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薄壁截锥壳静气动弹性响应分岔研究

石乔木 石先杰 李鹏 张德春

空气动力学学报2025,Vol.43Issue(2):51-59,9.
空气动力学学报2025,Vol.43Issue(2):51-59,9.DOI:10.7638/kqdlxxb-2024.0097

薄壁截锥壳静气动弹性响应分岔研究

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

石乔木 1石先杰 2李鹏 1张德春1

作者信息

  • 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
  • 折叠

摘要

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.

关键词

低速轴向气流/薄壁截锥壳/响应分岔/非线性屈曲/风洞实验

Key words

low-speed axial airflow/thin-walled truncated conical/response bifurcation/nonlinear buckling/wind tunnel experiment

引用本文复制引用

石乔木,石先杰,李鹏,张德春..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):51-59,9.

基金项目

国家自然科学基金(12072298) (12072298)

空气动力学学报

OA北大核心

0258-1825

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