Research Progress on the Application of Aerodynamic Topology in New Conceptual Configuration Design of Aircraft

doi:10.12382/bgxb.2025.0104

Abstract

Abstract:

Aircraft aerodynamic configuration design has long adhered to an experience-driven design philosophy,where the aerodynamic performance of the baseline shape often determines and limits the performance improvements achievable through shape optimization.This traditional design approach is incapable of yielding disruptive aerodynamic configurations.In recent years,with the emergence of aerodynamic topology design concepts,aerodynamic topology optimization methods have gained attention and are expected to be applied to the design of novel aircraft aerodynamic configurations.Focusing on aerodynamic topology optimization methods,this paper reviews their development in terms of topology representation methods and optimization algorithms,and analyzes typical application cases of existing methods in the design of novel aircraft aerodynamic configurations.First,the historical development of aerodynamic topology optimization methods is outlined.Second,recent advances in the application of aerodynamic topology to novel aircraft configuration design are summarized.Subsequently,the challenges and difficulties faced by aerodynamic topology optimization methods are discussed,including difficulties in handling high-speed compressible turbulent flows and insufficient smoothness at fluid-solid interfaces in aircraft flow topology.Finally,future research directions in this field are prospected.

Key words: aircraft, aerodynamic configuration design, multidisciplinary optimization design, aerodynamic topology, new conceptual configuration

CLC Number:

TJ301

LIAO Peng, LIU Chuanzhen, YANG Jinguang, ZHANG Yudong, BAI Peng. Research Progress on the Application of Aerodynamic Topology in New Conceptual Configuration Design of Aircraft[J]. Acta Armamentarii, 2025, 46(11): 250104-.

Figures/Tables 21

Fig.1 Progress in the design of commercial airplanes[1]

Fig.2 Unconventional aircraft aerodynamic configuration[1]

Table 1 The main development process of international aerodynamic topology optimization methods

年份	作者	所属国家	主要工作
2003	Borrvall等^[41]	瑞典	首次将拓扑优化方法引入流体力学领域
2007	Othmer等^[42]	德国	首次将连续伴随方法与拓扑优化设计结合,并应用于进排气管设计
2014	Romero等^[43]	巴西	提出了基于旋转坐标系的叶轮转子拓扑优化设计方法
2018	Dilgen等^[44]	丹麦	分别针对两个方程植入与渗透系数有关的源项,并重点介绍了自动微分求灵敏度
2020	Yoon^[45]	韩国	在COMSOL中针对k-epsilon两方程模型添加源项
2021	Sá等^[46]	巴西	系统性地提出了基于密度法的亚音速可压缩流体拓扑优化方法框架
2023	Maffei等^[47]	巴西	解决了基于密度法的可压缩流体拓扑优化方法中流固边界清晰表征问题
2024	Feppon^[48]	比利时	基于渐近均匀化技术发展了面向流体微通道的多尺度拓扑优化方法

Fig.3 Airfoil topology configuration[49]

Fig.4 Airfoil topology configuration[51]

Fig.5 Flow mechanism[51]

Fig.6 RSVS parameterization method[52]

Fig.7 RSVS parameterization method[52]

Fig.8 Iterative process[52]

Fig.9 Comparison of pressure distribution on airfoils[53]

Fig.10 Optimal shape under two volume constraints[54]

Fig.11 Definition of design variables[55]

Fig.12 Comparison of pressure distributions around representative airfoil configurations at an AoA of 2°[55]

Fig.13 3D wing designs using representative airfoil configurations[55]

Fig.14 3D level set functions and 2D structural boundary[55]

Fig.15 3D level set functions and 2D structural boundary[56]

Fig.16 Samples with different topological structures[56]

Fig.17 Pareto optimal solution topology shape(the left is the front view,and the right is the cross sectional view)[57]

Fig.18 The pressure distribution of the topology with the highest lift to drag ratio[57]

Fig.19 Process of converting image to quadtree structure[58]

Fig.20 Sample solutions and their shapes[58]

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