低温推进剂地面加注系统冷量利用方案分析  

Analysis on Utilization of Cooling Capacity for Ground Loading System of Cryogenic Propellants

作　　者：谢福寿[1] 雷刚 王磊[1] 厉彦忠[1,2] XIE Fu-shou LEI Gang WANG Lei LI Yan-zhong(School of Energy and Power Engineering, Xi＇ an Jiaotong University, Xi＇ an 710072, 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710072 [2]航天低温推进剂技术国家重点实验室,北京100028

出　　处：《宇航学报》2016年第12期1507-1512,共6页Journal of Astronautics

基　　金：国家自然科学基金(51376142);航天低温推进剂技术国家重点实验室开放课题(SKLTSCP1610)

摘　　要：为了降低低温推进剂损耗,提高利用效率,降低发射成本,提出了4套运载火箭低温推进剂地面加注系统的冷量利用方案。基于热力学原理,建立了非稳态数学模型,并以能量品质高低作为衡量方案优劣的标准,通过实例计算对比分析了各个冷量利用方案的可行性。研究得出4套冷量利用方案从热力学角度出发都是可行的,其中方案A和方案D最优,方案A可应用在目前现有低温推进剂地面加注系统中,而方案D则可应用于未来重型运载火箭低温推进剂地面加注系统之中。In order to decrease loss of cryogenic propellants, enhance utilization rate, reduce launch cost, four schemes of cooling capacity utilization are proposed. Based on the principle of thermodynamics, unsteady mathematical model is developed. With energy quality as criteria of evaluating schemes, each scheme of cooling capacity utilization is comparatively analyzed by example calculation. The study shows that four schemes of cooling capacity utilization are all feasible from the angle of thermodynamics, of which the scheme A and the scheme D are optimal. The scheme A can be applied into the present ground loading systems of cryogenic propellants, and the scheme D can be applied into the future ground loading systems of cryogenic propellants for heavy launch vehicle.

关 键 词：运载火箭 低温推进剂 冷量利用 能量品质 热力学 

分 类 号：V511.6[航空宇航科学与技术—航空宇航推进理论与工程]