Optimal design of composite wing structures with blended laminates

摘要: Abstract In this paper we formulate the problem of wing box design optimization using composite laminates with blending constraints. The use necessitates inclusion fiber orientation angle layers as well total thickness laminate variables in problem. is decomposed into several independent local panel problems. general such an approach results a nonblended solution no continuity lay ups across panels, which may not only increase up cost but also be structurally unsafe due to discontinuities. need for blended increases complexity many fold. impose constraints globally by guide based methodology within genetic algorithm scheme and compare published ones. Two different schemes – outer inner are presented. result shows that optimum obtained current has better reported weight on lower side. Finally, parametric study effect global deflection constraint