Aeroelastic Damping Augmentation and Flutter Analysis for a High-Aspect-Ratio Wing Aircraft in the Transonic Flight Regime

Kurzfassung

This paper demonstrates the design and verification of an active flutter suppression controller on the DLR-F25 short/medium range aircraft configuration. The controller synthesis is based on state-space models derived from linearized frequency domain RANS data to allow transonic flow effects to be captured. The post-synthesis verification of the controller is performed via time-accurate, coupled CFD-CSM simulations with the controller integrated in the simulation environment to command control surface deflections at each time step. In a first step, flutter computations based on linearized frequency domain RANS data are carried out to identify the critical flutter points to be mitigated. These analyses are supported by coupled time domain computations that confirm the identified flutter points. Finally, flutter computations integrating the action of the controller and coupled time domain computations in closed loop are conducted. Both closed loop investigations show that the controller is able to effectively suppress the investigated flutter points.