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NASA-LLIS-0177
Lessons Learned - Solid Rocket Motor (SRM) O-ring
Year: 1992
Abstract: Description of Driving Event:
The o-ring used in the SRM case joint is critical to the sealing of the joint, yet is not designated as a critical process. The adequacy of o-ring processing and quality control is questionable even though a number of o-rings in bonded storage were thoroughly analyzed and tested as part of 51-L failure analysis effort and found to be acceptable. The manufacturing process included delivery of the final o-ring rubber material to where the material is cut to the proper lengths and a scarf joint is made. This manufacturing process is a potential problem area as seen by repairs of inclusions and voids in the rubber delivered.
The o-ring used in the SRM case joint is critical to the sealing of the joint, yet is not designated as a critical process. The adequacy of o-ring processing and quality control is questionable even though a number of o-rings in bonded storage were thoroughly analyzed and tested as part of 51-L failure analysis effort and found to be acceptable. The manufacturing process included delivery of the final o-ring rubber material to where the material is cut to the proper lengths and a scarf joint is made. This manufacturing process is a potential problem area as seen by repairs of inclusions and voids in the rubber delivered.
Subject: Flight Equipment
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| contributor author | NASA - National Aeronautics and Space Administration (NASA) | |
| date accessioned | 2017-09-04T16:06:58Z | |
| date available | 2017-09-04T16:06:58Z | |
| date copyright | 33900 | |
| date issued | 1992 | |
| identifier other | BHZCQCAAAAAAAAAA.pdf | |
| identifier uri | https://yse.yabesh.ir/std/handle/yse/70201 | |
| description abstract | Description of Driving Event: The o-ring used in the SRM case joint is critical to the sealing of the joint, yet is not designated as a critical process. The adequacy of o-ring processing and quality control is questionable even though a number of o-rings in bonded storage were thoroughly analyzed and tested as part of 51-L failure analysis effort and found to be acceptable. The manufacturing process included delivery of the final o-ring rubber material to where the material is cut to the proper lengths and a scarf joint is made. This manufacturing process is a potential problem area as seen by repairs of inclusions and voids in the rubber delivered. | |
| language | English | |
| title | NASA-LLIS-0177 | num |
| title | Lessons Learned - Solid Rocket Motor (SRM) O-ring | en |
| type | standard | |
| page | 2 | |
| status | Active | |
| tree | NASA - National Aeronautics and Space Administration (NASA):;1992 | |
| contenttype | fulltext | |
| subject keywords | Flight Equipment | |
| subject keywords | Industrial Operations | |
| subject keywords | Risk Management/Assessment |