【摘要】 目的 研究某高超声速导弹飞行过程中的振动状态，获得导弹在给定压力载荷下的振动响应特性。方法结合有限元分析、随机振动理论，利用三维软件构建导弹有限元模型，并在Ansys Workbench平台对其进行模态分析及谐响应分析。基于模态分析结果，对导弹进行随机振动响应试验，探究导弹在频域及力学上的振动响应特征。结果 计算得出导弹前六阶固有频率和振型，获得导弹上一检测点在给定振动激励载荷下的加速度响应曲线，并得到导弹整体结构的应力分布云图。结论 导弹模型强度符合要求，导弹在振动激励载荷下的加速度响应峰值均出现在380～400Hz，应力极值出现在导弹尾部区域，在此区域内，导弹更易产生结构性损伤。在飞行器地面环境模拟试验中，应着重考虑此频域及位置的振动条件。更多还原

【Abstract】 The work aims to study the vibration state of a hypersonic missile during flight and obtain the vibration response characteristics of the missile under a given pressure load. Combined with finite element analysis and random vibration theory,the finite element model of the missile was constructed with the three-dimensional software, and the modal analysis and harmonic response analysis were carried out on the platform of Ansys Workbench. Based on the modal analysis results, the random vibration response test of the missile was carried out to explore the vibration response characteristics of the missile in frequency domain and mechanics. The first six natural frequencies and vibration modes of the missile were calculated. The acceleration response curve of a detection point on the missile under a given vibration excitation load was obtained. The stress distribution pattern of the overall structure of the missile was obtained. The strength of the missile model meets the requirements. The peak acceleration response of the missile under vibration excitation load appears between 380 Hz and 400 Hz, and the extreme stress appears in the tail area of the missile. In this area, the missile is more prone to structural damage. In the ground environment simulation experiment of the missile, the vibration conditions in this frequency domain and position should be emphatically considered.更多还原