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 requirements of honeycomb sandwich plate of an optical small satellite on the weight and stiffness, and to reduce the dynamic response of components on honeycomb sandwich plate, the equivalent theory and dynamic analysis of honeycomb sandwich plate were studied. First of all, the equivalent theory of the hexagon honeycomb core and the face sheet with adhesive layer were introduced. Then, the finite element model of -Y honeycomb sandwich plate of an optical small satellite were established, and the optimization analysis of the honeycomb core parameter with the weight and dynamic stiffness as the goal was performed. Analyzing and comparing the weight and stiffness of different core, finally, the honeycomb core of 0.03 mm in thickness and 5 mm in length was chosen. And then, on the basis of modal analysis, sine vibration and random vibration analysis are performed on the honeycomb sandwich plate. Finally, the sine and random vibration test are carried out. The experimental results and analytic solution showed that the first natural frequency error is 1.9%; the sine acceleration response error is 4.5% and the random acceleration response RMS error is 3.7%. These indicated that the analysis model is established accurately, the equivalence of parameters is reasonable and the dynamic analysis is accurate, and thus could meet the dynamic response requirements of satellite integration and each single component on the honeycomb sandwich plate.