blade and decrease of power consumption.
2 dwg
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