Mathematical model and experimental results for cryogenic densification and sub-cooling using a submerged cooling source

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• 作者：J.K. Partridge^a ; ^{jonathan.k.partridge@nasa.gov} ; J.W. Tuttle^b ; W.U. Notardonato^a ; W.L. Johnson^a
• 关键词：Cryogenic densification
• 刊名：Cryogenics
• 出版年：2012
• 期刊代码：45_00112275
• 类别：et
• 出版时间：April-June, 2012
• 卷：52
• 期：4-6
• 页码：262-267
• 文件大小：2046 K

摘要

Among the many factors that determine overall rocket performance, propellant density is important because it affects the size of the rocket. Thus, in order to decrease the size of a rocket, it may be desirable to increase the density of propellants. This study analyzes the concept of increasing the propellant density by employing a cooling source submerged in the liquid propellant. A simple, mathematical model was developed to predict the rate of densification and the propellant temperature profile. The mathematical model is generic and applicable to multiple propellants. The densification rate was determined experimentally by submerging a cooling source in liquid oxygen at constant positive pressure, and measuring the time rate of change in temperature with respect to vertical position. The results from the mathematical model provided a reasonable fit compared to experimental results.