Abstract
Abstract : An improved certification methodology for composite structures was developed. The methodology permits certification of bonded and concurred composite structures with the same level of confidence as bolted structures. This methodology also ensures that the threat of in service low velocity impact is adequately addressed. The methodology was demonstrated on actual composite aircraft structures to evaluate the damage tolerance capability of these structures. The F/A-18A upper wing skin was used for methodology demonstration. Sensitivity studies were conducted to determine the influence of impact damage threat scenarios and damage tolerance design requirements on the reliability of composite structures.
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