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NASA-LLIS-3077
Lessons Learned - Design for Operability; Door Penetration Thermal Barrier Design
Year: 2010
Abstract: Abstract:
Door interfaces require a thermal seal that must be flexible and soft yet handle temperatures as high as 2000 degrees Fahrenheit. Silica-glassbased fabrics are primarily used for this application. Heat cycles on these materials tend to make them stiff and brittle, resulting in parts that are susceptible to damage from both flight and processing operations. New ideas to address this design requirement need to be explored. For the Space Shuttle Program, configuration changes were made that greatly improved process operability, but the basic design has remained unchanged. From stand-point of flight safety, a single thermal barrier does not supply redundancy, and that risk must be accepted.
Door interfaces require a thermal seal that must be flexible and soft yet handle temperatures as high as 2000 degrees Fahrenheit. Silica-glassbased fabrics are primarily used for this application. Heat cycles on these materials tend to make them stiff and brittle, resulting in parts that are susceptible to damage from both flight and processing operations. New ideas to address this design requirement need to be explored. For the Space Shuttle Program, configuration changes were made that greatly improved process operability, but the basic design has remained unchanged. From stand-point of flight safety, a single thermal barrier does not supply redundancy, and that risk must be accepted.
Subject: Entry Systems
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| contributor author | NASA - National Aeronautics and Space Administration (NASA) | |
| date accessioned | 2017-09-04T15:05:58Z | |
| date available | 2017-09-04T15:05:58Z | |
| date copyright | 05/17/2010 | |
| date issued | 2010 | |
| identifier other | LDMGFDAAAAAAAAAA.pdf | |
| identifier uri | https://yse.yabesh.ir/std/handle/yse/3460 | |
| description abstract | Abstract: Door interfaces require a thermal seal that must be flexible and soft yet handle temperatures as high as 2000 degrees Fahrenheit. Silica-glassbased fabrics are primarily used for this application. Heat cycles on these materials tend to make them stiff and brittle, resulting in parts that are susceptible to damage from both flight and processing operations. New ideas to address this design requirement need to be explored. For the Space Shuttle Program, configuration changes were made that greatly improved process operability, but the basic design has remained unchanged. From stand-point of flight safety, a single thermal barrier does not supply redundancy, and that risk must be accepted. | |
| language | English | |
| title | NASA-LLIS-3077 | num |
| title | Lessons Learned - Design for Operability; Door Penetration Thermal Barrier Design | en |
| type | standard | |
| page | 2 | |
| status | Active | |
| tree | NASA - National Aeronautics and Space Administration (NASA):;2010 | |
| contenttype | fulltext | |
| subject keywords | Entry Systems | |
| subject keywords | Ground processing and manifesting |