Bifurcation of static aeroelastic response of thin-walled truncated conical shells

SHI Qiaomu; SHI Xianjie; LI Peng; ZHANG Dechun

doi:10.7638/kqdlxxb-2024.0097

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Bifurcation of static aeroelastic response of thin-walled truncated conical shells

更新时间：2026-05-28

- Bifurcation of static aeroelastic response of thin-walled truncated conical shells
- Vol. 43, Issue 2, Pages: 51-59(2025)
- 作者机构：
  
  1. 西南交通大学力学与航空航天学院,成都,610031
  2. 中国工程物理研究院总体工程研究所,绵阳,621000
- 作者简介：
- 基金信息：
- DOI：10.7638/kqdlxxb-2024.0097
  CLC： V211.1;V211.74
- Published：2025
- 稿件说明：
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石乔木, 石先杰, 李鹏, 等. 薄壁截锥壳静气动弹性响应分岔研究[J]. 空气动力学学报, 2025, 43(2): 51−59.

SHI Qiaomu, SHI Xianjie, LI Peng, et al. Bifurcation of static aeroelastic response of thin-walled truncated conical shells[J]. 2025, 43(2): 51-59.
石乔木, 石先杰, 李鹏, 等. 薄壁截锥壳静气动弹性响应分岔研究[J]. 空气动力学学报, 2025, 43(2): 51−59. DOI： 10.7638/kqdlxxb-2024.0097

SHI Qiaomu, SHI Xianjie, LI Peng, et al. Bifurcation of static aeroelastic response of thin-walled truncated conical shells[J]. 2025, 43(2): 51-59. DOI： 10.7638/kqdlxxb-2024.0097.

摘要

为探究薄壳结构的气动弹性失稳问题，设计和完成了低速轴向气流中薄壁截锥壳结构的静气动弹性响应风洞实验。实验中观测到截锥壳出现了显著的非线性响应行为：随着风速的连续变化，结构呈现典型的5瓣式小幅变形向4瓣式大幅变形的突跳现象。为揭示系统出现这种非线性响应的分岔机理，基于非线性壳体变形理论，提出了截锥壳稳态气动力的简化计算模型，计算和重现了系统响应分岔过程，准确捕捉到了分岔的临界风速。结果表明，考虑结构非线性时，系统响应分岔的临界风速（非线性失稳风速）低于线性系统的失稳临界风速；系统在升、降速阶段会呈现不同的响应路径，具有复杂的全局分岔行为，这本质上是轴向稳态气流“冲击”壳体所诱发的结构非线性屈曲问题。本文研究为薄壁结构的气动弹性设计提供了重要的理论依据。

Abstract

To investigate the aeroelastic instability of thin-shell structures

this article presents a comprehensive wind tunnel experiment focusing on the static aerodynamic response of a thin-walled truncated conical shell structure subjected to low-speed axial airflow. The experiment uncovered significant nonlinear response behavior of the truncated conical shell. As the wind speed increased

the structure initially exhibited a typical small five-petal deformation

followed by an abrupt transition to a large four-petal deformation. To provide a theoretical explanation for the observed bifurcation of this nonlinear response

a simplified calculation model for the steady-state aerodynamic force of the truncated cone shell was proposed. Based on the theory of nonlinear shell deformation

the bifurcation process of the response was calculated and reproduced

accurately capturing the critical wind speed at which the bifurcation occurs. Results indicate that

when considering the geometric nonlinearity of the truncated cone shell structure

the critical speed of system response bifurcation (nonlinear instability speed) is lower than that predicted by a linear system. Furthermore

the system demonstrates different response trajectories during the acceleration and deceleration stages

characterized by complex global bifurcation characteristics. The bifurcation behavior of static aeroelastic response occurring in truncated conical shells can be attributed to the nonlinear buckling problem induced by the "impact" of axial steady-state airflow on the shell.This study provides an important theoretical basic for the aeroelastic design of thin-walled structures.

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