TY - GEN
T1 - Aircraft aeroservoelastic modelling of the flexop unmanned flying demonstrator
AU - Meddaikar, Yasser M.
AU - Dillinger, Johannes K.S.
AU - Klimmek, Thomas
AU - Krüger, Wolf R.
AU - Wüstenhagen, Matthias
AU - Kier, Thiemo
AU - Hermanutz, Andreas
AU - Hornung, Mirko
AU - Rozov, Vladyslav
AU - Breitsamter, Christian
AU - Alderman, James
AU - Takarics, Béla
AU - Vanek, Bálint
N1 - Publisher Copyright:
� 2019 by German Aerospace Center (DLR). Published by the American Institute of Aeronautics and Astronautics, Inc.
PY - 2019
Y1 - 2019
N2 - This paper presents the aeroservoelastic modelling toolchain established for the aircraft design exercise within the European research project, FLEXOP. The FLEXOP project aims to develop and apply active flutter suppression and load alleviation techniques on an unmanned flying demonstrator. The developed methods are then to be applied in the design of a commercial-scale wing derivative in a scale-up task. A high-fidelity finite element (FE) structural model is the first block in the modelling process. A condensed FE model together with aerodynamic models based on the doublet-lattice (DLM) and vortex-lattice (VLM) methods represent the aeroelastic system. The aerodynamics represented by the afore-mentioned panel methods is complemented by results from higher-fidelity computational fluid dynamics (CFD) simulations. Reduced-order aeroservoelastic models suitable for control-synthesis are then generated using a “bottom-up” modelling approach. The aim of the paper is to present an overview of the different models encountered during such a design process and their domains of application.
AB - This paper presents the aeroservoelastic modelling toolchain established for the aircraft design exercise within the European research project, FLEXOP. The FLEXOP project aims to develop and apply active flutter suppression and load alleviation techniques on an unmanned flying demonstrator. The developed methods are then to be applied in the design of a commercial-scale wing derivative in a scale-up task. A high-fidelity finite element (FE) structural model is the first block in the modelling process. A condensed FE model together with aerodynamic models based on the doublet-lattice (DLM) and vortex-lattice (VLM) methods represent the aeroelastic system. The aerodynamics represented by the afore-mentioned panel methods is complemented by results from higher-fidelity computational fluid dynamics (CFD) simulations. Reduced-order aeroservoelastic models suitable for control-synthesis are then generated using a “bottom-up” modelling approach. The aim of the paper is to present an overview of the different models encountered during such a design process and their domains of application.
UR - http://www.scopus.com/inward/record.url?scp=85083944090&partnerID=8YFLogxK
U2 - 10.2514/6.2019-1815
DO - 10.2514/6.2019-1815
M3 - Conference contribution
AN - SCOPUS:85083944090
SN - 9781624105784
T3 - AIAA Scitech 2019 Forum
BT - AIAA Scitech 2019 Forum
PB - American Institute of Aeronautics and Astronautics Inc, AIAA
T2 - AIAA Scitech Forum, 2019
Y2 - 7 January 2019 through 11 January 2019
ER -