Multiple Control Surface Utilization in Active Aeroelastic Wing Technology

Abstract

This study investigates the use of multiple control surfaces to effect roll trim of aircraft. Analytic models of a rectangular wing and a e ghter aircraft are used as examples for steady aeroelastic and antisymmetric trim analyses. The e nite element method is used to calculate structural deformations caused by steady aerodynamic input forces, which are generated by a linear panel method. Values of control surface effectiveness, calculated from the e exible rolling moment stability derivatives, are used to determine which control surfaces are most effective in achieving a desired roll maneuver. The roll trim equation of motion is solved for multiple control surface dee ections using an iterative technique that minimizes the control effort to achieve a specie ed roll rate. Roll trim utilizing multiple control surfaces, including leading-edge surfaces, is examined over a range of dynamic pressures. Aircraft models with reduced wing stiffness are investigated to determine if roll performance requirements can be achieved through the use of multiple control surfaces. The results of utilizing multiple control surfaces on e exible wings are examined to determine if weight savings can be achieved while maintaining a desired level of roll performance.