Leading edge structure, in particular for an air inlet of an aircraft engine nacelle

Abstract

A leading edge structure for an air inlet of an aircraft nacelle includes a leading edge and an inner partition defining a longitudinal compartment that is located inside the leading edge and accommodates a de-icing and/or anti-icing mat. The leading edge structure includes a multi-axial composite structure placed on top of a heating element for anti-icing and/or de-icing.

What is claimed is: 
     
         1 . A leading edge structure for an aircraft nacelle air inlet comprising: a leading edge and an inner partition defining a longitudinal compartment inside said leading edge accommodating at least one of deicing and anti-icing means, wherein said leading edge is formed from at least one multiaxial composite structure placed on top of a heating element designed for deicing and/or anti-icing. 
     
     
         2 . The structure according to  claim 1 , wherein the multiaxial composite structure comprises reinforcing fibers made from carbon, copper or aluminum. 
     
     
         3 . The structure according to  claim 1 , wherein it comprises a multiaxial composite structure made using a sewing method. 
     
     
         4 . The structure according to  claim 1 , wherein it comprises a multiaxial composite structure made using a needling method. 
     
     
         5 . The structure according to  claim 1 , wherein the multiaxial composite structure comprises a weaving frame of the angle interlock type. 
     
     
         6 . The structure according to  claim 2 , wherein the multiaxial composite structure comprises reinforcing fibers whereof the orientation is inclined relative to the normal to the plane of the structure. 
     
     
         7 . The structure according to  claim 2 , wherein the multiaxial composite structure comprises reinforcing fibers arranged parallel to the normal of the plane of the structure. 
     
     
         8 . The structure according to  claim 2 , wherein the reinforcing fibers do or do not pass completely through the thickness of the composite structure. 
     
     
         9 . The structure according to  claim 1 , wherein the leading edge has a variable thickness along its profile, and in particular, for example, a greater thickness at major curves and lesser at its ends. 
     
     
         10 . The structure according to  claim 2 , wherein the leading edge has a density of reinforcing fibers that varies depending on the thermal needs. 
     
     
         11 . An air inlet, wherein it comprises a leading edge structure according to  claim 1 . 
     
     
         12 . A nacelle for an aircraft engine, wherein it comprises an air inlet according to  claim 11 .