Aeroelastic tailoring of blended composite panels with lamination parameters

An optimization method for blended composite panels with aeroelastic constraint is presented in this paper. On the basis of composite panel sub-region division, the lamination parameters of a guide laminate and length indicator of each ply of the guide laminate are introduced as design variables using parallel genetic algorithm(GA) for optimization. For each individual, the inverse problem of obtaining laminate configuration to target the lamination parameters is solved by another GA. The method of defining design variables can reduce the number of design variables obviously compared with previous work. And the numerical results indicate that the present method is capable of producing fully blended designs of composite wing with aeroelastic performance improvement and weight reduction.