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NASA-LLIS-0966
Lessons Learned – Space Shuttle Main Engine (SSME): Fuel System Oscillations
Year: 1995
Abstract: Description of Driving Event:
After the main fuel valve starts to open, three oxidizer valves in the SSME are separately subjected to a series of position commands to precisely control oxidizer system priming times for the three combustors. The first oxidizer valve to be commanded is the fuel preburner oxidizer valve (FPOV). After a delay of 0.100 seconds, the FPOV is ramped to 56 percent open at its maximum skew rate. At 0.72 seconds, the FPOV is given a "notch" command to close about 10%. Just prior to the third fuel system oscillation, second "notch" command is given.
After the main fuel valve starts to open, three oxidizer valves in the SSME are separately subjected to a series of position commands to precisely control oxidizer system priming times for the three combustors. The first oxidizer valve to be commanded is the fuel preburner oxidizer valve (FPOV). After a delay of 0.100 seconds, the FPOV is ramped to 56 percent open at its maximum skew rate. At 0.72 seconds, the FPOV is given a "notch" command to close about 10%. Just prior to the third fuel system oscillation, second "notch" command is given.
Subject: Configuration Management
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| contributor author | NASA - National Aeronautics and Space Administration (NASA) | |
| date accessioned | 2017-09-04T17:55:43Z | |
| date available | 2017-09-04T17:55:43Z | |
| date copyright | 05/15/1995 | |
| date issued | 1995 | |
| identifier other | FKUEQCAAAAAAAAAA.pdf | |
| identifier uri | http://yse.yabesh.ir/std/handle/yse/178932 | |
| description abstract | Description of Driving Event: After the main fuel valve starts to open, three oxidizer valves in the SSME are separately subjected to a series of position commands to precisely control oxidizer system priming times for the three combustors. The first oxidizer valve to be commanded is the fuel preburner oxidizer valve (FPOV). After a delay of 0.100 seconds, the FPOV is ramped to 56 percent open at its maximum skew rate. At 0.72 seconds, the FPOV is given a "notch" command to close about 10%. Just prior to the third fuel system oscillation, second "notch" command is given. | |
| language | English | |
| title | NASA-LLIS-0966 | num |
| title | Lessons Learned – Space Shuttle Main Engine (SSME): Fuel System Oscillations | en |
| type | standard | |
| page | 2 | |
| status | Active | |
| tree | NASA - National Aeronautics and Space Administration (NASA):;1995 | |
| contenttype | fulltext | |
| subject keywords | Configuration Management | |
| subject keywords | Cryogenic Systems | |
| subject keywords | Ground Equipment | |
| subject keywords | Hardware | |
| subject keywords | Launch Vehicle | |
| subject keywords | Parts Materials & Processes | |
| subject keywords | Safety & Mission Assurance | |
| subject keywords | Spacecraft | |
| subject keywords | Test Article | |
| subject keywords | Test Facility |