Hydrogen/Oxygen Propellant Densifier Using a Two‐Stage Pulse Tube Cryocooler
Hydrogen/Oxygen Propellant Densifier Using a Two‐Stage Pulse Tube Cryocooler
复制标题
DOI：
10.1063/1.1774869
复制
发表时间：
2004-07
期刊：
影响因子：
--
通讯作者：
C. Nguyen;A. J. Yeckley;A. Culler;M. Haberbusch;R. Radebaugh
中科院分区：
文献类型：
--
作者：
C. Nguyen;A. J. Yeckley;A. Culler;M. Haberbusch;R. Radebaugh
推出了一种正在申请专利的独特热声推进剂致密剂，可同时致密用于航空航天器的液氢和液氧推进剂。热声致密器由两级脉冲管制冷机组成，使用氦气作为工作流体，运行频率为 30 Hz。极其可靠的脉冲管没有移动部件，采用水冷，并采用声学驱动。脉冲管由热声斯特林热机 (TASHE) 和线性挠性轴承压缩机驱动。实验室原型是在俄亥俄州米兰的 Sierra Lobo, Inc. 工厂设计、制造和测试的。独特的设计特点包括可轻松测试低温回热器材料的可拆卸第二级和先进的后冷却器设计几何形状。将介绍系统描述，并将脉冲管性能的实验数据与 REGEN 3.2 和其他分析预测进行比较。
A unique, patent pending, thermoacoustic propellant densifier, that simultaneously densifies liquid hydrogen and liquid oxygen propellants for aerospace vehicles is introduced. The thermoacoustic densifier consists of a two‐stage pulse tube cryocooler that operates at 30 Hz using helium as the working fluid. The extremely reliable pulse tube has no moving parts, is water cooled, and is acoustically driven. The pulse tube has been driven by a Thermoacoustic Stirling Heat Engine (TASHE) and a linear flexure bearing compressor. A laboratory prototype was designed, fabricated, and tested at the Sierra Lobo, Inc. facility in Milan, Ohio. Unique design features include a removable 2nd stage for easy testing of low temperature regenerator materials and an advanced aftercooler design geometry. A system description will be presented and experimental data of the pulse tube performance will be compared with REGEN 3.2 and other analytical predictions.