低温推进剂加注系统置换介质的相似性分析
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摘要
为了研究新一代航天推进系统低温推进剂加注系统的气体置换流程特性,采用数值模拟的方法,对置换介质的流动过程进行了模拟和分析,重点考察低温液体增压罐的工作压力、气路调节阀开度对于系统中流动状态和流量及压力调节的影响,并分别以氢、氮作为介质对系统内的流动特性进行计算,分析置换过程中流量调节的氮氢相似性。结果显示,氮气置换系统所得的流量压力调节规律与氢气置换系统在影响因素和变化趋势方面是相似的;但是,在相同的液体储罐增压工作压力和调节阀开度下,氢气系统内的最大流速可达氮气系统内最大流速的5倍,考虑到氢气系统的安全性要求,精确的流量调节策略还需要根据实际氢的置换测试结果来进行确定。
To study the flow characteristics of gas replacement process in the cryogenic propellant loading system for novel spacecraft propulsion systems,numerical modeling method was adopted to simulate the flowing process of replacement gas. The effects of the operating pressure of self-pressurized liquid tank and the opening of gas control valve on the flow status,flowing rate and pressure adjustment were analyzed. The flow characteristics of the system with replacement medium GH2 and GN2 were then calculated to analyze the similarity between them of gas replacement process. The results show that the influencing factors and trends for the pressure control of nitrogen system are similar to those for hydrogen system. However,the maximum velocity in the hydrogen system can be 5 times higher than that in the nitrogen system under the operating conditions with the same pressure of liquid tank and the same opening of control valve. Thus,for safe operation of the hydrogen system,the accurate adjustment strategy of hydrogen system should be supported by further measurement work on the gas replacement with hydrogen.
To study the flow characteristics of gas replacement process in the cryogenic propellant loading system for novel spacecraft propulsion systems,numerical modeling method was adopted to simulate the flowing process of replacement gas. The effects of the operating pressure of self-pressurized liquid tank and the opening of gas control valve on the flow status,flowing rate and pressure adjustment were analyzed. The flow characteristics of the system with replacement medium GH2 and GN2 were then calculated to analyze the similarity between them of gas replacement process. The results show that the influencing factors and trends for the pressure control of nitrogen system are similar to those for hydrogen system. However,the maximum velocity in the hydrogen system can be 5 times higher than that in the nitrogen system under the operating conditions with the same pressure of liquid tank and the same opening of control valve. Thus,for safe operation of the hydrogen system,the accurate adjustment strategy of hydrogen system should be supported by further measurement work on the gas replacement with hydrogen.
引文
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[13]张永敬.战略导弹液体推进剂加注定量方式的改进[J].推进技术,1992,13(5):59-61.(ZHANG Yongjing.The Improvement of Quantitative Filling Method of Liquid Propellant in a Strategic Missile[J].Journal of Propulsion Technology,1992,13(5):59-61.)
[14]马鸿武,杨金岩,王衍文.液体火箭推进剂加注模拟仿真系统的设计与实现[J].推进技术,1993,14(1):46-50.(MA Hong-wu,YANG Jin-yan,WANG Yanwen.The Design and Implementation of Simulation System of Propellant Filling in Liquid Rocket[J].Journal of Propulsion Technology,1993,14(1):46-50.)
[15]杨世铭,陶文铨.传热学[M].北京:高等教育出版社,1998.
[16]陆亚俊,马最良,邹平华.暖通空调(第二版)[M].北京:中国建筑工业出版社,2007.
[17]Paul Wing.Determining and Using the Control Valve Pressure Recovery Factor[J].Instrumentation Technology,1979,26(8):55-59.
[18]Driskell L.Control Valve Sizing with ISA Formulas[J].Instrumentation Technology,1974,21(7):33-48.
[2]吴文跃.空间站的在轨推进剂再加注问题[J].推进技术,1988,9(2):50-56.(WU Wen-yue.The Problem of on-Orbit Propellant Refueling for Space Stations[J].Journal of Propulsion Technology,1988,9(2):50-56.)
[3]Moore W I,Arnold R J.Failure of Liquid Oxygen Filling System of Saturn V[J].Missiles and Space Vehicles,1979,2:69-74.
[4]瓦费林·尼亚波部拉诺夫.液体低温系统[M].北京:低温工程编辑部,1993.
[5]符锡理.运载火箭液氢液氧低温推进剂加注技术[J].低温工程,1995,(6):1-8.
[6]符锡理.运载火箭发射场液氮加注系统[J].低温工程,1995,(1):7-11.
[7]张亮亮,陈虹,高旭,等.氢箱置换过程中气体流量控制技术试验研究[J].低温与超导,2015,(10):17-21.
[8]王红雨.液氢加注系统的气体置换方法探讨[J].低温与特气,2007,25(6):20-22.
[9]何明飞.氢气置换用量及用时计算[J].低温工程,2010,(6):46-49.
[10]叶欣,张青,张邦双.液氢加注系统氢气置换计算[J].低温工程,2014,(6):38-41.
[12]朱子勇,孙万民,王占林.某试验台LH2贮箱气体置换过程数值模拟[J].火箭推进,2011,37(6):52-60.
[13]张永敬.战略导弹液体推进剂加注定量方式的改进[J].推进技术,1992,13(5):59-61.(ZHANG Yongjing.The Improvement of Quantitative Filling Method of Liquid Propellant in a Strategic Missile[J].Journal of Propulsion Technology,1992,13(5):59-61.)
[14]马鸿武,杨金岩,王衍文.液体火箭推进剂加注模拟仿真系统的设计与实现[J].推进技术,1993,14(1):46-50.(MA Hong-wu,YANG Jin-yan,WANG Yanwen.The Design and Implementation of Simulation System of Propellant Filling in Liquid Rocket[J].Journal of Propulsion Technology,1993,14(1):46-50.)
[15]杨世铭,陶文铨.传热学[M].北京:高等教育出版社,1998.
[16]陆亚俊,马最良,邹平华.暖通空调(第二版)[M].北京:中国建筑工业出版社,2007.
[17]Paul Wing.Determining and Using the Control Valve Pressure Recovery Factor[J].Instrumentation Technology,1979,26(8):55-59.
[18]Driskell L.Control Valve Sizing with ISA Formulas[J].Instrumentation Technology,1974,21(7):33-48.
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