摘要
阐述了星箭振动试验过程中的过试验现象及其机理,分析了几种常用的力限试验条件设计方法。通过建立星箭分析模型,利用三种分析方法进行了星箭力限试验条件的计算,并与星箭耦合分析、振动台仿真分析结果进行了对比。表明如果两个子系统的有限元分析模型和外载荷在分析频段均可靠,直接通过有限元软件获得界面力和界面加速度,并进一步得出二者的转换关系,应更有应用价值。在有限元模型不可靠或星箭结构方案设计阶段,基于复杂二自由度模型的简化分析方法,可以较好地得到力限试验条件。
In this paper, the overload theory of the payload and launch vehicle vibration testing is explained. Several commonly used methods are analyzed. Using the payload and launch vehicle FEM models, three methods are used to calculate the force limited input .The results are compared with the couple-load analysis and the vibration simulation. The results show that we can use FEM software to obtain interface force and acceleration if the FEM model and the external force are reliable. If the FEM model is not reliable or the structure is in the project selection stage, the better method is to use the Complex Two Degree-Of-Freedom System to obtain the force limited input.
出处
《强度与环境》
2010年第3期1-9,共9页
Structure & Environment Engineering
