Anti-icing system and method for controlling air intake of aircraft gas turbine engine

The invention belongs to the field of aerospace, relates to a data analysis technology, and aims at solving the problem that in the prior art, the icing condition of an air inlet cannot be analyzed and verified by combining the flow state and the air state of the air inlet, in particular to an anti-icing system and method for controlling the air inlet of an aircraft gas turbine engine. Comprising an anti-icing analysis platform, and the anti-icing analysis platform is in communication connection with a flow monitoring module, an icing monitoring module and a storage module; the flow monitoring module is used for monitoring and analyzing the gas flow state of a gas inlet of an aircraft gas turbine engine. The gas inlet of the engine is marked as a monitoring object, and whether the gas flow state of the monitoring object meets the requirement or not is judged according to the total flow value. According to the method, the gas flow state of the gas inlet of the aircraft gas turbine engine can be monitored and a