A UCAV Wing Design, Assessment and Comparisons.

Nangia, R. K.; Coppin, Joe; Ghoreyshi, Mehdi

doi:10.2514/6.2018-2842

Cited by 17 publications

(9 citation statements)

References 8 publications

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“…The aerodynamic performances of baseline and the ASG Design2 wings were detailed and compared in Ref. [2]. The study concluded that the Design2 wing indicates an improvement in sustained turn performance and is a considerable improvement over the baseline wing.…”

Section: Introductionmentioning

confidence: 99%

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: Introductionmentioning

confidence: 99%

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

Self Cite

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“…Liersch et al [22] provided conceptual design analyses for the SACCON configuration and compared the aerodynamic performance of the SACCON model using low-and high-fidelity approaches. A UCAV wing design and optimization process for the MULDICON UCAV is presented by Nangia et al [23]. A contribution to aerodynamic design includes the effect of airfoil shape, LE geometry, engine integration, and the vortex flow at various angles of attack (AOA) on the aerodynamic characteristics of a 53 deg swept UCAV configuration by Schütte et al [24].…”

Section: Saccon Muldiconmentioning

confidence: 99%

“…Most of the UCAV conceptual designs available in the literature [7][8][9][10][11][12][13][14][15][16][17][18][19][20][21][22][23][24][25] are tailless flying wing configurations with a low to moderate aspect ratio (AR), internal weapon carriage, concealed propulsion systems, absence of high lift devices, and moderate to high leading-edge (LE) sweep angle edge-aligned wings (40 ≤ Λ ≤ 60 deg) [8,9]. However, the design of UCAV configurations is a complex task because it requires a high level of integration within the subsystems combined with vorticial flow structures.…”

Section: Introductionmentioning

confidence: 99%

Conceptual Configuration of Non-Constant Sweep UCAV Concept

Aleisa

Kontis

Nikbay

et al. 2022

AIAA AVIATION 2022 Forum

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The design of unmanned combat aerial vehicles (UCAVs) used for military applications is dictated by their low-observability characteristics rather than the aerodynamic performance. Owing to this reason, the UCAVs experience flow separation during takeoff and landing and exhibit stability issues. Moreover, the wing design significantly influences the aerodynamic performance of the UCAV model. The configurations of UCAV models are still under exploration, and the conceptual design of UCAV is still undergoing various developments, so the dimensions and shape of the UCAV design have not been defined yet. Hence, the assessment of the conceptual configurations and their design are worthy issues that need to be investigated. In the present work, the initial weight, aerodynamic sizing, planform selection and then the conceptual design of a non-constant leading-edge UCAV configuration was performed. Later, the obtained conceptual design was optimized using multi-fidelity surrogate models with a vortex-lattice method to achieve a better lift and drag ratio. Lastly, the optimized design was validated using the computational fluid dynamic (CFD) model to verify the accuracy of the surrogate model. It was found that the optimized design exhibited superior lift and drag characteristics compared to the reference design.

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“…Finally, the discontinuities in the pitching moment could be reduced and the maximum lift coefficient was increased. Details about this second, inverse design approach are given by Nangia et al [48]; Table 3 shows its achievements with respect to maximum lift coefficient. It can be seen that the design targets for these three points are nearly met.…”

Section: Muldicon Designmentioning

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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A UCAV Wing Design, Assessment and Comparisons.

Cited by 17 publications

References 8 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

Conceptual Configuration of Non-Constant Sweep UCAV Concept

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

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