中文摘要：

星箭分离冲击是航天器所经历的较为严酷的力学环境之一。为了预示星箭分离面的径向冲击响应,基于星箭对接框承受轴对称径向载荷的假设,提出一种简化的轴对称圆环振动模型,采用有限元法数值验证简化模型的有效性。采用星箭对接框的简化圆环方法,分析包带预紧力、对接框主要结构参数与冲击响应的关系,以及包带和卡块质量对冲击的影响。分析结果表明,分离面径向冲击随着包带预紧力增加而增大;考虑包带和卡块质量的影响,延迟对接框应变能释放时间。在保证星箭可靠连接和分离的前提下,减小包带预紧力、延长对接框应变能释放时间,是降低分离面径向冲击的有效手段。

英文摘要：

The shock induced by satellite-rocket separation is one of the severe mechanical environments that the spacecraft has to experience.An axisymmetric circular ring vibration model is established to analyze the radial shock response of the satellite-rocket separation interface during separation process.By using this model validated by finite element analysis,the influence on the radial shock response concerning band pre-tightening force,structural parameter of the interface ring,mass of clamp band and fixture block are discussed.It is shown that the radial shock of the satellite-rocket separation interface increases with the increase of the pre-tightening force of clamp band.Considering the mass of the band and fixture block,the release time of the strain energy stored in the interface ring is prolonged.In ensuring the reliable satellite-rocket connection and separation,it is an effective means of decreasing the interface shock to reduce the pre-tightening force of clamp band and to delay the release time of strain energy of the interface connection structures.