航天器火工冲击载荷减缓设计及验证

目的研究航天器火工冲击缓冲方案,降低火工冲击对航天器上设备的影响。方法根据火工冲击环境防护设计原则设计3种系统级缓冲方案,由NASTRAN软件进行响应预示,用星箭分离局部结构解锁分离试验数据进行验证及模型修正。结果在星箭连接界面增加间断面的加速度响应最大衰减量为62%,增加复杂构型结构的加速度响应最大衰减量为82%,采用冲击隔离的加速度响应最大衰减量为60%。结论在星箭连接界面增加间断面、复杂构型结构或减小星箭界面接触面积均有一定的缓冲效果,系统缓冲设计时应综合考虑质量、结构连接刚度、缓冲效果、卫星状态、运载火箭状态约束等条件。冲击响应预示计算结果与试验结果基本吻合(在±6 d B内),表明这种预示方法能够较准确预示某卫星结构火工冲击响应。

Design and Verification of Pyrotechnic Shock Reduction Scheme of Spacecraft

Objective To study pyrotechnic shock reduction schemes for the spacecraft, and reduce the influence of pyrotechnic shock on the devices mounted in the spacecraft. Methods Three pyrotechnic shock reduction schemes were designed based on the principles of pyrotechnic shock reduction, prediction of shock response was made by NASTRAN software, and validation and model modification were conducted using the separation test data of local joint structure of satellite and launch vehicle. Results The maximum decrease of acceleration response was 62% by increasing the interfaces between satellite and launch vehicle, 86% by inserting a complex structure between satellite and launch vehicle, and 60% by decreasing the contact area. Conclusion Certain pyrotechnic shock reduce effect can be achieved by increasing the interfaces, inserting a complex structure or decreasing the contact area between satellite and launch vehicle. Mass, stiffness of joint structure, pyrotechnic shock reduction effect, and the satellite and launch vehicle status restrictions are factors to be considered when designing the system pyrotechnic shock reducing schemes.