管路布局方式对载人航天器辐射器散热能力的影响分析

摘要

以采取双管路并联结构的载人航天器圆筒辐射器为研究对象,建立了辐射器散热能力数值分析模型,对比分析了不同参数下,并联支路工质相同流动方向和相反流动方向两类布局方式给辐射器散热能力带来的影响,选取的参数包括管路长度、管路进口工质温度和液体工质流量.计算结果表明,在辐射器面板面积和流体回路长度相同的前提下,两类管路布局方式对应的辐射器散热能力存在不可忽视的差别.随着管路长度的增加,入口工质温度的增加,工质流量的减小,工质流向相同的辐射器散热能力越来越高于工质流向相反的辐射器.在文章的参数设定下,工质流向相同的辐射器与工质流向相反的辐射器间最大散热能力差别可达到19.5℅,最小散热能力差别可达到16.7℅.%An unsteady numerical model for heat dissipation potential of manned spacecraft cylinder radiator with two parallel loops was developed. Based on this model, impact of radiator loops layout with same and reverse working liquid flowing direction on radiator heat dissipation potential under different parameters was analyzed,including loop length,working liquid flux and working liquid temperature at loop entrance. According to the calculation results,on the premise of the same plate area and loop length,loops layout could bring non-ignorable difference of heat dissipation potential of radiators.As the loop length is longer, working liquid temperature at loop entrance is higher,or working liquid flux is less,heat dissipation potential of radiator with same working liquid flowing direction is better than that of radiator with reverse working liquid direction. The difference of max heat dissipation potential could be up to 19.5%,and the difference of minimum heat dissipation potential could be up to 16.7%.