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运载火箭低温贮箱采用大面积冷屏与多层隔热材料组成的复合结构可以有效减少低温推进剂蒸发损耗,延长低温推进剂在轨贮存时间。通过建立多层隔热材料耦合90 K大面积冷屏的传热模型,获得了引入大面积冷屏后对多层隔热材料层间温度分布及热流密度影响的变化规律,对比了采用冷屏技术和直接对液氢采用主动制冷两种方式,同等条件下采用冷屏在主动制冷系统重量和功耗方面可分别节省60%和64%。研究了低温推进剂不同在轨贮存时间和冷屏安装在多层隔热材料中不同位置时热管理系统重量和功耗成本,以成本最小为目标获得了90 K冷屏布局最优化设计方法。
The use of a composite structure of large-area cold-screen and multi-layer thermal insulation materials for cryogenic storage tanks of launch vehicles can effectively reduce the evaporation loss of low-temperature propellants and prolong the storage time of cryogenic propellants in orbit. By establishing the heat transfer model of 90 K large area cold screen coupled with multi-layer thermal insulation material, the variation of temperature distribution and heat flux density between multi-layer insulation materials after introducing large area cold-screen was obtained. Technology and the direct use of liquid hydrogen for active refrigeration in two ways, under the same conditions using cold-screen active cooling system in terms of weight and power consumption can save 60% and 64%. The weight and power cost of the thermal management system when different cryogenic propellants are stored in different positions on the rails and the cold screens are installed in different positions in the multilayer thermal insulation materials are studied. The 90 K cold screen layout optimization design method is obtained with the goal of minimizing the cost.