Analyses of Cryogenic Propellant Tank Pressurization based upon Ground Experiments
Analyses of Cryogenic Propellant Tank Pressurization based upon Ground Experiments
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DOI：
10.2514/6.2012-5199
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发表时间：
2012-09
期刊：
影响因子：
--
通讯作者：
C. Ludwig;M. Dreyer
中科院分区：
文献类型：
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作者：
C. Ludwig;M. Dreyer
低温推进剂火箭的增压系统需要机载加压气体。本研究的目的是分析加压气体温度对降低发射装置质量所需加压气体质量的影响。首先，进行了地面实验，以研究加压过程中的加压气体进口温度的影响。其次，对小型两级入轨（TSTO）运载火箭的低温上面级进行了系统研究，重点是压力气体温度对推进剂管理系统质量的影响。一个重要的实验结果是，对于蒸发推进剂作为加压气体，最高适用气体温度是最好的，以减少所需的加压气体，但条件是所有的加压线冷却。此外，氦的使用对于降低加压气体质量是非常有利的。同样重要的是，在加压结束后立即发生压降。从系统分析得出的结论是，蒸发的推进剂和氦气加压气体温度的增加导致总的推进剂管理系统的质量减少，尽管应用外部氦气容器。
The pressurization system of cryogenic propellant rockets requires on-board pressurant gas. The objective of this study was to analyze the influence of the pressurant gas temperature on the required pressurant gas mass in terms of lowering the launcher mass. First, ground experiments were performed in order to investigate the pressurization process with regard to the influence of the pressurant gas inlet temperature. Second, a system study for the cryogenic upper stage of a small Two Stage to Orbit (TSTO) launch vehicle was performed with focus on the influence of the pressurant gas temperature on the propellant management system mass. One important experimental result is that for evaporated propellant as pressurant gas, the maximum applicable gas temperature is best for reducing the needed pressurant gas, but on condition that all pressurization lines are chilled down. Moreover, the use of helium is very advantageous with regard to lowering the pressurant gas mass. Also significant is that an immediate pressure drop occurred after the pressurization end. The conclusion drawn from the system analysis is that an increased evaporated propellant and helium pressurant gas temperature resulted in a decrease of the total propellant management system mass, despite the application of external helium vessels.