Design and aeroelastic assessment of a forward-swept wing aircraft

Krüger, Wolf R.; Klimmek, Thomas; Liepelt, René; Schmidt, Hauke; Waitz, Stefan; Cumnuantip, Sunpeth

doi:10.1007/s13272-014-0117-0

Cited by 17 publications

(13 citation statements)

References 19 publications

(17 reference statements)

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“…MONA is embedded in a conceptual design process for multidisciplinary design optimization [8]. Some example of usage are the configurations FERMAT [9], ALLEGRA [10], and DLR-F19 [2]. The MONA process in this work is using three software tools: the two in-house tools ModGen [11] and Loads Kernel [12] as well as the commercial software MSC Nastran [13].…”

Section: Parametric Modeling Loads and Design Process-monamentioning

confidence: 99%

“…However, matrix A 2 is omitted during the approximation, as suggested in [30]. The unsteady parts A 3 , A 4 , ..., A 3+n depend on the lag states 10 Top view on aerodynamic model lag a , lag 2 , ..., lag n . As the time simulation usually starts from an initial steady level flight, the lag states are assumed to be zero at the beginning.…”

Section: Aerodynamic Modelmentioning

confidence: 99%

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

2020

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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.

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Section: Parametric Modeling Loads and Design Process-monamentioning

confidence: 99%

Section: Aerodynamic Modelmentioning

confidence: 99%

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

2020

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“…For the generation of the structural wing model, the tool ModGen was used. ModGen has been specifically developed for the generation of parametric representations of structural and aeroelastic models to be used in aeroelastic analysis and optimization tasks; see for example the application on the so-called FERMAT, a structural model for the CRM configuration [22], or on a forward-swept wing aircraft [23].…”

Section: Parametric Wing Definitionmentioning

confidence: 99%

Investigations of passive wing technologies for load reduction

et al. 2019

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Wings of modern aircraft have to be designed to give optimal response with respect to loads, comfort and performance. An essential part of the wing development is thus a design process which can take all these aspects into consideration. In the "Adaptive Wing" work package of the CleanSky "Smart Fixed Wing Aircraft" project, a multi-fidelity wing design method using aeroelastic tailoring has been developed. In the article, the process is presented in detail. The approach is based on a parametric wing design approach. Both beam models and shell models are derived and optimized in separate optimization environments. Investigations of the use of unbalanced laminates in aeroelastic tailoring are presented, employing the optimization of lamination parameters. The applications are demonstrated on two aircraft configurations, a long range and a short range transport aircraft. Further developments presented in the article include the introduction of CFD-based aerodynamics in the tailoring process, and a process extension to assess the influence of aeroelastic tailoring on fatigue.

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“…While the structure is usually intended to be symmetric, both mass configuration and load condition could be asymmetric. ModGen may be used as a stand-alone tool, as part of the ModGen/Nastran design process (MONA) [16,19] or modules may be integrated in a fully automated design process [20]. The MONA process can be set up slightly differently, the principal steps used for the DLR-F19 are depicted in Fig.…”

Section: Parametric Modeling Loads and Design Processmentioning

confidence: 99%

Design and sizing of a parametric structural model for a UCAV configuration for loads and aeroelastic analysis

Voß

Klimmek

2016

CEAS Aeronaut J

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The authors present the setup of a parametric structural finite element model for the loads and aeroelastic analysis of an unmanned combat air vehicle (UCAV). The DLR-F19 is a "flying wing" configuration with a geometry based on previous research conducted in the scope of the "Mephisto" project and its predecessors "FaUSST" and "UCAV2010". While a considerable body of knowledge exists regarding conventional configurations, unconventional configurations lack that same level of experience, and data for comparison is rarely available. Using an adequate structural model, the conceptual design stage becomes more sophisticated and already allows for the investigation of physical effects at an early stage of the design process. Strategies for structural modeling and proper condensation, aero-structural coupling, loads integration, control surface attachment, and the use of composite materials are addressed in this paper. The resulting model is sized for minimum structural weight, taking into account 216 load cases. In addition, a comprehensive loads analysis campaign is conducted and the resulting loads are evaluated at defined monitoring stations. In addition to maneuver loads, quasi-static gust loads are calculated using the Pratt formula and compared to results obtained from a dynamic 1-cosine gust simulation. The reasons

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Design and aeroelastic assessment of a forward-swept wing aircraft

Cited by 17 publications

References 19 publications

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

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

Investigations of passive wing technologies for load reduction

Design and sizing of a parametric structural model for a UCAV configuration for loads and aeroelastic analysis

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