Thermodynamic vent system performance testing with subcooled liquid methane and gaseous helium pressurant |
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| Authors: | RH Flachbart LJ Hastings A Hedayat SL Nelson SP Tucker |
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| Affiliation: | 1. Engineering Directorate, NASA Marshall Space Flight Center, Marshall Space Flight Center, Huntsville, AL 35812, USA;2. Alpha Technology Inc., Huntsville, AL 35812, USA;1. Japan Aerospace Exploration Agency, Tsukuba, Ibaraki 305-8505, Japan;2. Japan Aerospace Exploration Agency, Sagamihara, Kanagawa 252-5210, Japan;1. Institute of Refrigerant and Cryogenics, Xi’an Jiaotong University, Xi’an 710049, China;2. State Key Laboratory of Technologies in Space Cryogenic Propellants, Beijing 100028, China;1. Instituto de Cerámica y Vidrio, CSIC, Kelsen 5, 28049 Madrid, Spain;2. Belgian Ceramic Research Centre, Avenue Gouverneur Cornez 4, B-7000 Mons, Belgium;1. College of Aerospace Science and Engineering, National University of Defense Technology, Changsha 410073, Hunan, PR China;2. Department of Energy Sciences, Lund University, Lund 22100, Sweden |
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| Abstract: | LCH4 testing was conducted at the Marshall Space Flight Center using the multipurpose hydrogen test bed (MHTB) to evaluate the performance of a spray-bar thermodynamic vent system (TVS) with subcooled LCH4 and gaseous helium (GHe) pressurant. Thirteen days of testing were performed in November 2006, with total tank heat leak conditions of about 715 W and 420 W at a fill level of approximately 90%. A total of 23 TVS cycles were completed. The TVS successfully controlled the ullage pressure within a prescribed control band but did not maintain a stable liquid saturation pressure. This was likely due to a TVS design not optimized for this particular propellant and test conditions, and possibly due to a large artificially induced heat input directly into the liquid. |
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