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Finite-element reentry heat-transfer analysis of space shuttle orbiter
| Content Provider | NASA Technical Reports Server (NTRS) |
|---|---|
| Author | Ko, William L. Quinn, Robert D. Gong, Leslie |
| Copyright Year | 1986 |
| Description | A structural performance and resizing (SPAR) finite-element thermal analysis computer program was used in the heat-transfer analysis of the space shuttle orbiter subjected to reentry aerodynamic heating. Three wing cross sections and one midfuselage cross section were selected for the thermal analysis. The predicted thermal protection system temperatures were found to agree well with flight-measured temperatures. The calculated aluminum structural temperatures also agreed reasonably well with the flight data from reentry to touchdown. The effects of internal radiation and of internal convection were found to be significant. The SPAR finite-element solutions agreed reasonably well with those obtained from the conventional finite-difference method. |
| File Size | 2157135 |
| Page Count | 59 |
| File Format | |
| Alternate Webpage(s) | http://archive.org/details/NASA_NTRS_Archive_19870020362 |
| Archival Resource Key | ark:/13960/t3xt0kx7s |
| Language | English |
| Publisher Date | 1986-12-01 |
| Access Restriction | Open |
| Subject Keyword | Fluid Mechanics And Heat Transfer Aluminum Surface Temperature Space Shuttle Orbiters Reentry Shielding Convection Finite Element Method Wings Thermal Protection Aerodynamic Heating Thermal Analysis Space Transportation System Heat Transfer Coefficients Cross Sections Aircraft 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 |
