Parametric Modelling of High Lift Systems - Simulation And Validation of Dynamic Operational Loads


Flugdynamik und Lasten





Art der Publikation:



Michael Neumann, F. Thielecke


Deutscher Luft- und Raumfahrtkongress, Bremen 27. - 29. Sept. 2011

As a result of the development of larger and more efficient aircrafts the need for optimization of high-lift systems increases significantly. In contrast to this, the increasingly shorter development and testing time makes it necessary to optimize the design process in prediction accuracy due to static and dynamic loads. Generally, the design and dimensioning of high-lift systems are mainly affected by failure cases. Albeit, operational load cases, like a landing gear impact, can have dimensioning effect, too. Hence, these effects have to be investigated and considered. In this specific case, the local dynamic loads and acceleration of the flap system are significantly affected by the structural behavior of the component chain landing gear, fuselage, wing, wing-flap-interface, flap support and the flaps themselves. The dynamic response behavior of the flaps is particularly nonlinear due to bearing friction and backlash and bracings within the wing-flap-interface. In order to investigate the dynamic effects on the flap system in the early stages of design, as well as attendant to the certification process, the Institute of Aircraft Systems Engineering in collaboration with the Airbus Deutschland GmbH developed a tool chain for generic modeling of multi-body structures for the simulation environment MSC.Adams. The degree of abstraction of the individual subsystems and their components can, according to the existing data, models and the required accuracy, simply and quickly be adapted. Hence, parameter studies and uncertainty analysis are simply realizable. Similarly, it is possible and necessary to implement boundary conditions like air or ground loads in order to investigate specified load cases. Using the developed techniques, simulations for a large civil aircraft were done and validated successfully on the basis of real flight test data. Therefore, the main task of future work is the advancement of generic model building and the prediction of loads and accelerations working at the flap system as a result of ground loads.