US Patent 10889381 Anti-icing system and aircraft

An anti-icing system according to the present invention blows heated air to a curved inner surface of a main wing of an aircraft. The anti-icing system includes: a piccolo tube that includes a flow path through which the heated air flows in a longitudinal direction from a rear end to a front end, and a plurality of ejection holes provided along the longitudinal direction to make the flow path communicate with an outside; and an engine that supplies the heated air toward the piccolo tube. The heated air ejected from the ejection holes of the piccolo tube is ejected toward an upper limit position and a lower limit position of an outside airflow stagnation point that are virtually formed on the main wing.