新型多层绝热材料组合包覆工艺及其绝热性能
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摘要
在深空探测过程中,利用多层隔热材料是降低低温推进剂蒸发量的主要隔热方式。但多层绝热材料其结构较为复杂,加工、安装和使用条件都非常特殊,决定了其在深空探测应用中具有一定的难度。本文首先从工艺特性的角度,通过与常规包覆方法进行对比,对多层绝热材料在贮箱表面的组装工艺进行探究,采用尼龙搭扣带、胶钉枪开发了一套效能高、经济性好的新型固定方法,通过高真空测试平台对该多层绝热包覆工艺进行测试并分析其绝热效应的影响。结果表明:使用该包覆工艺成型的多层绝热组件当量热导率可以达到1. 1 mW/(m·K),且具有较小的漏热量,系统稳定性好。
In the process of the deep space explorations,the application of multilayer insulation materials has been extensively recognized as the most common method of realizing heat insulation in propellant tanks. Compared to other materials,however,the structure in which multilayer insulation materials are made is relatively complex.Additionally,there are also a set of specialized criteria to which its processing,installation,and application are constrained. This paper explored the assembly process in the practical processing of multilayer insulation materials by developing a new and standardized mode of using Velcro straps and glue guns. Next,the performance of this process was recorded and compared with the conventional winding coating process. Subsequently,the multilayer insulation coating process was tested and the influence of adiabatic effect was analyzed. Through the high vacuum test platform,the equivalent thermal conductivity of the multilayer insulation components formed by this process could reach 1. 1 mW/(m·K)with smaller heat leakage and system stability.
In the process of the deep space explorations,the application of multilayer insulation materials has been extensively recognized as the most common method of realizing heat insulation in propellant tanks. Compared to other materials,however,the structure in which multilayer insulation materials are made is relatively complex.Additionally,there are also a set of specialized criteria to which its processing,installation,and application are constrained. This paper explored the assembly process in the practical processing of multilayer insulation materials by developing a new and standardized mode of using Velcro straps and glue guns. Next,the performance of this process was recorded and compared with the conventional winding coating process. Subsequently,the multilayer insulation coating process was tested and the influence of adiabatic effect was analyzed. Through the high vacuum test platform,the equivalent thermal conductivity of the multilayer insulation components formed by this process could reach 1. 1 mW/(m·K)with smaller heat leakage and system stability.
引文
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[10]闫指江,吴胜宝,赵一搏,等.低温贮箱组合绝热材料隔热性能测试试验研究[J].载人航天,2017,23(1):56-60.
[11]FOURIER J B J,FREEMAN A. Analytical theory of heat[M]. Dover Publications Inc. New York,1952.
[12]MCINTOSH G E. Layer by layer MLI calculation using a separated mode equation[J]. Advances in Cryogenic Engineering,1994,39B:1683-1690.
[2]闵桂荣.卫星热控制技术[M].北京:宇航出版社,1991.
[3]CUNNINGTON G,TIEN C. A study of heat-transfer processes in multilayer insulations[J]. Thermophysics Applications to Thermal Design of Spacecraft,1969,23:111-126.
[4]江经善.多层隔热材料及其在航天器上的应用[J].宇航材料工艺,2000,30(4):17-25.
[5]郭舜.多层隔热系统[J].中国空间科学技术,1980.
[6]HATAKENAKA R,MIYAKITA T,SUGITA H,et al.Development and testing of a zero stitch MLI blanket using plastic pins for space use[J]. Cryogenics,2014,64:121-134.
[7]朱浩唯.变密度真空多层绝热的理论与实验研究[D].上海交通大学,2013.
[8]STIMPSON L D,JAWORSKI W. Effects of overlaps,stitches,and patches on multilayer insulation.[J]. Aiaa Journal,1972.
[9]闫指江,吴胜宝,赵一博,等.应用于低温推进剂在轨贮存的组合绝热材料综述[J].载人航天,2016,22(3):293-297.
[10]闫指江,吴胜宝,赵一搏,等.低温贮箱组合绝热材料隔热性能测试试验研究[J].载人航天,2017,23(1):56-60.
[11]FOURIER J B J,FREEMAN A. Analytical theory of heat[M]. Dover Publications Inc. New York,1952.
[12]MCINTOSH G E. Layer by layer MLI calculation using a separated mode equation[J]. Advances in Cryogenic Engineering,1994,39B:1683-1690.