摘要
针对航天器大面积热控辐射器流体管遭受空间碎片撞击概率高的特点,提出了采取热管辐射器和加强流体管路自身防护的改进措施。通过开展所在轨道的碎片环境分析和撞击风险评估,确定了流体管需要满足的防护要求。随后通过超高速撞击试验,获得了流体管路的临界直径,并在此基础上开展了热控辐射器流体管路的击穿风险失效评估。结果表明:航天器热控辐射器流体管路的非击穿概率(PNP)高于指标要求,保证了长寿命需求,设计方法可为其它热控辐射器碎片防护设计提供参考。
In response to the high probability of space debris impact on the fluid pipes of the large area thermal control radiator of spacecraft,the protective design measures are proposed by adopting the heat pipe radiator and strengthening the self-protection of the fluid pipe.By conducting the orbital debris environment analysis and impact probability evaluation,the protective requirement that the fluid pipes needs to meet have been determined.Subsequently,the critical diameter value of fluid pipes is obtained through hypervelocity impact tests.And based on it,a breakdown risk failure assessment of the fluid pipes of the compartment thermal control radiator is conducted.The results show that the non breakdown probability(PNP)of the fluid pipes of thermal control radiator is higher than the requirement,ensuring a long life.The design method can provide reference for the debris protection design of other types of thermal control radiators.
作者
韩海鹰
赵亮
郑世贵
曹剑峰
付杨
HAN Haiying;ZHAO Liang;ZHENG Shigui;CAO Jianfeng;FU Yang(Beijing Institute of Spacecraft System Engineering,Beijing 100094,China)
出处
《航天器工程》
CSCD
北大核心
2023年第4期60-64,共5页
Spacecraft Engineering
关键词
航天器
热控辐射器
空间碎片防护
spacecraft
thermal control radiator
space debris protection
