An innovative route from wind tunnel experiments to flight dynamics analysis for a highly swept flying wing

Schwithal, Jana; Rohlf, D.; Looye, Gertjan; Liersch, Carsten M.

doi:10.1007/s13272-016-0214-3

Cited by 19 publications

(13 citation statements)

References 15 publications

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“…The third step ("Post analysis", marked in green) consists of different analysis tools, further investigating the properties of the aircraft. On the left side of the workflow, there is "HAREM", a DLR analysis tool for investigating and evaluating the handling qualities of an aircraft [21,22,23]. In this branch, the flightSim tool is used again, but this time it creates a 6 degree of freedom dynamic aircraft model which is handed over to HAREM.…”

Section: Fig 8 Overview Of Parameter Variations Performed For the Smentioning

confidence: 99%

Distributed Multidisciplinary Optimization and Collaborative Process Development Using RCE

Boden

Flink

Mischke

et al. 2019

AIAA Aviation 2019 Forum

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DLR's Remote Component Environment (RCE) is an open-source software environment for defining and executing workflows containing distributed simulation tools by integrating them into a peer-to-peer network. It is being developed primarily by DLR and has been used in various engineering projects, including several aerospace projects dealing with multidisciplinary optimization (MDO) and multidisciplinary analysis (MDA). RCE has several advantages that can help to achieve more reusable multidisciplinary processes. The workflow is composed of built-in and user-defined components. Disciplinary tools are integrated as standalone components, with defined inputs and outputs, and then distributed over the network. While executing the workflow, data dependencies between the components are automatically detected, and a component is executed as soon as all its input data is available. Thus, multiple components can run at the same time. The components of a multidisciplinary process can also be executed in a distributed manner, where the tools are located on different machines with possibly different operating systems. Once configured, the peer-to-peer network is automatically established between the RCE instances running on different machines, making components visible and executable even between instances that are only connected indirectly. The distributed execution capability alleviates tool deployment issues, including those related to the protection of intellectual property. RCE supplies a graphical editor for creation of workflows, using the built-in components to control the data flow. Some built-in components can be used to perform optimization tasks within the workflow, including nested loops, using built-in or user integrated optimization algorithms. We demonstrate the use of some of the key features of RCE for MDA and MDO purposes based on several collaborative DLR projects where distributed simulation tools are being used.

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Section: Fig 8 Overview Of Parameter Variations Performed For the Smentioning

confidence: 99%

Distributed Multidisciplinary Optimization and Collaborative Process Development Using RCE

Boden

Flink

Mischke

et al. 2019

AIAA Aviation 2019 Forum

View full text Add to dashboard Cite

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“…When the iteration finally has converged, a subsequent analysis process is started: In this case, the flight Simulation tool is used again, but this time it creates a dynamic aircraft model which is handed over to the ''HAREM'' tool. HAREM is an analysis tool for investigating and evaluating the handling qualities of an aircraft [14,36,37].…”

Section: Design Processmentioning

confidence: 99%

“…Signature investigations are presented in the articles by Lindermeir [12] and Kemptner [13]. Finally, the papers by Schwithal et al [14] and Kuchar et al [15] are dealing with flight mechanics assessment and controller development.…”

Section: Introductionmentioning

confidence: 99%

Multidisciplinary design and aerodynamic assessment of an agile and highly swept aircraft configuration

Liersch

Huber²,

Schütte

et al. 2016

CEAS Aeronaut J

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The characteristics of highly swept aircraft configurations have been studied in a series of consecutive research projects in DLR for more than 15 years. Currently, the investigations focus on the generic SACCON UCAV configuration, which was specified in a common effort together with the NATO STO/AVT-161 task group. This paper is the first one in a series of articles presenting the SACCON-related research work within DLR. First, the article describes the conceptual design studies being performed for this aircraft configuration. At this point the question is raised, whether the simple aerodynamic methods used within conceptual design can be applied to such type of aircraft configurations with sufficient accuracy. Thus, the second part of this article provides a comparison of the aerodynamic characteristics of the SACCON configuration predicted by low-and high-fidelity aerodynamic methods, as well as some results from wind tunnel experiments. Keywords Conceptual aircraft design Á Multi-fidelity Á Highly swept aircraft configurations Á SACCON Á UCAV aerodynamics Abbreviations C A Axial force coefficient [-] C D Drag force coefficient [-] C L Lift force coefficient [-] C N Normal force coefficient [-] C S Body-fixed side force coefficient [-] C Y Side force coefficient [-] C l Rolling moment coefficient [-] C m Pitching moment coefficient [-] C mx Body-fixed X-moment coefficient [-] C my Body-fixed Y-moment coefficient [-] C mz Body-fixed Z-moment coefficient [-] C n Yawing moment coefficient [-] I xx Mass moment of inertia (X-axis) [kg m 2 ] I yy Mass moment of inertia (Y-axis) [kg m 2 ] I zz Mass moment of inertia (Z-axis) [kg m 2 ] V

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“…Weak instabilities were observed in some of the flight modes, especially in the sideslip condition, which could be easily controlled by the control effectors. Besides the conventional linear evaluation methods [9], a novel approach of identifying the aerodynamic model from innovative wind tunnel maneuvers was employed for the tailless DLR-F19 configuration [10], [11]. The resulting aerodynamic model was able to capture the highly nonlinear aerodynamic effects and could directly be integrated into the flight dynamics model, which exhibited Dutch-roll mode corresponding to flying qualities worse than level 3.…”

Section: Introductionmentioning

confidence: 99%

An Innovative Experimental Approach to Lateral-Directional Flying Quality Investigation for Tailless Aircraft

Nie¹,

Liu²,

Cen³

et al. 2020

IEEE Access

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Tailless aircraft suffers from limited yaw control power and poor directional stability inherently. To address these issues in the early design process of a tailless configuration with low costs and risks, this paper presents an innovative experimental approach to control law validation and quantitative flying quality evaluation with a dynamically scaled model mounted on a three degree-of-freedom rig in the wind tunnel. The motion equations of the tailless demonstrator on the rig are derived, and then the comparisons of the lateral-directional flight dynamics between the rig constrained model and the free flight model are carried out. Construction of the control augmentation system for yaw and roll motion is accomplished according to the scale modified criteria of flying qualities. Effectiveness of the designed control law is demonstrated with steady pilot-in-the-loop flights at different airspeeds and angles of attack. The achieved closed-loop flying qualities are evaluated by applying multistep maneuvers for low order equivalent system identification. Whereas severe instability is observed in yaw for the open-loop case, the closed-loop flying quality of the Dutch-roll mode can be improved to level 1 at low angle of attack.

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An innovative route from wind tunnel experiments to flight dynamics analysis for a highly swept flying wing

Cited by 19 publications

References 15 publications

Distributed Multidisciplinary Optimization and Collaborative Process Development Using RCE

Distributed Multidisciplinary Optimization and Collaborative Process Development Using RCE

Multidisciplinary design and aerodynamic assessment of an agile and highly swept aircraft configuration

An Innovative Experimental Approach to Lateral-Directional Flying Quality Investigation for Tailless Aircraft

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