星箭分离缓冲设计方法及试验验证研究

Shock isolation of satellite-rocket separation and its test verification

星箭分离冲击环境是指星箭分离时刻火工品起爆作用于卫星结构上产生的高频、高量级的瞬态冲击响应。一般情况下,高频的火工冲击载荷不会造成航天器结构的破坏,但是却能对具有晶振、脆性材料等的精密电子设备造成致命损伤,从而造成航天任务的失败,甚至发生灾难性的事故。因此,卫星系统级缓冲设计对卫星总体设计,改善星上设备冲击环境,从而实现整星减重具有重要意义。针对我国某卫星平台星箭分离时刻星上冲击环境过大的问题,基于冲击波在结构中的传播和衰减特性,提出了缓冲孔、缓冲垫和过渡段三种系统级缓冲方案,星箭分离缩比试验结果表明:本文提出的三种方案有效的提高了冲击载荷过星箭界面的衰减量,从而明显改善了星上的冲击环境,三种缓冲方案可行、有效。

Pyroshock environment of satellite-rocket separation is the high frequency and high level transient response of structure systems to loading induced by the activation of pyrotechnic devices incorporated into the satellite-rocket structure. Typically, pyroshock does not cause satellite structure damage, but it can cause fatal injuries of electronic equipments with crystals and brittle materials, resulting in the failure of the entire mission even catastrophic accidents. Therefore, shock isolation is very importance for improving the shock environment and saving weight of the satellite. This paper shows the pyroshock problem of a satellite platform with primary truss structure. In order to meet the specification for the shock environment of its component, three attenuation means are proposed based on shock pulse transmition. A scaled test, which is designed to simulate satellite-rocket separation process, demonstrates that the three means are feasible and effective.