초록 ▼

The invention relates to a method for making a nacelle element (2) that includes the steps of: (A) forming an array of heating resistors on a substrate using a photolithographic method; (B) applying a web (50, 52) of composite materials onto the array obtained in step (A); (C) applying an inner skin

The invention relates to a method for making a nacelle element (2) that includes the steps of: (A) forming an array of heating resistors on a substrate using a photolithographic method; (B) applying a web (50, 52) of composite materials onto the array obtained in step (A); (C) applying an inner skin (12) onto the de-icing assembly (13) thus obtained. The invention also relates to a nacelle including such an element (2).

대표청구항 ▼

1. A method for making an aircraft nacelle element, comprising: A. forming a single layer of an array of heating resistors comprising a metal or alloy with a resistivity between 0.00024 Ω-mm and 0.002 Ω-mm using a photolithographic method;B. encapsulating the array between webs of composite material

1. A method for making an aircraft nacelle element, comprising: A. forming a single layer of an array of heating resistors comprising a metal or alloy with a resistivity between 0.00024 Ω-mm and 0.002 Ω-mm using a photolithographic method;B. encapsulating the array between webs of composite materials to form a de-icing assembly for a leading edge of the aircraft nacelle; andC. applying an inner skin onto an inner side of the de-icing assembly. 2. The method according to claim 1, further comprising a step B1 between steps B and C in which the assembly obtained at the end of step B is pierced with piercing means so as to obtain acoustic holes. 3. The method according to claim 1, wherein the inner skin includes a composite layer on which a honeycomb structure is mounted. 4. The method according to claim 3, further comprising a step D in which the de-icing assembly and the composite layer of the inner skin are pierced using a piercing means. 5. The method according to claim 3, wherein the composite layer of the inner skin is pierced beforehand in step C. 6. The method according to claim 2, wherein the acoustic holes obtained have a diameter between 0.2 mm and 2.5 mm. 7. The method according to claim 1, wherein, before step B, an electric power array is made on a face opposite to a face of a substrate including the array of heating resistors. 8. The method according to claim 7, wherein the power array is connected to the heating resistor array via a connection means passing through the substrate. 9. The method according to claim 7, wherein the power array comprises a metal or an alloy whereof an ambient temperature resistivity is equal to about 1.7 μΩ·cm. 10. The method according to claim 1, wherein the alloy of the heating resistors comprises at least one of alloys of copper and nickel. 11. The method according to claim 1, wherein the method uses a substrate manufactured from glass fibers, epoxy resin, or a thermoplastic insulating film. 12. The method according to claim 7, wherein, during step A, the substrate is substantially flat. 13. The method according to claim 1, wherein each web comprises a material of the glass fiber type associated with a thermoduric or thermoplastic resin. 14. The method according to claim 1, wherein before step C, a surface of the de-icing assembly is cut such that a maximum gap between the de-icing assembly and the inner skin is in the vicinity of 1.7 mm. 15. The method according to claim 1, wherein at the end of step B or C, a surface coating is applied on the de-icing assembly. 16. A turbojet engine nacelle including an element obtained using the method according to claim 1. 17. The nacelle according to claim 16, wherein the element is an air intake lip.