基于CST的三维机翼气动结构解析参数化建模与优化方法

杨予成; 粟华; 龚春林; 谷良贤; 丁轩鹤; 王子一

doi:10.13224/j.cnki.jasp.20220289

基于CST的三维机翼气动结构解析参数化建模与优化方法

doi: 10.13224/j.cnki.jasp.20220289

西北工业大学航天学院陕西省空天飞行器设计重点实验室，西安 710072

基金项目: 基础科研计划（JCKY2020204B016）

详细信息

作者简介:
杨予成（1998-），男，硕士生，主要从事飞行器设计与多学科优化方面研究

通讯作者:
粟华（1985-），男，副研究员，博士，主要从事飞行器设计与多学科优化技术方面研究。E-mail：su@nwpu.edu.cn

中图分类号: V214.19
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- 被引次数: 0
出版历程
- 收稿日期: 2022-04-30
- 网络出版日期: 2023-11-04

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

Shannxi Aerospace Flight Vehicle Design Key Laboratory，School of Astronautics，Northwestern Polytechnical University，Xi’an 710072，China

摘要

摘要:
针对概念设计阶段机翼设计需要大范围探索设计空间并进行气动结构一体化设计的需求，提出一种基于类别/形状变换函数（class-shape function transformation, CST）的三维机翼气动结构解析参数化建模与优化方法。在二维CST基础上，推导三维CST参数化几何模型的解析函数形式，通过网格自适应离散与结构特征提取技术建立了三维机翼的气动和结构解析参数化模型，能够同时支持包括机翼几何构型、结构布局、结构尺寸、材料属性等参数的气动结构一体化快速建模与优化求解，具备几何模型大范围参数化以及气动、结构模型的建模过程自动化能力。采用该方法对某大展弦比机翼开展气动结构一体化优化设计，对比固定结构布局优化方案，优化结果梁由2个减至1个，翼肋由20个减至15个，质量相比减少26.1%。
- 几何建模 /
- 解析参数化建模 /
- 类别/形状变换函数 /
- 机翼设计 /
- 气动弹性优化
Abstract:
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%.
- geometric modeling /
- analytical parametric modeling /
- class/shape function transformation /
- wing design /
- aeroelastic optimization

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图 1 基本曲面框架

Figure 1. Frame of basic surface

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图 2 部件参数化外形

Figure 2. Parametric shape of component

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图 3 参数化气动网格模型

Figure 3. Parametric aerodynamic mesh model

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图 4 网格修正流程

Figure 4. Mesh correction process

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图 5 气动网格修正前后对比

Figure 5. Comparison of before and after aerodynamic mesh correction

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图 6 机翼结构参数化模型

Figure 6. Parametric model of the wing structure

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图 7 气动结构一体化优化流程

Figure 7. Aero-structural integration optimization process

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图 8 DPW-W1机翼参数化气动模型

Figure 8. Parametric aerodynamic model of DPW-W1 wing

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图 9 DPW-W1翼型压力分布对比

Figure 9. Pressure distribution comparison of DPW-W1 wing

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图 10 DPW-W1机翼参数化气动结构模型

Figure 10. Parametric aero-structural model of DPW-W1 wing

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图 11 气动结构优化Mises应力云图

Figure 11. Contours of Mises stress for aero-structural optimization

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图 12 优化前后机翼截面对比

Figure 12. Comparison of pre- and post-optimized wing sections

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图 13 变布局优化后的机翼结构布局

Figure 13. Variable layout optimized wing structure layout

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图 14 变布局优化后机翼Mises应力云图

Figure 14. Contours of Mises stress for variable structural layout aero-structural optimization

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表 1 基本曲面设计变量

Table 1. Design variables of basic surface

设计变量	参数
翼根截面形状控制因子	$ {N_{11}} $，$ {N_{12}} $
翼梢截面形状控制因子	$ {N_{21}} $，$ {N_{22}} $
法向形状控制因子	${M_1}$，${M_2}$
展向形状控制因子	${T_1}$，${T_2}$
表面权重因子	$ {{{b}}_{i,j}} $
展向权重因子	$ {{{b}}_t} $

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表 2 气动结果对比

Table 2. Comparison of aerodynamic results

参数		修正前	修正后	文献[24]
$ {C_L} $	数值	0.46873	0.48262	0.48684
$ {C_L} $	与文献[24]的误差/%	−3.72	−0.87	0.48684
$ {C_D} $	数值	0.01819	0.01978	0.02098
$ {C_D} $	与文献[24]的误差/%	−13.3	−5.72	0.02098
$ {C_M} $	数值	−0.06754	−0.07210	−0.06970
$ {C_M} $	与文献[24]的误差/%	−3.10	3.44	−0.06970
$ L/D $	数值	25.7686	24.3994	23.21
$ L/D $	与文献[24]的误差/%	11.02	5.12	23.21

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表 3 优化结果对比

Table 3. Comparison of optimization results

参数	优化前	优化后
参数	优化前	固定结构布局	可变结构布局
$ {C_L} $	0.40348	0.40015	0.40001
$ {C_D} $	0.01333	0.01311	0.01316
最大位移变形/m	2.66198	2.75547	2.73183
最大扭转变形/m	0.070146	0.067274	0.066811
结构质量/kg	20412.7	18849.5	13926.2

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