The recent introduction of composite materials in aircraft primary structures has resulted in lower weight and improved performance. These improvements require the development of new design concept and manufacturing techniques for weight and cost efficient structures. Current manufacturing approaches are focused on cocuring, where the skin and stiffeners are cured together in a single autoclave cure, and secondary bonding, where stiffeners and skin are cured seperately and then bonded together with an adhesive film. For this study, cocuring and secondary bonding manufacturing techniques were used to produce four stiffened panels. Experience gained with those techniques is discussed. Ultrasound C-scan inspection was carried out to detect any defects in the panels. These panels were tested in compression to verify their structural efficiency of assembling technique. This paper presents the details of different assembly methods, and identifies and discusses the advantages and disadvantages of each manufacturing technique.
Structural efficiency of different assembly methods for stiffened composite panels: cocuring and secondary bonding
Strukturelle Leistungsfähigkeit verschiedener Herstellungsverfahren für versteifte Verbundwerkstoffplatten: zusammen Aushärten (Cocuring) und Sekundärbindung
1997
8 Seiten, 7 Bilder, 1 Tabelle, 7 Quellen
Conference paper
English
Wing assembly having discretely stiffened composite wing panels
European Patent Office | 2023
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