Multi-Disciplinary Design and Performance Assessment of Effective, Agile NATO Air Vehicles

Cummings, Russell M.; Liersch, Carsten M.; Schuette, Andreas

doi:10.2514/6.2018-2838

Cited by 28 publications

(16 citation statements)

References 57 publications

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“…The MULDICON planform and its geometrical dimensions are shown in Figure 1. A more detailed description of the con- figuration can be found in Cummings et al [1]. For a better comparison between the moment coefficients, all moment coefficients are normalized with the same reference length of c re f = 6m.…”

Section: Test Casesmentioning

confidence: 99%

“…The objectives of this study are related to the NATO STO AVT-251 Task Group [1], which was established to computationally design a new Multi-Disciplinary configuration, named MULDICON from previous NATO Task Group experiences to meet a set of desired mission requirements. The design of MULDICON needs to achieve satisfactory performance and handling characteristics and therefore should engage all participants in a collaborative effort.…”

Section: Introductionmentioning

confidence: 99%

“…Email addresses: patrick.loechert@dlr.de (Patrick Löchert), kerstin.huber@dnw.aero (Kerstin C. Huber), mehdi.ghoreyshi@usafa.edu (Mehdi Ghoreyshi), jallen12000@gmail.com (Jacob Allen) 1 Corresponding Author.…”

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confidence: 99%

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Control device effectiveness studies of a 53∘ swept flying wing configuration. Experimental, computational, and modeling considerations

Löchert

Huber²,

Ghoreyshi

et al. 2019

Aerospace Science and Technology

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The present investigation covers studies of different control devices on several 53 • swept flying wing configurations without a vertical tail plane. The wings considered share the same planform but differ in their spanwise profile shapes. The planform, developed under the NATO AVT-251 Task Group, is referred to as the MULDICON (or MULtiDIsciplinary CONfiguration). The objectives of this article are twofold: (1) to design yaw control surfaces for the MULDICON wing using an experimental/computational approach and (2) to develop aerodynamic models that rapidly and accurately predict the effectiveness of control surfaces over a wide range of flight conditions. The yaw control surface design (position and size) should provide sufficient yaw moment with almost no contribution in roll and pitch moment. To identify such concepts, a number of preliminary experiments on a generic flying wing configuration have been conducted. Two promising concepts from wind tunnel tests were then numerically examined for being implemented in the MULDICON baseline wing. Concepts with spoilers and a split flap were specifically considered. For medium to high angles of attack, the flow topology of the baseline wing is dominated by a vortical flow field on the upper outer wing. This leads to interactions between vortex and the control device which influences the flow and the attitude of the control device on the upper wing side. Furthermore, this work considers developing aerodynamic models for predicting stability derivatives of several MULDICON designs over a wide range of flight conditions. Aerodynamic loads models are only developed for normal force and pitch moment coefficients, however, the developed approach can easily being extended to include lateral aerodynamic coefficients as well. Quasi-steady models of this work are power series expansions of traditional linear aerodynamic models to capture nonlinear effects. Additionally, the models can estimate static and dynamic stability derivatives and the control surface powers.

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Section: Test Casesmentioning

confidence: 99%

Section: Introductionmentioning

confidence: 99%

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Control device effectiveness studies of a 53∘ swept flying wing configuration. Experimental, computational, and modeling considerations

Löchert

Huber²,

Ghoreyshi

et al. 2019

Aerospace Science and Technology

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“…We designed the MULDICON configuration in close cooperation with the NATO STO task group AVT-251 on "Multi-Disciplinary design and performance assessment of effective, agile NATO Air Vehicles" [14]. It was a rather special design task, as the outer shape of MULDICON (a slightly modified SACCON shape) was already fixed in the beginning and the design task was purely to integrate an aircraft into that shape.…”

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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“…This article is focused on the design of the MULDICON configuration, which was performed in close cooperation with the NATO STO task group AVT-251 on "Multi-Disciplinary design and performance assessment of effective, agile NATO Air Vehicles" [2]. It belongs to a series of Mephisto-based publications, covering various aspects of the SACCON redesign task.…”

Section: Introductionmentioning

confidence: 99%

Design studies and multi-disciplinary assessment of agile and highly swept flying wing configurations

Liersch¹,

Schütte²,

Siggel

et al. 2020

CEAS Aeronaut J

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This article belongs to a series of publications on the design and assessment of the MULDICON UCAV configuration. MULDICON is a 53° swept flying wing combat aircraft concept, investigated in a common effort between the DLR research project Mephisto and the NATO STO Research Task Group AVT-251. This article focuses on the development of the overall concept starting from its predecessor, the SACCON configuration, and the requirements which had been defined for the MULDICON design task. A second focus is placed on the investigation of the vortex-dominated flow topology arising around such a configuration and its sensitivity to specific geometric changes. Furthermore, the article briefly introduces the DLR conceptual aircraft design system and the extensions which have been developed for improving its capabilities for UCAV assessment. Finally, an industrial view on the MULDICON design task is provided, as well as a conclusion of the Mephisto results and an outlook upon further work.

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Multi-Disciplinary Design and Performance Assessment of Effective, Agile NATO Air Vehicles

Cited by 28 publications

References 57 publications

Control device effectiveness studies of a 53∘ swept flying wing configuration. Experimental, computational, and modeling considerations

Control device effectiveness studies of a 53∘ swept flying wing configuration. Experimental, computational, and modeling considerations

Distributed Multidisciplinary Optimization and Collaborative Process Development Using RCE

Design studies and multi-disciplinary assessment of agile and highly swept flying wing configurations

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