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NASA-LLIS-0176
Lessons Learned - Solid Rocket Motor (SRM) Field Joints and Configuration
Year: 1992
Abstract: Description of Driving Event:
The primary reason for the use of the putty in the SRM was to act as a thermal barrier in the joints to prevent o-ring erosion resulting from circumferential hot gas flow during motor firing. Prior to the 51-L mishap, the putty was believed to perform such that it would allow pressure to the primary oring during the SRM ignition transient. Subsequently, it has been found that humidity and temperature enhance the characteristics of putty relative to its pressure holding characteristics. The uncertainty of these characteristic changes directly affected the ability of the field joint to seal.
The primary reason for the use of the putty in the SRM was to act as a thermal barrier in the joints to prevent o-ring erosion resulting from circumferential hot gas flow during motor firing. Prior to the 51-L mishap, the putty was believed to perform such that it would allow pressure to the primary oring during the SRM ignition transient. Subsequently, it has been found that humidity and temperature enhance the characteristics of putty relative to its pressure holding characteristics. The uncertainty of these characteristic changes directly affected the ability of the field joint to seal.
Subject: Flight Equipment
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| contributor author | NASA - National Aeronautics and Space Administration (NASA) | |
| date accessioned | 2017-09-04T18:13:25Z | |
| date available | 2017-09-04T18:13:25Z | |
| date copyright | 33900 | |
| date issued | 1992 | |
| identifier other | HEZCQCAAAAAAAAAA.pdf | |
| identifier uri | http://yse.yabesh.ir/std;jsery=autho162s7D8308/handle/yse/196401 | |
| description abstract | Description of Driving Event: The primary reason for the use of the putty in the SRM was to act as a thermal barrier in the joints to prevent o-ring erosion resulting from circumferential hot gas flow during motor firing. Prior to the 51-L mishap, the putty was believed to perform such that it would allow pressure to the primary oring during the SRM ignition transient. Subsequently, it has been found that humidity and temperature enhance the characteristics of putty relative to its pressure holding characteristics. The uncertainty of these characteristic changes directly affected the ability of the field joint to seal. | |
| language | English | |
| title | NASA-LLIS-0176 | num |
| title | Lessons Learned - Solid Rocket Motor (SRM) Field Joints and Configuration | en |
| type | standard | |
| page | 2 | |
| status | Active | |
| tree | NASA - National Aeronautics and Space Administration (NASA):;1992 | |
| contenttype | fulltext | |
| subject keywords | Flight Equipment | |
| subject keywords | Hardware | |
| subject keywords | Test & Verification |