国防科技大学学报2025，Vol.47Issue(3)：73-80,8.DOI:10.11887/j.cn.202503008
火箭横向模态耦合型自激振动的稳定性分析与仿真模拟
Stability analysis and simulation of transverse mode-coupled self-excited vibration of rocket
摘要
Abstract
In order to intensive study the self-excited vibration phenomenon of rocket in the flight test,a two-degree-of-freedom linear system based on the coupling of elastic force and aerodynamic force was established,and the working mechanism of self-excited vibration caused by the displacement feedback between pitch and yaw degrees of freedom was explained.By analyzing the stability of the motion equation of the system,the criterion of losing asymptotic stability of equilibrium point and generating self-excited vibration was obtained.The time history curves of pitch and yaw angular displacement were obtained by solving ordinary differential equations with numerical method.The comparison between the simulation results and the measured data shows that the sudden amplification of vibration divergence phenomenon during the flight of rocket is the mode-coupling self-excited vibration caused by displacement feedback.In addition,the analysis results show that the beat or constant frequency vibration usually occurs before and after the self-excited vibration.关键词
模态耦合/位移反馈/稳定性分析/自激振动/拍频振动Key words
mode-coupling/displacement feedback/stability analysis/self-excited vibration/beat frequency vibration分类
军事科技引用本文复制引用
商霖,张海瑞,孙向春,宋志国,高峰,孙冬伟..火箭横向模态耦合型自激振动的稳定性分析与仿真模拟[J].国防科技大学学报,2025,47(3):73-80,8.基金项目
国家自然科学基金资助项目(U20B2028) （U20B2028）
