Integrated Research on Carbon Composite Materials. Volume III. Structural Component Development
Abstract
The performance prediction, testing, and post-test evaluation of a representative graphite-fiber, resin-matrix aircraft fuselage component are presented. Polyamide-imide, polysulfone, and nylon are investigated as resin matrix. Additional material properties were determined and structural margins of safety defined by discrete element analysis. After seven response tests under various load combination, the component was tested to destruction under combined bending and shear loads. Failure occurred at 110 percent of the target design load but below the failure load predicted from tests on flat panels. A WEIGHT SAVING OF 27 PERCENT OVER AN ALUMINUM STRUCTURE OF EQUIVALENT STRENGTH WAS DEMONSTRATED. Post-test evaluations included tensile and compression tests on curved skin panels, on stringers, and on stringer- kin combinations. Optical and electron microscopic examination of the fracture surfaces provided further insight into the failure mechanism.
Document Details
- Document Type
- Technical Report
- Publication Date
- Jan 01, 1971
- Accession Number
- AD0879661