Volume 39 Issue 4
Apr.  2024
Turn off MathJax
Article Contents
YANG Yucheng, SU Hua, GONG Chunlin, et al. Analytical aero-structural modeling and optimization method of three-dimensional wing based on CST[J]. Journal of Aerospace Power, 2024, 39(4):20220289 doi: 10.13224/j.cnki.jasp.20220289
Citation: YANG Yucheng, SU Hua, GONG Chunlin, et al. Analytical aero-structural modeling and optimization method of three-dimensional wing based on CST[J]. Journal of Aerospace Power, 2024, 39(4):20220289 doi: 10.13224/j.cnki.jasp.20220289

Analytical aero-structural modeling and optimization method of three-dimensional wing based on CST

doi: 10.13224/j.cnki.jasp.20220289
  • Received Date: 2022-04-30
    Available Online: 2023-11-04
  • To facilitate the large-scale exploration of design space and the design of aero-structural integration in the conceptual design stage, a three-dimensional parametric modeling and optimization method for wing aero-structural analysis was proposed by using the class-shape function transformation (CST) method. Based on the two-dimensional CST, the analytical function form of the three-dimensional CST parametric geometric model was deduced. Established by using the mesh adaptive discrete and structural feature extraction technology, the aero-structural analysis parametric model of the three-dimensional wing can support the rapid modeling and optimization of the aerodynamic structure integration simultaneously, including parameters of the wing geometry configuration, structural layout, structural size, material properties, etc. Besides, it can automate the modeling process for the geometric models with a wide range of parameterization and aero-structural models. By applying this method, the aerodynamic structure of a large scale wing can be optimized from a multidisciplinary perspective. This method was adopted to work out the design of optimal aerodynamic structure integration for a large aspect ratio wing. According to the optimization result, the number of beams was reduced from 2 to 1, the number of wing ribs reduced from 20 to 15, and the mass reduced by 26.1%.

     

  • loading
  • [1]
    GURUSWAMY G P,OBAYASHI S. Study on the use of high-fidelity methods in aeroelastic optimization[J]. Journal of Aircraft,2004,41(3): 616-619. doi: 10.2514/1.843
    [2]
    胡嘉欣,芮姝,高瑞朝,等. 飞行器结构布局与尺寸混合优化方法[J]. 航空学报,2022,43(5): 225363. HU Jiaxin,RUI Shu,GAO Ruichao,et al. Hybrid optimization method for structural layout and size of flight vehicles[J]. Acta Aeronautica et Astronautica Sinica,2022,43(5): 225363. (in Chinese

    HU Jiaxin, RUI Shu, GAO Ruichao, et al. Hybrid optimization method for structural layout and size of flight vehicles[J]. Acta Aeronautica et Astronautica Sinica, 2022, 43(5): 225363. (in Chinese)
    [3]
    BENAOUALI A,KACHEL S. An automated CAD/CAE integration system for the parametric design of aircraft wing structures[J]. Journal of Theoretical and Applied Mechanics,2017,55(2): 447-459.
    [4]
    陈婉春,孙刚. 基于气动特性翼型参数化方法的适用性研究[J]. 力学季刊,2015,36(4): 678-689. CHEN Wanchun,SUN Gang. Applicability of airfoil parameterization methods based on aerodynamic performance[J]. Chinese Quarterly of Mechanics,2015,36(4): 678-689. (in Chinese

    CHEN Wanchun, SUN Gang. Applicability of airfoil parameterization methods based on aerodynamic performance[J]. Chinese Quarterly of Mechanics, 2015, 36(4): 678-689. (in Chinese)
    [5]
    HICKS R M,HENNE P A. Wing design by numerical optimization[J]. Journal of Aircraft,1978,15(7): 407-412. doi: 10.2514/3.58379
    [6]
    FUJII K,DULIKRAVICH G S. Recent development of aerodynamic design methodologies[M]. Wiesbaden,Germany:Vieweg+Teubner Verlag,1999.
    [7]
    VECCHIA P D,DANIELE E,DʼAMATO E. An airfoil shape optimization technique coupling PARSEC parameterization and evolutionary algorithm[J]. Aerospace Science and Technology,2014,32(1): 103-110. doi: 10.1016/j.ast.2013.11.006
    [8]
    LEUNG T,ZINGG D. Single- and multi-point aerodynamic shape optimization using a parallel newton-krylov approach[R]. AIAA 2009-3803,2009.
    [9]
    BECKER G,SCHÄFER M,JAMESON A. An advanced NURBS fitting procedure for post-processing of grid-based shape optimizations[R]. AIAA2011-891,2011.
    [10]
    VALENCIA E,ALULEMA V,HIDALGO V,et al. A CAD-free methodology for volume and mass properties computation of 3-D lifting surfaces and wing-box structures[J]. Aerospace Science and Technology,2021,108: 106378. doi: 10.1016/j.ast.2020.106378
    [11]
    KULFAN B M. Recent extensions and applications of the ‘CST’ universal parametric geometry representation method[J]. The Aeronautical Journal,2010,114(1153): 157-176. doi: 10.1017/S0001924000003614
    [12]
    KULFAN B M,BUSSOLETTI J E. “Fundamental” parametric geometry representations for aircraft component shapes[R]. AIAA2006-6948,2006.
    [13]
    KULFAN B M. Universal parametric geometry representation method[J]. Journal of Aircraft,2008,45(1): 142-158. doi: 10.2514/1.29958
    [14]
    张德虎,席胜,田鼎. 典型翼型参数化方法的翼型外形控制能力评估[J]. 航空工程进展,2014,5(3): 281-288,295. ZHANG Dehu,XI Sheng,TIAN Ding. Geometry control ability evaluation of classical airfoil parametric methods[J]. Advances in Aeronautical Science and Engineering,2014,5(3): 281-288,295. (in Chinese

