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Structural performance of two aerobrake hexagonal heat shield panel concepts
| Content Provider | NASA Technical Reports Server (NTRS) |
|---|---|
| Author | Dyess, James W. Dorsey, John T. |
| Copyright Year | 1992 |
| Description | Structural sizing and performance are presented for two structural concepts for an aerobrake hexagonal heat shield panel. One concept features a sandwich construction with an aluminum honeycomb core and thin quasi-isotropic graphite-epoxy face sheets. The other concept features a skin-rib isogrid construction with thin quasi-isotropic graphite-epoxy skins and graphite-epoxy ribs oriented at 0, +60, and -60 degs along the panel. Linear static, linear bifurcation buckling, and nonlinear static analyses were performed to compare the structural performance of the two panel concepts and assess their feasibility for a lunar transfer vehicle aerobrake application. |
| File Size | 1727630 |
| Page Count | 32 |
| File Format | |
| Alternate Webpage(s) | http://archive.org/details/NASA_NTRS_Archive_19920015558 |
| Archival Resource Key | ark:/13960/t83j8cr97 |
| Language | English |
| Publisher Date | 1992-05-01 |
| Access Restriction | Open |
| Subject Keyword | Spacecraft Design, Testing And Performance Lunar Surface Vehicles Structural Design Panels Construction Honeycomb Cores Aluminum Sandwich Structures Ribs Supports Heat Shielding Graphite-epoxy Composites Aerobraking Buckling Spacecraft Design Large Space Structures 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 |
