| タイトル | Radiative metallic thermal protection systems - A status report |
| 著者（英） | Rummler, D. R.; Bohon, H. L.; Shideler, J. L. |
| 著者所属（英） | NASA Langley Research Center |
| 発行日 | 1977-01-01 |
| 言語 | eng |
| 内容記述 | During the early stages of the space shuttle program there were a number of technological uncertainties concerning the applicability of metallic thermal protection systems (TPS) to the multimission environment of the shuttle. To resolve the uncertainties and to advance the state-of-the-art, the NASA-Langley Research Center initiated a broad-based technology program to develop metallic TPS over the temperature range from 810 K to 1590 K. Wind tunnel tests conducted to assess the influence of surface/stream interaction of wavy surfaces on the design of metallic TPS indicate small increases in heat flux and surface drag for flow angles less than 20 deg. Analytical and experimental investigations, recently completed, have significantly improved prediction methods for cyclic creep behavior of TPS components repeatedly exposed to complex mission cycles. Thermal/structural concept optimization studies to minimize mass while maintaining structural integrity have led to advanced designs with unit masses which are competitive with those for shuttle RSI. In addition, the durability and reusability of metallic TPS have been repeatedly demonstrated in tests of full-scale systems. The current state-of-the-art strongly suggests that radiative metallic TPS have come of age. |
| NASA分類 | SPACECRAFT DESIGN, TESTING AND PERFORMANCE |
| レポートNO | 77A25743
AIAA PAPER 77-391 |
| 権利 | Copyright |
| URI | https://repository.exst.jaxa.jp/dspace/handle/a-is/438837 |
