NFFD控制点分布对气动外形优化的影响

马明生; 唐静; 李彬; 周桂宇

doi:10.13700/j.bh.1001-5965.2016.0277

NFFD控制点分布对气动外形优化的影响

doi: 10.13700/j.bh.1001-5965.2016.0277

马明生^{1, 2, ,},
唐静¹,
李彬²,
周桂宇²

1.
西北工业大学航空学院, 西安 71007
2.
中国空气动力研究与发展中心计算空气动力研究所, 绵阳 621000

详细信息

作者简介:
马明生, 男, 博士, 研究员, 博士生导师。主要研究方向:飞行器气动总体设计

唐静, 男, 博士研究生。主要研究方向:飞行器气动外形优化设计、非结构网格技术

李彬, 男, 博士。主要研究方向:飞行器气动外形优化设计、外挂物分离投放数值模拟

通讯作者:
马明生, E-mail:ma_mingsheng@sina.cn

中图分类号: V221⁺.3;TB553
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出版历程
- 收稿日期: 2016-04-11
- 录用日期: 2016-05-20
- 网络出版日期: 2017-04-20

Effects of NFFD control points distribution on aerodynamic shape optimization

MA Mingsheng^{1, 2
, ,},
TANG Jing¹,
LI Bin²,
ZHOU Guiyu²

1.
School of Aeronautics, Northwestern Polytechnical University, Xi'an 71007
2.
Computational Aerodynamics Institute, China Aerodynamics Research and Development Center, Mianyang 621000, China

More Information

Corresponding author: MA Mingsheng, E-mail:ma_mingsheng@sina.cn

摘要

摘要:
基于非均匀有理B样条的自由型面变形（NFFD）技术具有对变形对象普适性和控制点影响区域局部性的特点，广泛应用于气动外形优化。本文通过扩展控制体和合理布置外侧控制点，实现了NFFD技术在参数化曲面并改变曲面形状时，同步变形控制体内的表面网格和空间网格，并从理论上保证了控制体边界内外的网格协调。基于离散伴随方法求取梯度，分别采用拟牛顿（QN）法和序列二次规划（SQP）优化方法，通过从初始翼型NACA0012到标准翼型EH1590的反设计，研究了NFFD控制点数量和分布对设计结果的影响。在某飞翼标模单点全机升阻比优化应用中，改进控制点分布后获得了更高的升阻比，收敛速度显著提高。
- 气动优化 /
- 反设计 /
- 自由型面变形 /
- 网格变形 /
- 控制点分布 /
- 翼型 /
- 飞翼
Abstract:
The NURBS based free-form deformation (NFFD), which is universal for representation of object geometry, and whose control point influence zone is local for geometry deformation, is used widely for aerodynamic shape optimization. By extending the control volume and locating the outer control points appropriately, NFFD is used to parameterize the surface, deform the surface grid and volume grid in one single process. The grid cells both inside and outside control volume are preserved consistent theoretically after shape deformation. With the gradient of object function calculated by discrete adjoint method, both the quasi-Newton (QN) and sequential quadratic programming (SQP) optimization techniques are applied to inverse airfoil design from the initial airfoil, NACA0012, to the standard flying-wing airfoil, EH1590. The effects of the number and distribution of control points on optimization result are discussed. In the case of the lift-to-drag ratio optimization for a whole aircraft with flying-wing in a single design state, the convergence speed is improved obviously and higher lift-to-drag ratio is obtained by improving the distribution of control points.
- aerodynamic optimization /
- inverse design /
- free-form deformation /
- grid deformation /
- control points distribution /
- airfoil /
- flying-wing

HTML全文

图 1 变形前后控制体和翼型

Figure 1. Control volume and airfoil before and after deformation

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图 2 不同基函数次数时翼型变形

Figure 2. Airfoil deformation of different basis function degrees

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图 3 修改后的控制体和变形后的翼型

Figure 3. Modified control volume and deformed airfoil

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图 4 二维NFFD控制点和其定义的控制曲面

Figure 4. 2D control points and control surface of NFFD

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图 5 同时参数化物面和变形空间网格的控制体

Figure 5. Control volume for both shape parameterization and space grid deformation

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图 6 NFFD变形空间网格

Figure 6. Space grid deformation by NFFD

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图 7 IDWF变形空间网格

Figure 7. Space grid deformation by IDWF

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图 8 初始翼型和3种均匀分布控制点

Figure 8. Initial airfoil and three types of uniformly distributed control points

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图 9 控制点均匀分布时目标函数收敛历程

Figure 9. Convergence history of objective function with uniformly distributed control points

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图 10 控制点均匀分布时反设计翼型比较

Figure 10. Comparison of inversely designed airfoils with uniformly distributed control points

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图 11 第1步各控制点的目标函数梯度

Figure 11. Objective function gradient of control points at the first step

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图 12 初始翼型和3种聚集分布控制点

Figure 12. Initial airfoil and three types of aggregated distributed control points

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图 13 采用QN法和SQP方法的不同控制点目标函数收敛历程

Figure 13. Convergence history of objective function based on different control points by QN and SQP methods

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图 14 控制点均匀和聚集分布时反设计翼型比较

Figure 14. Comparison of inversely designed airfoils between uniformly and aggregated distributed control points

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图 15 飞翼优化改进前后的控制点及其分布

Figure 15. Control points and distribution before and after flying-wing optimization

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图 16 升阻比和相对容积比收敛历程

Figure 16. Convergence history of lift-to-drag ratio and volume ratio

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图 17 升力和阻力系数收敛历程

Figure 17. Convergence history of lift and drag coefficients

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图 18 优化后不同展向剖面几何形状和压力分布比较

Figure 18. Comparison of wing section shapes and pressure distribution at different span location after optimization

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