A computer code for areoelastic tailoring of an arrow wing supersonic cruise configuration is developed. A direct search method is employed to find the optimum fiber orientation angles and thickness distributions of the upper and lower skin panels of the wing box for the minimum weight design under the multiple constraints. The static strength, symmetric and antisymmetric flutter velocities are taken into account at the same time as the constraints. The code is applied to a typical arrow wing configuration to demonstrate its capabilities.
Application of direct search method to aeroelastic tailoring of an arrow wing configuration
nalsp0049021.pdf
(416.68KB)
