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NASA-LLIS-0485
Lessons Learned - Isolate the Propulsion Pressurization System from the Propellant Tanks (1993)
Year: 1996
Abstract: Abstract:
The "most probable cause" of the Mars Observer mission failure was identified as migration of substantial amounts of nitrogen tetroxide oxidizer upstream through the check valves where it condensed on the cold tubing. When the pressurization sequence was executed upon Mars encounter, the liquid oxidizer may have mixed rapidly with fuel in the lines and detonated. The recommendations included (1) preventing hazardous propellant vapor migration and (2) performing thermal analysis of pressurization systems to identify incipient conditions for propellant condensation.
The "most probable cause" of the Mars Observer mission failure was identified as migration of substantial amounts of nitrogen tetroxide oxidizer upstream through the check valves where it condensed on the cold tubing. When the pressurization sequence was executed upon Mars encounter, the liquid oxidizer may have mixed rapidly with fuel in the lines and detonated. The recommendations included (1) preventing hazardous propellant vapor migration and (2) performing thermal analysis of pressurization systems to identify incipient conditions for propellant condensation.
Subject: Bipropellant Propulsion System
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| contributor author | NASA - National Aeronautics and Space Administration (NASA) | |
| date accessioned | 2017-09-04T17:00:37Z | |
| date available | 2017-09-04T17:00:37Z | |
| date copyright | 35411 | |
| date issued | 1996 | |
| identifier other | XPBEQCAAAAAAAAAA.pdf | |
| identifier uri | https://yse.yabesh.ir/std/handle/yse/124107 | |
| description abstract | Abstract: The "most probable cause" of the Mars Observer mission failure was identified as migration of substantial amounts of nitrogen tetroxide oxidizer upstream through the check valves where it condensed on the cold tubing. When the pressurization sequence was executed upon Mars encounter, the liquid oxidizer may have mixed rapidly with fuel in the lines and detonated. The recommendations included (1) preventing hazardous propellant vapor migration and (2) performing thermal analysis of pressurization systems to identify incipient conditions for propellant condensation. | |
| language | English | |
| title | NASA-LLIS-0485 | num |
| title | Lessons Learned - Isolate the Propulsion Pressurization System from the Propellant Tanks (1993) | en |
| type | standard | |
| page | 3 | |
| status | Active | |
| tree | NASA - National Aeronautics and Space Administration (NASA):;1996 | |
| contenttype | fulltext | |
| subject keywords | Bipropellant Propulsion System | |
| subject keywords | Energetic Materials - Explosive/Propellant/Pyrotechnic | |
| subject keywords | Propellant Vapor Diffusion | |
| subject keywords | Spacecraft |