Suppression of control reversal using leading- and trailing-edge control surfaces
Academic Article
Overview
Identity
Additional Document Info
Other
View All
Overview
abstract
Control reversal is the loss, due to the flexibility of the primary aerostructure, of aircraft maneuvering loads induced by control surfaces. In recent years, attention has been given to the suppression of reversal through the use of distributed control surfaces. The authors study reversal behavior for a wing section with full-span leading-edge and trailing-edge control surfaces. The essential equations are developed by examining static aeroelastic responses. Analysis and experiments are presented. Specific trailing-edge to leading-edge control commands are identified to optimize performance. Although reversal is not eliminated in the experiments, the addition of the leading edge is shown to improve performance substantially. The research also identifies the adverse consequences of actuator flexibility.
