星箭界面整星隔振设计及减振效果验证

Semi-active and passive design for whole-spacecraft vibration isolation and its validation by engineering test

星箭界面减振设计对改善卫星发射时的动力学环境具有重要意义。文章设计串联式磁流变阻尼隔振平台和并联式黏滞阻尼隔振平台,并对这2种隔振平台基于某中型卫星模型开展整星系统级隔振性能的工程试验研究,通过减振特性对比分析评估它们的减振效果。结果显示:串联式磁流变阻尼隔振平台3方向减振效果均较好,质量控制满足设计要求,但会改变系统固有频率;并联式黏滞阻尼隔振平台对系统结构质量和固有频率的影响均较小,x向减振效果较好,但y向、z向减振效果不理想,须进一步优化系统参数。研究结果可为整星隔振的实际工程应用提供依据。

The isolation of the vibrations of satellite and rocket systems is important to improve the vibration environment of the satellite in the launch stage.In order to suppress the vibration of the satellites,the vibration isolation platforms with a serial magnetorheological damper and with a parallel viscous damper are designed,respectively.Based on the middle-sized satellite specimen,a test system is built for validating the whole-spacecraft’s vibration isolation effect.It is shown that with the magnetorheological damper,a fairly satisfactory reduction of the vibration is realized with a certain mass control but at a price of the natural frequency of the system being changed;while the parallel viscous damper performs fairly well in x direction,yet brings about no significant difference in y and z directions.The result provides a basis for the practical engineering application of the whole-spacecraft vibration isolation.