张欢,刘海平,刘天雄,向树红,张庆明.航天器火工冲击载荷减缓设计及验证[J].装备环境工程,2015,12(3):34-41. ZHANG Huan,LIU Hai-ping,LIU Tian-xiong,XIANG Shu-hong,ZHANG Qing-ming.Design and Verification of Pyrotechnic Shock Reduction Scheme of Spacecraft[J].Equipment Environmental Engineering,2015,12(3):34-41.
航天器火工冲击载荷减缓设计及验证
Design and Verification of Pyrotechnic Shock Reduction Scheme of Spacecraft
投稿时间:2015-02-13  修订日期:2015-06-15
DOI:10.7643/issn.1672-9242.2015.03.006
中文关键词:  火工冲击环境防护  有限元分析  航天器  缓冲方案
英文关键词:pyrotechnic shock environment protection  FEA  spacecraft  shock reduction schemes
基金项目:
作者单位
张欢 北京空间飞行器总体设计部,北京 100094 
刘海平 北京空间飞行器总体设计部,北京 100094 
刘天雄 北京空间飞行器总体设计部,北京 100094 
向树红 北京卫星环境工程研究所,北京 100094 
张庆明 北京理工大学 爆炸科学与技术国家重点实验室,北京 100081 
AuthorInstitution
ZHANG Huan Beijing Institute of Spacecraft System Engineering, Beijing 100094, China 
LIU Hai-ping Beijing Institute of Spacecraft System Engineering, Beijing 100094, China 
LIU Tian-xiong Beijing Institute of Spacecraft System Engineering, Beijing 100094, China 
XIANG Shu-hong Beijing Institute of Spacecraft Environment Engineering, Beijing 100094, China 
ZHANG Qing-ming State Key Laboratory of Explosion Science and Technology, Beijing Institute of Technology, Beijing 100081, China 
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中文摘要:
      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 dB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。
英文摘要:
      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.
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