Effects of stability margin and thrust specific fuel consumption constrains on multi-disciplinary optimization for blended-wing-body design

Zhou, Minghui; Chen, Zhenli; Tan, Zhiying; Gu, Wenting; Dong, Liqun; Chang-sheng, Yuan; Zhang, Binqian

doi:10.1016/j.cja.2019.05.018

Cited by 14 publications

(7 citation statements)

References 16 publications

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“…The manta ray biomimetic glider in the present paper is actually a Blended-Wing-Body (BWB) configuration, which is a revolutionary concept for commercial transports and a potential option for future civil aircraft and underwater glider (UG) [ 24 ]. Different from the traditional underwater vehicle, the BWB underwater glider merges the traditional fuselage and wing structure into a shape similar to a flying wing, which is able to glide through the water by controlling their buoyancy and converting the lift on wings into propulsive force without a power propulsion system [ 25 ].…”

Section: Resultsmentioning

confidence: 99%

A study on the hydrodynamic performance of manta ray biomimetic glider under unconstrained six-DOF motion

2020

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A manta ray biomimetic glider is designed and studied with both laboratory experiments and numerical simulations with a new dynamic update method called the motion-based zonal mesh update method (MBZMU method) to reveal its hydrodynamic performance. Regarding the experimental study, an ejection gliding experiment is conducted for qualitative verification, and a hydrostatic free-fall experiment is conducted to quantitatively verify the reliability of the corresponding numerical simulation. Regarding the numerical simulation, to reduce the trend of nose-up movement and to obtain a long lasting and stable gliding motion, a series of cases with the center of mass offset forward by different distances and different initial angles of attack have been calculated. The results show that the glider will show the optimal gliding performance when the center of mass is 20mm in front of the center of geometry and the initial attack angle range lies between A0 = -5° to A0 = -2.5° at the same time. The optimal gliding distance can reach six times its body length under these circumstances. Furthermore, the stability of the glider is explained from the perspective of Blended-Wing-Body (BWB) configuration.

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Section: Resultsmentioning

confidence: 99%

A study on the hydrodynamic performance of manta ray biomimetic glider under unconstrained six-DOF motion

2020

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“…It is slightly lower for the BWB, which has good aerodynamic efficiency [27]. Therefore, the SWB aerodynamic design needs to be improved [28].…”

Section: Improvement Of Swb Aerodynamic Designmentioning

confidence: 99%

Design Improvement of a BWB Aerodynamic Performance at Cruise and Take-Off Speeds

Duan

2022

International Journal of Aerospace Engineering

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As a high-performance aircraft, BWB (blended wing body) has attracted the attention of many countries around the world. A 300-seat BWB design is proposed by the Airplane Concept Design Institute of Northwestern Polytechnical University, which is also called SWB. The aerodynamic performance of it is evaluated by CFD (computational fluid dynamics). The CFD calculation method is based on RANS (Reynolds-averaged Navier–Stokes), and it is verified by wind tunnel test results at take-off speed. However, the aerodynamic design of the SWB needs to be improved to meet the market demand to increase its cruise Mach number from 0.8 to 0.85. To achieve this goal, firstly, based on the previous calculation and analysis results, the basic shape of SWB is improved by using “aft-body extending” technology and discrete adjoint optimization method. Then, the winglets are applied to the improved basic shape to improve its cruise speed aerodynamic performance, and the Krueger flaps are applied as its high-lift device to improve its take-off and landing aerodynamic performance. The CFD calculation and wind tunnel test results show that these improvements make SWB-2 have a good aerodynamic performance at the Mach number of 0.85. Therefore, these design improvements are appropriate and effective for improving the aerodynamic performance of BWB.

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“…Firstly, this approach has been applied in research aimed at designing various aircraft configurations. The examples range from civil transport aircraft [30][31][32], conceptual BWB configurations [1,33,34] to other unconventional aircraft [35,36] and some unmanned airplanes [37,38]. Secondly, various achievements have been made in exploring the effects of this technique on the tradeoffs or benefits in terms of aircraft design [1,33,39].…”

Section: Introductionmentioning

confidence: 99%

“…The examples range from civil transport aircraft [30][31][32], conceptual BWB configurations [1,33,34] to other unconventional aircraft [35,36] and some unmanned airplanes [37,38]. Secondly, various achievements have been made in exploring the effects of this technique on the tradeoffs or benefits in terms of aircraft design [1,33,39]. For instance, the study in [1] presented that a higher L/D could be achieved by relaxing the static stability margin.…”

Section: Introductionmentioning

confidence: 99%

“…For instance, the study in [1] presented that a higher L/D could be achieved by relaxing the static stability margin. The work in [33] discussed the relation between relaxed static stability, aerodynamic performance, and the direct operating cost (DOC) of civil aircraft. Moreover, some works connected static stability characteristics with improved aerodynamic efficiency in aerodynamic shape optimization issues, which led to the development of an effective and efficient method of studying optimal shape design under the balance between aerodynamic performance, static stability, and trim drag [34,40].…”

Section: Introductionmentioning

confidence: 99%

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Effects of Static Stability Margin on Aerodynamic Design Optimization of Truss-Braced Wing Aircraft

Qiao

et al. 2023

Aerospace

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Currently, the aviation industry is facing an oil and energy crisis and is contributing much more greenhouse gas emissions to the environment. Aircraft design approaches, such as aerodynamic shape optimization, new configuration concepts, and active control technology, have been the primary and effective means of achieving goals concerning fuel burn, noise, and emissions. For now, the design problems of relaxed static stability (RSS, an active control technique) and truss-braced wing (TBW) configurations with high-fidelity aerodynamic shape optimization methods have been investigated widely to promote aerodynamic performance. Nevertheless, they are studied almost always separately, and the combination of exploration and refined design is rarely presented. Therefore, the purposes of this work are to evaluate the benefits of RSS on a full TBW wing–body–tail configuration under various flight conditions and the effects on multi-components and to further explore the potential and analyze the aerodynamic features with the combination of shape optimization and RSS. To address these issues, on the one hand, a range of seven static stability margins are adopted to evaluate its effects with a high-fidelity Reynolds-averaged Navier–Stokes solver. On the other hand, seven cases of drag minimization multipoint aerodynamic design optimization are performed, which are with 600 shape variables and 13 twist variables, subject to lift coefficient, trim, and thickness constraints. The results indicate that with RSS only, the initial configuration has a 2.39% drag reduction under cruise conditions and a 3.01% and a 5.24% drag reduction under two off-design conditions. Additionally, the effects on the multi-components are observed and analyzed. Moreover, all of the optimized configurations with RSS have 2.13%, 2.42%, and 2.12% drag reductions under cruise conditions, drag divergence conditions, and near-buffet-onset conditions, respectively. The most promising optimized configuration has a lift-to-drag ratio of 24.48 with an aerodynamic efficiency of 17.14. The evaluations with a series of off-design points also present high-level aerodynamic efficiency.

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Effects of stability margin and thrust specific fuel consumption constrains on multi-disciplinary optimization for blended-wing-body design

Cited by 14 publications

References 16 publications

A study on the hydrodynamic performance of manta ray biomimetic glider under unconstrained six-DOF motion

A study on the hydrodynamic performance of manta ray biomimetic glider under unconstrained six-DOF motion

Design Improvement of a BWB Aerodynamic Performance at Cruise and Take-Off Speeds

Effects of Static Stability Margin on Aerodynamic Design Optimization of Truss-Braced Wing Aircraft

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