US2025083398A1 · US · A1
| Field | Value |
|---|---|
| Publication number | US-2025083398-A1 |
| Application number | US-202418957004-A |
| Country | US |
| Kind code | A1 |
| Filing date | Nov 22, 2024 |
| Priority date | Jul 27, 2020 |
| Publication date | Mar 13, 2025 |
| Grant date | — |
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A process for manufacturing a structural component made of composite material comprising a skin and at least one stiffening stringer applied rigidly and integrally to one face of the skin. The process comprises a) arranging, on a tool, a plurality of first layers of uncured or pre-cured composite material, forming the stringer and having a raised portion protruding from at least one flange; b) arranging, on the tool, a plurality of second layers of uncured or pre-cured composite material forming the skin; c) making a face of the skin and the flange of the stringer adhere to each other; d) applying a predetermined temperature and pressure on the assembly to compact the layers together, possibly curing the uncured material and rigidly joining the skin to the stringer; and e) performing a cutting operation on the free end side edge/s of the flange in a slanted direction.
Opening claim text (preview).
1 . A process for manufacturing a structural component in composite material comprising a skin and at least one stiffening stringer applied rigidly and integrally to a face of said skin; said process comprising the following steps: a) arranging on a tool a plurality of first layers of uncured or pre-cured composite material forming said stringer, wherein said stringer presents a longitudinal axis and has a raised portion-protruding from at least one flange extending parallel to said longitudinal axis and along a lying surface, which is flat or is a surface of revolution; b) arranging on said tool a plurality of second layers of uncured or pre-cured composite material forming said skin; c) making a face of said skin, parallel to said lying surface, and said flange of said stringer-adhere to each other; d) applying predetermined temperature and pressure on the assembly thus formed so as to compact said layers together, possibly curing the uncured material and rigidly joining said skin to said stringer; e) performing a cutting operation on the free end side edge/s of said flange in a slanted direction with respect to said lying surface and to the layers forming the flange itself and in such a way that the cut layers of said flange have, in the subsequent phase c), an extension along said lying surface, increasing towards the skin itself; and f) covering at least said end side edge/s of said flange with a coating of composite material so as to seal outwards the layers cut in step e) and forming said flange; said coating of composite material defining, at the end of said process, a constituent or integral part of said structural component; wherein said step f) is carried out by applying one or respective patch element/s in uncured composite material on the cut side edge/s of said flange so as to cover it/them and seal it/them outwards and to define said coating of composite material; and wherein during the application of said patch element or of each said patch element on the cut side edge/s, a first portion of the patch element itself covers the respective cut side edge of said flange and a second portion, still protruding from the cut side edge itself, is folded on said flange so as to interpose itself, in said step c), between said skin and said stringer or between said skin and said tool. 2 . The process according to claim 1 , wherein said stringer has, in a section transversal with respect to said longitudinal axis, a T- or L- or Z- or J-shaped profile. 3 . The process according to claim 1 , wherein said raised portion of said stringer is concave and is placed centrally between two said lateral flanges extending along said lying surface; and wherein, in said step c), said skin and said concave raised portion of said stringer form a closed-profile cavity. 4 . The process according to claim 3 , comprising, after step a) and before step c), the step of h) positioning at least one longitudinal expandable insert inside the concave raised portion of said stringer, so that the expandable insert is entirely housed within the cavity defined during step c); and the process further comprising, after step c) and during step d), the step of i) expanding said expandable insert against the walls delimiting the cavity to maintain said cavity. 5 . The process according to claim 4 , wherein the step i) is performed by applying pressure inside said expandable insert, in particular the same pressure applied outside the assembly during step d). 6 . The process according to claim 4 , wherein the step i) is carried out by applying heat to said expandable insert.
Stringers; Longerons · CPC title
provided with ridges or ribs, e.g. joined ribs · CPC title
locally reinforced, e.g. by fillers (filler concentrated near the surface B29C70/64) · CPC title
Perforating, cutting or machining during or after moulding · CPC title
Manufacturing or assembling aircraft, e.g. jigs therefor · CPC title
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