Ice protection device and method

An aircraft surface comprising a composite layer and an ice protection device for the aircraft surface, the device comprising:

• a layer of electrically conductive material configured and located at an outer face of the composite layer and being heated by electromagnetic induction,
• a perimetric monophasic winding configured to heat an edge surrounding a delimited area of the electrically conductive layer,
• an inner monophasic or multiphasic winding configured for heating an inside of the delimited area of the electrically conductive layer defined by the perimetric monophasic winding,
• a control unit, for independently controlling the perimetric monophasic winding and the inner monophasic or multiphasic winding, said control unit being configured such that the control unit is adapted to continuously operate the perimetric monophasic winding to avoid formation of ice in the edge of the delimited area and the control unit is also adapted to operate the inner monophasic or multiphasic winding when the ice formed inside the delimited area is to be detached.

An ice protection method for an aircraft surface comprising a composite layer and a layer of electrically conductive material configured and located at an external surface of the composite layer and adapted to be heated by electromagnetic induction, wherein the aircraft surface comprises:

• a perimetric monophasic winding configured to heat an edge surrounding a delimited area of the electrically conductive layer,
• an inner monophasic or multiphasic winding configured to heat an inside of the delimited area defined by the monophasic winding,
• the method comprising the steps of:
• continuously operating the perimetric monophasic winding by a control unit to avoid the formation of ice in the edge of the delimited area, and
• operating the inner monophasic or multiphasic winding when the ice formed in the area defined by the perimetric monophasic winding is to be detached.