摘要
为既能提高航天器排热能力,又能降低排热系统质量,提出了单相流体回路、蓄冷单相流体回路、热泵单相流体回路、蓄冷热泵回路4种排热方案,计算了各方案排热能力和系统质量构成。与单相流体回路相比,在给定条件下,采用蓄冷热泵回路可减少辐射器面积69.9%,降低排热系统质量53.5%。而蓄冷单相流体回路可减少辐射器面积56.0%,降低排热系统质量48.8%。结果表明:蓄冷方案可以有效解决航天器短时大排热功率问题。
Four heat rejection systems designed to enhance the spacecraft heat rejection rate for short intervals with the lightest possible system were a single phase loop, a cold storage-single phase loop, a heat pump-single phase loop, and a cold storage-heat pump loop. The four systems were evaluated based on heat rejection capacity relative to the system mass. Compared to the single phase loop, for the given design conditions, the cold storage-heat pump loop radiator area was reduced by 69.9% and the system weight was reduced by 53.5%. The radiator area and weight of the cold storage-single phase loop were 56.0% and 48.8% less than those of the single phase loop. The results indicate that the cold storage-heat pump loop provides the best heat rejection rate for the minimum mass.
出处
《清华大学学报（自然科学版）》
EI
CAS
CSCD
北大核心
2004年第8期1130-1133,共4页
Journal of Tsinghua University(Science and Technology)
基金
国家"八六三"高技术项目(863-2-2-3-3)
关键词
航天器
热控
蓄冷
相变材料
强化排热
热管理
space craft
thermal control
cold storage
phase change material
heat rejection enhancement
thermal management
