| タイトル | Finite-element reentry heat-transfer analysis of space shuttle Orbiter |
| 本文（外部サイト） | http://hdl.handle.net/2060/19870020362 |
| 著者（英） | Quinn, Robert D.; Ko, William L.; Gong, Leslie |
| 著者所属（英） | NASA Ames Research Center |
| 発行日 | 1986-12-01 |
| 言語 | eng |
| 内容記述 | 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. |
| NASA分類 | FLUID MECHANICS AND HEAT TRANSFER |
| レポートNO | 87N29795
NASA-TP-2657
H-1236
NAS 1.60:2657 |
| 権利 | No Copyright |
| URI | https://repository.exst.jaxa.jp/dspace/handle/a-is/148820 |
