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采用Pro/Engineer三维设计软件,建立6管旋回俯仰火箭发射装置三维模型,将模型导入ABAQUS/CAE环境中,建立了火箭发射装置有限元模型。通过有限元模型模态分析,获得火箭发射装置前4阶频率和振型,并分析计算了基频共振情况下火箭发射装置的变形和应力,找出结构潜在的问题,提出解决措施。通过对6管旋回俯仰火箭发射装置实物样机振动台试验,验证了有限元计算分析结果。研究结果表明有限元分析方法一定程度上解决了火箭发射装置振动特性分析理论性不足问题,提高初始设计可信度。
The Pro / Engineer three-dimensional design software was used to build a three-dimensional model of six-tube gyration pitch rocket launcher. The model was imported into the ABAQUS / CAE environment and a rocket launcher finite element model was established. Through the modal analysis of the finite element model, the first 4 orders of the rocket launch device’s frequency and mode shape are obtained. The deformation and stress of the rocket launch device under the fundamental resonance condition are analyzed and calculated, and the potential problems of the structure are found out and the solutions are proposed. Through the physical prototype shaking table test of six-tube gyration pitch rocket launcher, the finite element analysis results were verified. The research results show that the finite element analysis method can solve the theoretical problem of the vibration characteristics analysis of rocket launchers to a certain extent, and improve the credibility of initial design.