This assembly comprises a first component (9), a second component (3), and a connecting device (19) for connecting these two components together, this device (19) being of the type that maintains the integrity of the surface of said second component (3), and the assembly being noteworthy in that sai
This assembly comprises a first component (9), a second component (3), and a connecting device (19) for connecting these two components together, this device (19) being of the type that maintains the integrity of the surface of said second component (3), and the assembly being noteworthy in that said connecting device (19) comprises a structural skin (21) fixed to said first component (9) and a porous material (23) attached to this structural skin and fixed by contact to said second component (3).
대표청구항▼
1. An air intake assembly for an engine nacelle comprising: a structural inner partition,an outer panel exposed to an aerodynamic flow and disposed radially outward from an air intake of the engine nacelle,a connecting device between said structural inner partition and said outer panel, the connecti
1. An air intake assembly for an engine nacelle comprising: a structural inner partition,an outer panel exposed to an aerodynamic flow and disposed radially outward from an air intake of the engine nacelle,a connecting device between said structural inner partition and said outer panel, the connecting device configured to preserve integrity of an aerodynamic surface of said outer panel, the connecting device comprising: a structural skin fixed to said structural inner partition, anda porous material attached on said structural skin and fixed by contact on an inner side of said outer panel such that the connecting member does not intrude on the outer panel and alter aerodynamic characteristics of the aerodynamic surface of the outer panel. 2. The assembly according to claim 1, wherein said porous material comprises at least one of foams, expanding materials, felts, aggregates of small elements. 3. The assembly according to claim 1, wherein said porous material has closed cells that are not communicating. 4. The assembly according to claim 1, wherein said porous material has open cells that are communicating. 5. The assembly according to claim 1, wherein said porous material is fixed by brazing or adhesion on said structural skin and/or on said outer panel. 6. The assembly according to claim 1, wherein said structural skin extends beyond said porous material and ends are also fastened by contact on said outer panel. 7. The assembly according to claim 1, wherein said structural inner partition is fixed by riveting on said structural skin. 8. The assembly according to claim 1, wherein a material forming said porous material comprises at least one of metal, polymer, ceramic and composite materials. 9. The assembly according to claim 1, wherein said porous material comprises at least one of materials resisting temperatures of up to 200° C., material resisting temperatures up to 400° C., materials resisting temperatures up to 600° C., and materials resisting temperatures up to 800°. 10. The assembly according to claim 1, wherein a material forming said porous material comprises metal or ceramic materials. 11. The assembly according to claim 10, wherein said ceramic material is carbon foam. 12. The assembly according to claim 1, wherein said porous material is adhered to said structural skin. 13. The assembly according to claim 1, wherein said structural skin is formed in materials comprising at least one of metal alloys, ceramics, metal matrix composites, and ceramic matrix composites. 14. The assembly according to claim 1, wherein said porous material is formed by a superposition of layers of porous materials with different characteristics, in a direction of a thickness of the material. 15. The assembly according to claim 1, wherein said porous material is formed by a juxtaposition of blocks of porous materials with different characteristics, in a direction parallel to a middle plane of the material. 16. The assembly according to claim 1, wherein at least one honeycomb structure is juxtaposed with said porous material, said honeycomb structure and said porous material being sandwiched by said structural skin and said outer panel. 17. An air intake structure for a turbojet engine nacelle with pneumatic de-icing, including an air intake lip, said outer panel and said structural inner partition connecting said air intake lip to said outer panel and defining a pneumatic de-icing compartment, wherein said structural inner partition is connected to said outer panel by said connecting device, such that said structural inner partition, said connecting device and said outer panel form the air intake assembly according to claim 1. 18. The air intake structure according to claim 17, wherein said air intake lip is provided with at least a first sound attenuation panel made of an open cell porous material able to withstand a temperature of up to 400° C. and with a high thermal conductivity, situated inside said de-icing compartment and maintained by an upstream maintenance sheet and a downstream maintenance sheet, said first sound attenuation panel and the downstream maintenance sheet defining, with said structural inner partition and said air intake lip, the air intake assembly. 19. The air intake structure according to claim 18, further comprising a second sound attenuation panel made of an open cell porous material fixed inside said air intake lip downstream of the structural inner partition, separated from said first sound attenuation panel by a joint made of an open cell porous material able to withstand a temperature of up to 400° C. and having a low heat conductivity. 20. The air intake structure according to claim 19, wherein said second sound attenuation panel is chosen in the group comprising a panel with a porous material and open cells able to withstand a temperature of up to 120° C., and a panel with a honeycomb structure. 21. The air intake structure according to claim 19, wherein said first sound attenuation panel, said joint in a porous material and said second sound attenuation panel are covered with a shared sheet on which said structural inner partition is fixed, by riveting, said structural inner partition, said shared sheet and said first/second sound attenuation panels defining the air intake assembly. 22. The air intake structure according to claim 17, wherein the air intake lip forms a single-piece assembly with an outer wall of the air intake structure, said single-piece assembly being able to slide in relation to a fan case of the turbojet engine.
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이 특허에 인용된 특허 (4)
Novak Philip F. (Wichita KS) Shannon Robert D. (Wichita KS) Pinckney Robert L. (Cheyney PA) Humphreys ; Jr. James R. (Wichita KS), Aircraft construction.
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