The results of an analytical and experimental investigation of the response of composite I-stiffener panels with extension-shear coupling are presented. This tailored concept, when used in the panel cover skins of a tiltrotor aircraft wing has the potential for increasing the aeroelastic stability margins and improving the aircraft productivity. The extension-shear coupling is achieved by using unbalanced plus or minus 45 deg. plies in the skin. Experimental and STAGS analysis results are compared for eight I-stiffener panel specimens. The results indicate that the tailored concept would be feasible to use in the wing skin of a tiltrotor aircraft. Evaluation of specimens impacted at an energy level of 500 in.-lbs indicate a minimal loss in stiffness and less than 30 percent loss in strength. Evaluation of specimens with severed center stiffener and adjacent skin indicated a strength loss in excess of 60 percent.
Response of Damaged and Undamaged Tailored Extension-Shear-Coupled Composite Panels
Journal of Aircraft ; 43 , 2
2008-01-01
Preprint
Keine Angabe
Englisch
Response of Damaged and Undamaged Tailored Extension-Shear-Coupled Composite Panels
Online Contents | 2006
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