The autoclave based THERM-X(sub R) process was evaluated by cocuring complex curved panels with frames and stiffeners. The process was shown to result in composite parts of high quality with good compaction at sharp radius regions and corners of intersecting parts. The structural properties of the postbuckled panels fabricated were found to be equivalent to those of conventionally tooled hand laid-up parts. Significant savings in bagging time over conventional tooling were documented. Structural details such as cocured shear ties and embedded stiffener flanges in the skin were found to suppress failure modes such as failure at corners of intersecting members and skin stiffeners separation.
Innovative Fabrication Processing of Advanced Composite Materials Concepts for Primary Aircraft Structures
1992
248 pages
Report
No indication
English
Aircraft , Composite Materials , Engineering Materials , Tooling, Machinery, & Tools , Aircraft construction materials , Aircraft structures , Composite materials , Cost reduction , Curved panels , Fabrication , Structural analysis , Tooling , Aircraft design , Autoclaves , Compacting , Composite structures , Curing , Failure modes , Flanges , Process control (Industry)
Advanced structures and materials - Advanced concepts for primary metallic aircraft structures
Online Contents | 1998
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