基于速度分裂法的翼型阵风响应及减缓数值模拟

高坤; 郭同庆; 纪哲翰; 周迪; 陆志良

doi:10.7638/kqdlxxb-2022.0123

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基于速度分裂法的翼型阵风响应及减缓数值模拟

研究论文 | 更新时间：2026-05-28

- 基于速度分裂法的翼型阵风响应及减缓数值模拟
- Numerical simulations of airfoil gust response and alleviation based on split velocity method
- 空气动力学学报 2023年41卷第4期页码：84-95
- 作者机构：
  
  南京航空航天大学非定常空气动力学与流动控制工业和信息化部重点实验室,南京,210016
- 作者简介：
  
  高坤（1998-），男，陕西铜川人，硕士研究生，研究方向：气动弹性力学. E-mail：gaok0529@163.com
  郭同庆*，教授，研究方向：计算流体力学，气动弹性力学. E-mail：guotq@nuaa.edu.cn
- 基金信息：
  
  国家自然科学基金（11872212，12102187）;江苏省高校优势学科建设工程资助项目
- DOI：10.7638/kqdlxxb-2022.0123
  中图分类号： V211.47
- 纸质出版：2023
- 稿件说明：
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高坤, 郭同庆, 纪哲翰, 等. 基于速度分裂法的翼型阵风响应及减缓数值模拟[J]. 空气动力学学报, 2023, 41(4): 84−95.

GAO Kun, GUO Tongqing, JI Zhehan, et al. Numerical simulations of airfoil gust response and alleviation based on split velocity method[J]. 2023, 41(4): 84-95.
高坤, 郭同庆, 纪哲翰, 等. 基于速度分裂法的翼型阵风响应及减缓数值模拟[J]. 空气动力学学报, 2023, 41(4): 84−95. DOI： 10.7638/kqdlxxb-2022.0123

GAO Kun, GUO Tongqing, JI Zhehan, et al. Numerical simulations of airfoil gust response and alleviation based on split velocity method[J]. 2023, 41(4): 84-95. DOI： 10.7638/kqdlxxb-2022.0123.

摘要

国内现阶段飞行器阵风响应CFD模拟通常采用网格速度法（FVM），而近年提出的更为准确的速度分裂法（SVM）目前主要针对刚性飞行器阵风响应分析。本文将SVM拓展至弹性翼型的One-Minus-Cosine阵风响应计算和减缓研究。基于动态网格系统非定常Navier-Stokes方程，将阵风条件下的速度场分解为阵风速度与背景速度的叠加，理论推导出SVM阵风模拟控制方程，结果表明，FVM是SVM忽略源项后的一种近似方法。进一步建立起弹性翼型阵风响应预测的CFD/CSD时域耦合算法和基于俯仰控制的阵风响应减缓数值模拟方法。算例分析了NACA0012刚性及弹性翼型的One-Minus-Cosine阵风响应，计算结果与文献数据一致，在此基础上分析了阵风尺度、黏性和结构弹性对阵风响应的影响。开展了NACA64A010弹性翼型One-Minus-Cosine阵风减缓模拟，结果表明：单一的沉浮速度控制输入量更有利于减缓阵风载荷峰值，而沉浮速度、俯仰角相结合的控制输入量则能同时减缓翼型的沉浮和俯仰运动。本文工作可为三维飞行器阵风响应和减缓研究提供参考。

Abstract

It is a common practice for domestic researchers to conduct Computational Fluid Dynamics (CFD) simulations of the aircraft gust response using the field velocity method (FVM). The more accurate split velocity method (SVM) proposed recently has become progressively popular for gust response analysis but is limited to rigid aircraft. This paper extends SVM to simulate the One-Minus-Cosine gust response of elastic airfoils and to alleviate the gust load. First

velocity fields obtained by solving unsteady Navier-Stokes equations in dynamic meshes are decomposed into the gust and background velocities. The control equations of SVM are derived

which show that FVM is an approximation of SVM when neglecting the source term. Next

the CFD/CSD coupling algorithms in the time domain are established for the elastic airfoil gust response prediction and the gust response alleviation based on pitch control. The One-Minus-Cosine gust responses of rigid and elastic NACA0012 airfoils agree well with the reference data. The effects of gust length

viscosity

and structural elasticity on gust response are also analyzed. Finally

the One-Minus-Cosine gust alleviation simulation of the elastic NACA64A010 airfoil is conducted. Results show that changing only the plunge speed is more efficient in alleviating the peak gust load; the combined control of plunge speed and pitch angle can alleviate the plunge and pitch movements. This work lays a foundation for further study on gust response and alleviation of three-dimensional aircraft.

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references

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