Aeroelastic tailoring of laminated composite structure demands relatively high computational time especially for dynamic problem.\nThis paper presents an efficientmethod for aeroelastic dynamic response analysis with significantly reduced computational time. In\nthis method, a relationship is established between the maximum aeroelastic response and quasi-steady deflection of a wing subject\nto a dynamic loading. Based on this relationship, the time consuming dynamic response can be approximated by a quasi-steady\ndeflection analysis in a large proportion of the optimization process. This method has been applied to the aeroelastic tailoring of a\ncomposite wing of a tailless aircraft for minimum gust response.The results have shown that 20%ââ?¬â??36% gust response reduction has\nbeen achieved for this case. The computational time of the optimization process has been reduced by 90% at the cost of accuracy\nreduction of 2âË?¼4% comparing with the traditional dynamic response analysis.
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