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Identification and management of filament-wound case stiffness parameters
| Content Provider | NASA Technical Reports Server (NTRS) |
|---|---|
| Author | Rheinfurth, M. Verderaime, V. |
| Copyright Year | 1983 |
| Description | The high specific strength and the high specific modules made graphite epoxy laminate an expedient material substitute for the Shuttle Solid Rocket Motor steel case to substantially increase the payload performance without increasing the composite case axial growth during thrust build up which was constrained to minimize liftoff excitation effects on existing structural elements and interfaces. Parameters associated with axial growth were identified for quality and manufacturing controls. Included is an innovative method for experimentally verifying extensional elastic properties on a laminate pressurized test bottle. |
| File Size | 761728 |
| Page Count | 19 |
| File Format | |
| Alternate Webpage(s) | http://archive.org/details/NASA_NTRS_Archive_19830008129 |
| Archival Resource Key | ark:/13960/t07x16w6p |
| Language | English |
| Publisher Date | 1983-01-01 |
| Access Restriction | Open |
| Subject Keyword | Composite Materials Housings Space Shuttles Quality Control Solid Propellant Rocket Engines Thrust Distribution Elastic Properties Filament Winding Laminates Spacecraft Launching Pressurizing Ntrs Nasa Technical Reports Server (ntrs) Nasa Technical Reports Server Aerodynamics Aircraft Aerospace Engineering Aerospace Aeronautic Space Science |
| Content Type | Text |
| Resource Type | Technical Report |
