The use of composite materials in the primary structure of aircraft is becoming more common. Stiffened composite panels have been designed for a variety of load carrying conditions in aircraft. In this study, design considerations and manufacturing techniques for hat-stiffened composite panels were investigated. The cocuring manufacturing technique was used to produce the stiffened composite panel. Ultrasonic C-scan inspections were carried out to detect any defects in the panel. The panel was tested in compression to verify its structural efficiency. The panel was designed to carry loads after initiation of skin buckling. Both the buckling and post-buckling behavior were predicted using the finite element method. Eight-node 3-D laminated composite general shell elements were used in the analysis. The predicted buckling load and post-buckling response were compared with the test data. The buckling load of the stiffeners was also predicted by the finite element method and this load was considered as the failure load of the panel. In addition to the analysis and test results, this paper also presents the details of the laminate design and testing procedures.
A study of compression loaded hat-stiffened composite panels
Eine Untersuchung von druckbelasteten Verbundwerkstoffpanelen mit deckelartiger Versteifung
1995
8 Seiten, 6 Bilder, 1 Tabelle, 5 Quellen
Conference paper
English
Buckling and Postbuckling Behavior of Stiffened Composite Panels Loaded in Compression (TN)
Online Contents | 1997
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