卫星过渡支架附加约束阻尼层减振效果验证

摘要

From axial vibration test of satellite transition bracket、satellite bracket and satellite, it is found that the maximum vibration amplitude of the satellite transition bracket has been increased 4.24 times in the first mode 33.67Hz. This conduced to higher vibration condition for satellite interface. Constrained layer damping (CLD) was arranged on the surface of the satellite transition bracket to decrease vibration condition of satellite interface. Vibration suppression validation test of satellite transition bracket with CLD was carried out. Test result indicated that vibration amplitude of the satellite transition bracket has been decreased 15.1%-16.1% in the 0.15g level. Vibration suppression is more efficiency with vibration level increased. Strain response suppression is more efficiency than acceleration response for satellite transition bracket.%某型号卫星过渡支架、卫星支架及卫星在进行轴向方向振动试验时，在一阶共振频率33.67Hz时，经过卫星过渡支架加速度响应放大4.24倍，从而导致提供给卫星的界面振动条件过高。为了降低星箭界面振动量级，对卫星过渡支架采用增加约束阻尼层的方法进行减振。通过试验的方法对附加约束阻尼层减振效果进行了验证，试验结果表明随着振动量级增加约束阻尼层减振效果越明显，在0.15g输入条件下，星箭界面加速度响应减少15.1%～16.1%。对于过渡支架本身，应变响应减振效果比加速度响应减振效果更加明显。