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Aeroservoelastic Wing Sizing Using a Physics-Based Approach in Conceptual Aircraft Design

Krengel, Markus Dino and Hepperle, Martin and Hübner, Andreas-René (2019) Aeroservoelastic Wing Sizing Using a Physics-Based Approach in Conceptual Aircraft Design. AIAA Aviation 2019 Forum, 17.-21. Juni 2019, Dallas, USA. doi: 10.2514/6.2019-3368.

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Official URL: https://arc.aiaa.org/doi/10.2514/6.2019-3368


State of the art wing sizing in conceptual aircraft design is usually carried out by semiempirical methods, or with static load cases and a rigid airframe structure. On the other hand, combining the disciplines aerodynamics, structures and flight dynamics catches the impact of dynamic aircraft behavior on the mass of the flexible wing. By taking coupled physics effects into account at the early design stage, technologies like gust and maneuver load alleviation can be assessed. Overall aircraft efficiency benefits are expected. This paper presents a process for the integration of flight control and aeroelasticity into conceptual aircraft design. The main goal is an expansion of the wing design by introducing mission based dynamic load cases performed with a flexible structure. The process uses the tool ASWING§ to perform an unsteady lifting line calculation combined with non-linear Euler beam theory. Structural wing sizing is performed on a long range transport aircraft design. Elements of an open source simulation library are used to perform a controlled six-degree-of-freedom flight simulation. The sizing process is calibrated with the properties of a higher fidelity structure model, based on steady load cases. A dynamic validation of the lower fidelity behavior is provided by a higher fidelity approach, using unsteady Reynolds-Averaged Navier-Stokes equations coupled with a structural modal ansatz in a free flight simulation. It is shown, that the conceptual sizing process captures the maximum loads and dominant dynamic effects. Therefore it is qualified for usage in conceptual aircraft design. Deviations are traced back to configuration differences between the models and fundamental differences of the modeling approach. The presented process enables the assessment of how specific flight control laws and layouts change the optimum aircraft design.

Item URL in elib:https://elib.dlr.de/128357/
Document Type:Conference or Workshop Item (Speech)
Title:Aeroservoelastic Wing Sizing Using a Physics-Based Approach in Conceptual Aircraft Design
AuthorsInstitution or Email of AuthorsAuthor's ORCID iDORCID Put Code
Krengel, Markus DinoUNSPECIFIEDhttps://orcid.org/0000-0002-2082-7051138444910
Date:17 June 2019
Refereed publication:Yes
Open Access:No
Gold Open Access:No
In ISI Web of Science:No
Page Range:pp. 3368-3391
Keywords:Aircraft Design, Control Laws, Elastic, Wing Sizing
Event Title:AIAA Aviation 2019 Forum
Event Location:Dallas, USA
Event Type:international Conference
Event Dates:17.-21. Juni 2019
Organizer:AIAA - American Institute of Aeronautics and Astronautics
HGF - Research field:Aeronautics, Space and Transport
HGF - Program:Aeronautics
HGF - Program Themes:fixed-wing aircraft
DLR - Research area:Aeronautics
DLR - Program:L AR - Aircraft Research
DLR - Research theme (Project):L - Flight Physics (old)
Location: Braunschweig
Institutes and Institutions:Institute for Aerodynamics and Flow Technology > Transport Aircraft
Deposited By: Krengel, Markus Dino
Deposited On:23 Oct 2019 14:18
Last Modified:11 Jul 2023 10:50

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