| タイトル | Thermal response of advanced high temperature ceramic-composite insulation to a convectively heated environment |
| 著者（英） | Smith, M.; Leiser, D. B.; Stewart, D. A. |
| 著者所属（英） | NASA Ames Research Center |
| 発行日 | 1983-08-01 |
| 言語 | eng |
| 内容記述 | The Space Shuttle uses currently fibrous high temperature, reusable surface insulation (HRSI) as a Thermal Protection System (TPS) at 1260 C for normal-design mission operation. Higher density material of a similar type extended the maximum temperature to 1480 C. However, a surface temperature capability exceeding 1540 C is desired for future space vehicles, such as the Orbital Transfer Vehicle (OTV). A TPS providing such a capability would permit future entry vehicles to enter the atmosphere at a much higher velocity than the Space Shuttle. The present investigation is concerned with arc-jet test data obtained from a family of fibrous refractory-composite insulation (FRCI) materials developed to meet the future TPS requirements. FRCI materials containing between 20 and 80 percent aluminoborosilicate fibers with the balance composed of silica fibers were studied. |
| NASA分類 | NONMETALLIC MATERIALS |
| レポートNO | 84A13507 |
| 権利 | Copyright |
| URI | https://repository.exst.jaxa.jp/dspace/handle/a-is/400661 |
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