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

作　　者：石乔木 石先杰[2] 李鹏[1] 张德春 SHI Qiaomu;SHI Xianjie;LI Peng;ZHANG Dechun(School of Mechanics and Aerospace Engineering,Southwest Jiaotong University,Chengdu610031,China;General Engineering Research Institute of China Academy of Engineering Physics,Mianyang621000,China)

机构地区：[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

出　　处：《空气动力学学报》2025年第2期51-59,I0001,共10页Acta Aerodynamica Sinica

基　　金：国家自然科学基金(12072298)。

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。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 

分 类 号：V211.1[航空宇航科学与技术—航空宇航推进理论与工程] V211.74