Optimization of Flexible Wing Without Ailerons for Rolling Maneuver

Abstract

An optimum flexible wing structure with enhanced roll maneuver capability at high dynamic pressures is designed. A flexible wing optimized for weight with constraints on strength for 9-g symmetric pull-up maneuver at M=0.85 and constraints on the frequency distribution were used. Elastic twist and camber are achieved by providing a system of actuating elements distributed within the internal substructure of the wing to provide control forces. The modal approach was used to develop equilibrium equations for the steady roll maneuver of a wing subjected to acrodynamic loads and actuating forces. The distribution of actuating forces to achieve a specified flexible roll rate was determined by using an optimal control design approach. Here, a full-scale realistic wing was considered for the assessment of strain energy as a measure of the necessary power required to produce the antisymmetric twist and camber deformation to achieve the required roll performance