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为了满足星载一体化光学小卫星对主承力板的刚度和重量要求,降低主承力板上各单机的动力学响应,对工程常用的蜂窝夹层板等效理论和动力学分析方法进行研究。首先,介绍了六边形蜂窝芯子的等效理论和考虑胶层的面板等效理论。建立了某星载一体化光学小卫星-Y向主承力板的有限元模型,以重量和动态刚度为目标,对蜂窝芯子参数进行优化分析。通过分析比较不同芯子蜂窝板的重量和刚度,最终选择壁厚为0.03 mm,边长为5 mm的蜂窝芯子。然后,在模态分析的基础上,对蜂窝主承力板进行正弦振动和随机振动分析。最后,进行相应的正弦振动和随机振动试验。分析与试验结果表明:一阶自然频率误差为1.9%;正弦加速度响应误差为4.5%;随机均方根加速度响应误差为3.7%。表明分析模型建立准确,参数等效合理,动力学响应分析准确,并且能满足卫星结构总体和各个星上单机对主承力板的动力学响应要求。
In order to meet the stiffness and weight requirements of the main bearing plate by the satellite integrated optical small satellite and to reduce the dynamic response of each single bearing on the main bearing plate, the equivalent theory and dynamic analysis method of honeycomb sandwich panels . First of all, the equivalent theory of hexagonal honeycomb core and the panel equivalent theory of plastic layer are introduced. A finite element model of a small satellite-Y to the main bearing plate was established, and the honeycomb core parameters were optimized by the weight and dynamic stiffness. By analyzing the weight and stiffness of different honeycomb honeycomb panels, a honeycomb core with a wall thickness of 0.03 mm and a side length of 5 mm was finally selected. Then, based on the modal analysis, the sinusoidal vibration and random vibration analysis of the honeycomb main bearing plate are carried out. Finally, the corresponding sine vibration and random vibration test. The analysis and experimental results show that the first-order natural frequency error is 1.9%, the sinusoidal acceleration response error is 4.5% and the random root mean square acceleration response error is 3.7%. The results show that the analysis model is accurate, the parameters are equivalent and reasonable, the dynamic response analysis is accurate, and it can meet the dynamic response requirements of satellite structure and stand-alone on the main bearing plate.