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Design and sizing of an aeroelastic composite model for a flying wing configuration with maneuver, gust, and landing loads

Bramsiepe, Kjell and Voß, Arne and Klimmek, Thomas (2020) Design and sizing of an aeroelastic composite model for a flying wing configuration with maneuver, gust, and landing loads. CEAS Aeronautical Journal. Springer. doi: 10.1007/s13272-020-00446-x. ISSN 1869-5590.

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Official URL: http://dx.doi.org/10.1007/s13272-020-00446-x


The paper addresses the application of a parametric design process for a flying wing configuration. The multi-disciplinary configuration (MULDICON) is a generic unmanned combat air vehicle (UCAV) developed for research purposes, a further development of the DLR-F19 configuration, which was used for research activities in the scope of the DLR project Mephisto and its predecessors FaUSST and UCAV2010. For the MULDICON, the DLR parametric design process MONA is applied. Special emphasis is placed on the structural modeling with composite material where each layer is modeled and analyzed. Various failure criteria are compared to define suitable constraints for the optimization of the load carrying structure. In contrast to optimize the thickness of composites with global allowable strains, such strategy allows for a detailed analysis of every layer. The number of constraints due to the set-up of every ply is substantially increased compared to the strain allowables but the structural optimization is still applicable. The detailed structural and mass models represent the global stiffness and structural dynamic characteristics of the aircraft. For the loads analysis part of the design process, 9 different mass configurations with a total of 306 maneuvering load cases as well as 336 1-cos gust load cases are taken into account. Furthermore, a new simplified landing impact simulation is introduced to consider 12 landing load cases. All load cases are defined according to regulations like CS-25. Such number of load cases is necessary to cover a sufficient number of flight conditions. For the selection of the design loads for the structural optimization, the essential loads are analyzed for a subset of locations. Together with a parametrized optimization model, the structural optimization is conducted. The result is a weight-optimized structural model for the MULDICON. This entire model allows for the investigation of physics-based effects already at an early stage of the design process.

Item URL in elib:https://elib.dlr.de/134663/
Document Type:Article
Title:Design and sizing of an aeroelastic composite model for a flying wing configuration with maneuver, gust, and landing loads
AuthorsInstitution or Email of AuthorsAuthor's ORCID iD
Bramsiepe, KjellKjell.Bramsiepe (at) dlr.deUNSPECIFIED
Voß, ArneArne.Voss (at) dlr.dehttps://orcid.org/0000-0003-2266-7853
Klimmek, ThomasThomas.Klimmek (at) dlr.deUNSPECIFIED
Date:6 March 2020
Journal or Publication Title:CEAS Aeronautical Journal
Refereed publication:Yes
Open Access:Yes
Gold Open Access:No
In ISI Web of Science:No
Keywords:aeroelastic modeling, composite, structural optimization, maneuvering loads, gust loads, landing loads, flying wing, UCAV
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: Göttingen
Institutes and Institutions:Institute of Aeroelasticity > Loads Analysis and Aeroelastic Design
Deposited By: Bramsiepe, Kjell
Deposited On:22 Apr 2020 11:48
Last Modified:22 Apr 2020 11:48

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