北京航空航天大学学报 ›› 2015, Vol. 41 ›› Issue (5): 897-903.doi: 10.13700/j.bh.1001-5965.2014.0387

• 论文 • 上一篇    下一篇

二元可变后缘翼型的鲁棒优化设计

郑宇宁1, 邱志平1, 黄仁1, 苑凯华2   

  1. 1. 北京航空航天大学 航空科学与工程学院, 北京 100191;
    2. 北京机电工程研究所, 北京 100074
  • 收稿日期:2014-06-30 修回日期:2014-09-19 出版日期:2015-05-20 发布日期:2015-06-02
  • 通讯作者: 黄仁(1986—),男,湖南怀化人,博士,huangren@buaa.edu.cn,主要研究方向为气动弹性力学. E-mail:huangren@buaa.edu.cn
  • 作者简介:郑宇宁(1990—),男,陕西西安人,博士研究生,ynzheng@buaa.edu.cn
  • 基金资助:

    国家自然科学基金(11372025,11432002);国防基础科研计划(A0420132101,JCKY2013601B);高等学校学科创新引智计划(B07009)

Robust design optimization of a two-dimensional airfoil with deformable trailing edge

ZHENG Yuning1, QIU Zhiping1, HUANG Ren1, YUAN Kaihua2   

  1. 1. School of Aeronautic Science and Engineering, Beijing University of Aeronautics and Astronautics, Beijing 100191, China;
    2. Beijing Electron-Mechanical Engineering Institute, Beijing 100074, China
  • Received:2014-06-30 Revised:2014-09-19 Online:2015-05-20 Published:2015-06-02

摘要:

为了改善二元可变后缘翼型在外界条件变化时的气动稳定性,提出了一种考虑不确定性的鲁棒性优化方法.在类别形状函数变换(CST)方法的基础上,建立了二元可变后缘翼型的参数化模型.探讨了确定性优化方法与鲁棒性优化方法的区别.充分考虑翼型几何形状和来流马赫数的不确定性,进行了最大化升阻比均值、最小化升阻比标准差的鲁棒优化设计.对于优化后的可变后缘翼型,计算了变形所需的驱动能.结果表明:鲁棒性优化方法在提升翼型气动性能的同时降低了该性能对来流马赫数的敏感度,鲁棒性优化翼型所需的驱动能有所减少.

关键词: CST方法, 变后缘, 不确定性, 鲁棒性优化, 驱动能

Abstract:

In order to improve the aerodynamic stability of a two-dimensional airfoil with deformable trailing edge during the change of external conditions, a robust optimization method considering the uncertainty was proposed. Based on class-shape function transformation (CST) method, a parametric model was established to represent the geometry of a two-dimensional airfoil with a deformable trailing edge. The differences between robust optimization method and deterministic optimization method were discussed. Taking into account the uncertain airfoil geometry and inlet Mach number, the robust optimization method was applied to maximize the mean value of the lift-to-drag ratio and minimize its standard deviation. The actuation power requirement of the optimized airfoil with a deformable trailing edge was calculated. The results show that the robust optimization method can help to improve the aerodynamic performance of morphing airfoil and reduce the sensitivity of this performance to inlet Mach number simultaneously and to reduce the actuation power requirement of the robust optimal airfoil.

Key words: class-shape function transformation (CST) method, deformable trailing edge, uncertainty, robust optimization, actuation power

中图分类号: 


版权所有 © 《北京航空航天大学学报》编辑部
通讯地址:北京市海淀区学院路37号 北京航空航天大学学报编辑部 邮编:100191 E-mail:jbuaa@buaa.edu.cn
本系统由北京玛格泰克科技发展有限公司设计开发