    ZHANG Dehu, XI Sheng, TIAN Ding. Geometry control ability evaluation of classical airfoil parametric methods[J]. Advances in Aeronautical Science and Engineering, 2014, 5(3): 281-288, 295. (in Chinese)
    [15]
    关晓辉,李占科,宋笔锋. CST气动外形参数化方法研究[J]. 航空学报,2012,33(4): 625-633. GUAN Xiaohui,LI Zhanke,SONG Bifeng. A study on CST aerodynamic shape parameterization method[J]. Acta Aeronautica et Astronautica Sinica,2012,33(4): 625-633. (in Chinese

    GUAN Xiaohui, LI Zhanke, SONG Bifeng. A study on CST aerodynamic shape parameterization method[J]. Acta Aeronautica et Astronautica Sinica, 2012, 33(4): 625-633. (in Chinese)
    [16]
    LI Runze,DENG Kaiwen,ZHANG Yufei,et al. Pressure distribution guided supercritical wing optimization[J]. Chinese Journal of Aeronautics,2018,31(9): 1842-1854. doi: 10.1016/j.cja.2018.06.021
    [17]
    冯毅,唐伟,任建勋,等. 飞行器参数化几何建模方法研究[J]. 空气动力学学报,2012,30(4): 546-550. FENG Yi,TANG Wei,REN Jianxun,et al. Parametric geometry representation method for hypersonic vehicle configuration[J]. Acta Aerodynamica Sinica,2012,30(4): 546-550. (in Chinese doi: 10.3969/j.issn.0258-1825.2012.04.020

    FENG Yi, TANG Wei, REN Jianxun, et al. Parametric geometry representation method for hypersonic vehicle configuration[J]. Acta Aerodynamica Sinica, 2012, 30(4): 546-550. (in Chinese) doi: 10.3969/j.issn.0258-1825.2012.04.020
    [18]
    粟华,龚春林,谷良贤. 基于三维CST建模方法的两层气动外形优化策略[J]. 固体火箭技术,2014,37(1): 1-6,22. SU Hua,GONG Chunlin,GU Liangxian. Two-level aerodynamic shape optimization strategy based on three-dimensional CST modeling method[J]. Journal of Solid Rocket Technology,2014,37(1): 1-6,22. (in Chinese

    SU Hua, GONG Chunlin, GU Liangxian. Two-level aerodynamic shape optimization strategy based on three-dimensional CST modeling method[J]. Journal of Solid Rocket Technology, 2014, 37(1): 1-6, 22. (in Chinese)
    [19]
    SU Hua,GU Liangxian,GONG Chunlin. Research on geometry modeling method based on three-dimensional CST parameterization technology[R]. AIAA2015-3241,2015.
    [20]
    SU Hua,GONG Chunlin,GU Liangxian. Three-dimensional CST parameterization method applied in aircraft aeroelastic analysis[J]. International Journal of Aerospace Engineering,2017,2017: 1-15.
    [21]
    STRAATHOF M H,VAN TOOREN M J L. Extension to the class-shape-transformation method based on B-splines[J]. AIAA Journal,2011,49(4): 780-790. doi: 10.2514/1.J050706
    [22]
    De BOOR C. A practical guide to splines[J]. Applied Mathematical Sciences,1978,27(149): 157-157.
    [23]
    胡婕. 客机机翼气动/结构多学科设计优化研究[D]. 南京: 南京航空航天大学,2012. HU Jie. Application of MDO to integrated aerodynamic/structural design of wings[D]. Nanjing: Nanjing University of Aeronautics and Astronautics,2012. (in Chinese

    HU Jie. Application of MDO to integrated aerodynamic/structural design of wings[D]. Nanjing: Nanjing University of Aeronautics and Astronautics, 2012. (in Chinese)
    [24]
    VASSBERG J C,TINOCO E N,MANI M,et al. Summary of the third AIAA CFD drag prediction workshop[R]. AIAA 2007-260,2007.
    [25]
    XU Zhaoke,XIA Jian. Aerodynamic optimization based on continuous adjoint method for a flexible wing[J]. International Journal of Aerospace Engineering,2016,2016: 1-16.
  • 加载中

Catalog

    通讯作者: 陈斌, bchen63@163.com
    • 1. 

      沈阳化工大学材料科学与工程学院 沈阳 110142

    1. 本站搜索
    2. 百度学术搜索
    3. 万方数据库搜索
    4. CNKI搜索

    Article Metrics

    Article views (68) PDF downloads(32) Cited by()
    Proportional views
    Related

    /

    DownLoad:  Full-Size Img  PowerPoint
    Return
    Return