Evaluation of Composite Wing for XFV-12A Airplane. Appendix C.
Final rept. Aug-Sep 78.
ROCKWELL INTERNATIONAL COLUMBUS OHIO COLUMBUS AIRCRAFT DIV
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This Appendix, prepared as a supplement to final report NADC-77183-30 dated December 1976, presents results of static and fatigue tests of a graphiteepoxy wing box structure designed and fabricated by the Columbus Aircraft Division CAD of Rockwell International Corporation under contract N62269-74-C-0577. These tests were conducted by the Navy at the Naval Air Development Center, Warminster, PA. during the period August-September 1978. Static loads to 150 of design limit load for the critical carrier based landing condition were applied to the composite wing box structure followed by a two lifetime fatigue spectrum loading with no evidence of structural damage or deformation. Descriptions of the test setup, applied loadings, strain gage data, deflection transducer data, and comparisons of predicted vs recorded strain and deflection measurements are presented. Author
- Laminates and Composite Materials