CAJ | 학술논문

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。
모형호위성과도지가、위성지가급위성재진행축향방향진동시험시，재일계공진빈솔33.67Hz시，경과위성과도지가가속도향응방대4.24배，종이도치제공급위성적계면진동조건과고。위료강저성전계면진동량급，대위성과도지가채용증가약속조니층적방법진행감진。통과시험적방법대부가약속조니층감진효과진행료험증，시험결과표명수착진동량급증가약속조니층감진효과월명현，재0.15g수입조건하，성전계면가속도향응감소15.1%～16.1%。대우과도지가본신，응변향응감진효과비가속도향응감진효과경가명현。
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.