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Evaluation of a metal fuselage panel selectively reinforced with filamentary composites for space shuttle application
| Content Provider | NASA Technical Reports Server (NTRS) |
|---|---|
| Author | Wennhold, W. F. |
| Copyright Year | 1974 |
| Description | The use of high strength and modulus of advanced filamentary composites to reduce the structural weight of aerospace vehicles was investigated. Application of the technology to space shuttle components was the primary consideration. The mechanical properties for the boron/epoxy, graphite/epoxy, and polyimide data are presented. Structural testing of two compression panel components was conducted in a simulated space shuttle thermal environment. Results of the tests are analyzed. |
| File Size | 70156282 |
| Page Count | 199 |
| File Format | |
| Alternate Webpage(s) | http://archive.org/details/NASA_NTRS_Archive_19740009460 |
| Archival Resource Key | ark:/13960/t8vb2x676 |
| Language | English |
| Publisher Date | 1974-01-01 |
| Access Restriction | Open |
| Subject Keyword | Space Vehicles Spacecraft Components Epoxy Resins Space Shuttles Reinforcing Fibers Compression Tests Synthetic Fibers Reinforced Plastics Compressive Strength Composite Structures Ntrs Nasa Technical Reports ServerĀ (ntrs) Nasa Technical Reports Server Aerodynamics Aircraft Aerospace Engineering Aerospace Aeronautic Space Science |
| Content Type | Text |
| Resource Type | Technical Report |