Composite structures with stiffeners and method of making the same

A method for assembling a stiffened composite structure includes a step of co bonding a cured infused composite stiffener 22 to a pre-preg composite laminate skin element 20. The pre-preg composite laminate skin element is dimensionally changeable (e.g. is at b-stage cure). Alternatively the method...

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Bibliographische Detailangaben
Hauptverfasser:	Max Marley Osborne, David Andrew Pook, Ronnie Karol Ligeti, Lauren Anne Burns, Peter J. Lockett, James A. Thomas, Andrew Kenneth Glynn
Format:	Patent
Sprache:	eng
Schlagworte:	AFTER-TREATMENT OF THE SHAPED PRODUCTS, e.g. REPAIRING INDEXING SCHEME ASSOCIATED WITH SUBCLASS B29C, RELATING TO PARTICULARARTICLES INDEXING SCHEME ASSOCIATED WITH SUBCLASSES B29B, B29C OR B29D, RELATING TO MOULDING MATERIALS PERFORMING OPERATIONS SHAPING OF MATERIAL IN A PLASTIC STATE, NOT OTHERWISE PROVIDEDFOR SHAPING OR JOINING OF PLASTICS TRANSPORTING WORKING OF PLASTICS WORKING OF SUBSTANCES IN A PLASTIC STATE, IN GENERAL
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Beschreibung
Zusammenfassung:	A method for assembling a stiffened composite structure includes a step of co bonding a cured infused composite stiffener 22 to a pre-preg composite laminate skin element 20. The pre-preg composite laminate skin element is dimensionally changeable (e.g. is at b-stage cure). Alternatively the method for assembling the stiffened composite structure includes a step of coupling the stiffener 22, having a preform of a plurality of braided fibres, to the dimensionally changeable pre preg composite laminate skin element. The coupling may comprise co-bonding. A layer of bonding material may be provided between the skin and stiffener. Bonding may take place under pressure and heating. The stiffener may be formed by infusing dry fibres with resin and curing. Used in aircraft construction