The major part of the activities of the group “Aeroelastic Stability and System Response” is concerned with the aeroelasticity of civil and military
transport aircraft. However, small business aircraft and glider planes are also subject of investigation. Finally, the work includes contributions to the analysis of helicopters and tiltrotor aircraft.
The covered area comprises numerical analyses and the prediction of static and dynamic aeroelastic phenomena for air transport vehicles. The focus is always on the complete configuration; unconventional aircraft concepts are also investigated. The group cooperates closely with all other groups of the institute, in the field of numerical methods, as well as for experimental investigations, namely structural dynamics and wind tunnel testing.
For fixed wing aircraft, the area of activities ranges from flutter analyses of glider airplanes to numerical investigations of the stability of transport aircraft in transonic flow. The investigations are also based on experimental data, where available. Numerical approaches include the spatial and temporal coupling of fluid and structure, and the time exact solution based in CFD calculations. However, fast frequency domain approaches are heavily used for stability analyses and their application further developed.
Similar approached are used for the analysis of rotary wing aircraft, where the complex dynamic interaction of rotor and fuselage is the dominating subject of investigation. Focus of work is the improvement of the aeroelastic modelling of modern rotor blades and the rotor head as well as of dynamic rotor loads.
The methods for aeroelastic investigation are used in a number of DLR internal projects, as well as in several multidisciplinary national and EU projects.