Aeroelasticity & Structural Dynamics in a Fast Changing World
17 – 21 June 2024, The Hague, The Netherlands
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Wind Tunnel Testing Active Gust Load Alleviation of a Flexible Wing


Go-down ifasd2024 Tracking Number 107

Presentation:
Session: Wind tunnel testing 1
Room: Room 1.1
Session start: 13:30 Tue 18 Jun 2024

Felix Stalla   felix.stalla@dlr.de
Affifliation: German Aerospace Center (DLR), Institute of System Dynamics and Control

Thiemo M. Kier   thiemo.kier@dlr.de
Affifliation: German Aerospace Center (DLR), Institute of System Dynamics and Control

Gertjan Looye   gertjan.looye@dlr.de
Affifliation: German Aerospace Center (DLR), Institute of System Dynamics and Control

Kolja Michel   kolja.michel@dlr.de
Affifliation: German Aerospace Center (DLR), Institute of System Dynamics and Control

Thomas G. Schmidt   tg.schmidt@dlr.de
Affifliation: German Aerospace Center (DLR), Institute of Aeroelasticity

Charlotte Hanke   charlotte.hanke@dlr.de
Affifliation: German Aerospace Center (DLR), Institute of Aeroelasticity

Johannes Dillinger   johannes.dillinger@dlr.de
Affifliation: German Aerospace Center (DLR), Institute of Aeroelasticity

Markus Ritter   markus.ritter@dlr.de
Affifliation: German Aerospace Center (DLR), Institute of Aeroelasticity

Martin Tang   martin.tang@dlr.de
Affifliation: German Aerospace Center (DLR), Institute of Aeroelasticity


Topics: - Dynamic Loads (High and low fidelity (un)coupled analysis methods:), - Aeroservoelasticity (Vehicle analysis/design using model-based and data driven models), - Active Control and Adaptive Structures (Vehicle analysis/design using model-based and data driven models), - Wind Tunnel and Flight Testing (Experimental methods)

Abstract:

Increasing efficiency is at the core of next generation aircraft development. Aerodynamics can be improved by high aspect ratio wings, but as these wings are more susceptible to loads from gusts and maneuvers, structural weight might increase. Active load control enables the use of high aspect ratio wings while maintaining a relatively low structural weight. To enhance the technology readiness of such secondary flight control functions, experiments are indispensable. This paper describes the wind tunnel testing of a gust load alleviation controller on a flexible swept wing, equipped with multiple trailing edge flaps and acceleration sensors. Disturbances are injected by a gust generator located upstream of the model. The complete process leading up to the active control experiment is outlined: the simulation model used for controller development, the experimental identification of the system and updating of said model, the controller design, and the validation in the wind tunnel. µ-synthesis robust control is used, achieving the best possible performance with respect to the uncertainties in the system. The robust controller achieves a significant load reduction of up to 80% in the wind tunnel tests.