APPLICATION OF AEROELASTIC TAILORING TO ARROW WING CONFIGURATION

A computer code for aeroelastic tailoring of an arrow wing configuration of Supersonic Transport (SST) is developed. This computer code includes the strength analysis using an original finite element code and the aeroelastic analysis. In the optimization process of this code, Genetic Algorithm (GA) is employed to find the optimum laminate construction of the wing box for the minimum structural weight under the static strength and the aeroelastic constraints. This code is applied to a preliminary design of an arrow wing configuration. The optimum design satisfying only the static strength constraint is not satisfied with the aeroelastic constraint. In consideration of the aeroelastic constraint, the flutter characteristic is optimized and the optimum laminate construction which satisfies both the static strength and the aeroelastic constraints is obtained.