FIELD: transport.
SUBSTANCE: invention relates to aircraft engineering, particularly, to turbojet nacelles. The nacelle air intake leading edge comprises leading edge, inner web, and means for deicing and/or protection against icing. Said inner edge confines the lengthwise compartment inside said leading edge. Said leading edge is composed of at least one multiaxial composite structure. The latter is made by laying of 1D or 2D plies to be bonded together by reinforcing fibres extending there through and, at least, over their depth. Said multiaxial composite structure is arranged over the heating element and allow ice removal and/or protection against icing.
EFFECT: efficient ice removal and/or protection against icing.
12 cl, 5 dwg
