大展弦比飞行器突风响应数值计算

杨龙源; 魏新元; 曾竹青; 杨永

doi:10.7638/kqdlxxb-2024.0206

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大展弦比飞行器突风响应数值计算

研究论文 | 更新时间：2026-05-28

- 大展弦比飞行器突风响应数值计算
- Numerical simulation on gust responses of high aspect ratio aircraft
- 空气动力学学报 2026年44卷第4期页码：114-124
- 作者机构：
  
  西北工业大学飞行器基础布局全国重点实验室,西安,710072
- 作者简介：
  
  杨龙源（1999—），男，广西贺州人，研究方向：飞行器多学科耦合数值计算. E-mail：qfdlylyuan@163.com
  杨永*，教授，研究方向：空气动力学，流体力学，飞行器多学科耦合数值计算. E-mail：yyang@nwpu.edu.cn
- 基金信息：
- DOI：10.7638/kqdlxxb-2024.0206
  中图分类号： V211.3
- 纸质出版：2026
- 稿件说明：
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杨龙源, 魏新元, 曾竹青, 等. 大展弦比飞行器突风响应数值计算[J]. 空气动力学学报, 2026, 44(4): 114−124.

Yang Longyuan, Wei Xinyuan, Zeng Zhuqing, et al. Numerical simulation on gust responses of high aspect ratio aircraft[J]. 2026, 44(4): 114-124.
杨龙源, 魏新元, 曾竹青, 等. 大展弦比飞行器突风响应数值计算[J]. 空气动力学学报, 2026, 44(4): 114−124. DOI： 10.7638/kqdlxxb-2024.0206

Yang Longyuan, Wei Xinyuan, Zeng Zhuqing, et al. Numerical simulation on gust responses of high aspect ratio aircraft[J]. 2026, 44(4): 114-124. DOI： 10.7638/kqdlxxb-2024.0206.

摘要

大展弦比飞行器在受到突风扰动后，机翼弯矩、扭矩等载荷的重新分布容易引起气动与结构之间的强耦合，同时原有的飞行姿态与稳定性也会受到影响。为了准确获取大展弦比飞行器受突风扰动后的动态载荷分布与姿态响应，本文以展弦比为20的平直机翼+平尾构型为研究对象，综合考虑突风扰动下气动、结构、纵向姿态响应带来的影响，完成了飞行器在1-cos典型离散突风不同幅值下的多学科耦合数值模拟，并进一步研究了不同学科对动态载荷分布及姿态响应的影响规律。研究发现，耦合不同学科后计算的载荷分布和响应结果，相比于单一学科计算结果，其变化量存在线性叠加关系；但随着突风扰动不断增强，这种线性叠加关系将不再成立。在飞行器的载荷设计阶段，本文采用的多学科方法可作为飞行器突风设计的准确评估手段，用于评估突风对飞行器产生的影响。

Abstract

The bending moment and torque of a high aspect ratio (AR) wing are redistributed when encountering gust turbulence

leading to the strong coupling of aerodynamics and structural dynamics. Affected by gust encounter

the original attitude and stability of the aircraft may also change. In order to obtain the aircraft dynamic load distribution and flight dynamic response accurately during gust encounter

multidisciplinary numerical simulations were conducted on a wing-and-tail configuration with a straight wing of AR = 20 under different amplitudes of the typical 1-cos gust

comprehensively considering the effects of aerodynamics

structural dynamics

and longitudinal attitude response. The impact of different disciplines on the dynamic load distribution and attitude response was explored. The results show that there is a linear superposition relationship for the responses after coupling different disciplines. With the increase of gust amplitude

this linear superposition relationship is no longer valid. In the aircraft load design stage

the multidisciplinary method adopted in this paper can serve as an accurate assessment tool for gust design

evaluating the impact of gust disturbances on the aircraft.

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references

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