空间燃料贮箱变密度多层绝热结构传热性能研究  

Study on heat transfer performance of insulation structure in space fuel tank

作　　者：王莹[1] 厉彦忠[1,2] 陈鹏玮[1] 马原[1] 王磊[1] Wang Ying Li Yanzhong Chen Pengwei Ma Yuan Wang Lei(Institute of Refrigerating and Cryogenic Engineering,Xi＇ an Jiaotong University, Xi＇ an 710049 ,China State Key Laboratory of Technologies in Space Cryogenic Propellants, Beijing 100028,China)

机构地区：[1]西安交通大学能源与动力工程学院,西安710049 [2]航天低温推进剂技术国家重点实验室,北京100028

出　　处：《低温工程》2016年第5期57-63,共7页Cryogenics

基　　金：航天低温推进剂技术国家重点实验室开放式基金(SKLTSCP1407);陕西省自然科学基础研究计划资助项目(2015JQ5133);陕西省博士后科研项目资助

摘　　要：为了探究变密度多层绝热结构VDMLI层间结构布置对绝热性能的影响,对火箭低温推进剂储罐外的VDMLI结构建立了传热数学模型,并开展了变工况分析,揭示了不同影响因素,包括热边界温度、层数、层密度等对VDMLI绝热性能的影响。研究发现,热边界温度对VDMLI绝热性能以及温度分布有主要影响;层数在40—60即可满足漏热量要求并且整个绝热结构的质量较轻;变密度结构(VDMLI)比定密度(MLI)具有更轻的重量和较好的绝热效果,从内由外依次是低、中、高密度区,且最优变密度分配比例为低密度区层数占总层数的20%,高密度区约占40%,中密度区占33%—36%。研究内容为VDMLI的实际布置提供了可靠的理论支持。Using insulation structure （VDMLI） to control the evaporation of cryogenic propellant is a key approach for the long-term space exploration. In this study, a mathematic analysis model was built to find out the heat transfer law in VDMLI, which could guide us a way to reduce the energy loss and provide theoretical references for improvement and optimization of the system. Different influence factors was considered, including thermal boundary temperature, number of layers, layer density and residual gas between layers. It is found that with the increase of thermal boundary temperature, the heat leakage increases rapidly ; layers in the 40--60 can meet the heat leak and the quality of the insulation structure is relatively light ; VDMLI has less weight and better heat insulation effect than MLI. The optimal proportion of variable density distribution is 20% of the total number of layers in the low density area, and it is about 40% and 33%- 36% in the high density and the medium density respectively.

关 键 词：低温推进剂 VDMLI绝热结构 漏热量 层密度 

分 类 号：TB657[一般工业技术—制冷工程] TB66