Method for manufacturing a structural component of reinforced composite material with stiffening stringers

Abstract

A method for manufacturing a structural component (1) in composite material reinforced with stiffening stringers (2), which, in use, defines at least part of an outer casing (3) of a vector (4) and comprising a skin (5) and a plurality of stringers (2) having a hollow section rigidly and integrally fixed to said skin (5), the method comprising the steps of: a) laminating a plurality of first layers (5a) of uncured or precured composite material onto an external surface (6a) of a curing tool (6) to form said skin (5), such that a first face (5b) of said skin (5) which, in use, defines the inner surface of the structural component (1) facing the internal environment of the vector (4) faces the external surface (6a) of the tool (6);b) laminating respective pluralities of second layers (2a) of composite material onto longitudinal expandable hollow inserts (10) to form a plurality of said stringers (2) each having a longitudinal axis (B), such that each stringer (2) is wound, at least partially, on an external surface (10a) of a respective hollow insert (10) to determine a longitudinal cavity (11) of each stringer (2) coupled to a relative hollow insert (10) and thereby obtain a plurality of reinforcing elements (12) each defined by said stringer (2) wound on said hollow insert (10); c) placing each reinforcing element (12) on a second face (5c) of the skin (5) opposite said first face (5b) and defining, in use, the external surface of the structural component (1) that faces the environment external to the vector (4), and in such a way that the cavities (11) of each stringer (2) face said second face (5c);d) securing each reinforcing element (12) to the second face (5c) of the skin (5) in a respective fixed position with respect to the tool (6); e) housing the tool (6), the skin (5) and the reinforcing elements (12) inside a vacuum bag (13); f) compacting together the first layers (5a) that form the skin (5) with the second layers (2a) that form the stringers (2) by applying vacuum inside the vacuum bag (13); g) housing, after step f), the tool (6), the skin (5) and the reinforcing elements (12) in another vacuum bag (15); h) sealing the other vacuum bag (15) to delimit a vacuum chamber (16) inside it;i) applying a pre-set temperature and pressure to the outside of the vacuum chamber (16), in order to cure the composite material and determine the rigid and integral fixation of the stringers (2) to the second face (5c) of the skin (5). A structural component (1) obtained by the aforementioned manufacturing method is also described.

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