Open-Source Benchmark Model for Active Flutter Suppression

This paper presents a benchmark model for the analysis and active control of bending-torsion flutter in a flexible wing structure. The structural dynamics of a rectangular wing are modeled using a finite element (FE) beam formulation. Aerodynamic loads are computed using the planar Doublet Lattice Method (DLM), a frequency-domain linearized potential flow approach. To enable control design, the DLM results are converted to the time-domain using rational function approximation (RFA) based on Roger’s method. The structural and aerodynamic models are consistently coupled, forming an aeroservoelastic plant that is controlled via distributed trailing edge flaps as well as leading edge slats. The plant is observed through distributed IMUs that measure accelerations perpendicular to the wing surface. A thorough modal analysis of the coupled system is performed, revealing the evolution of the critical aeroelastic eigenmodes with increasing freestream velocity and their velocity-dependent modal observability and controllability. The accompanying open-source MATLAB/Simulink implementation provides a practical foundation for benchmarking aeroservoelastic control strategies.