| タイトル | Shuttle solid rocket motor nozzle alternate ablative evaluation |
| 著者（英） | Bailey, R. L.; Powers, L. B.; Morrison, B. H. |
| 著者所属（英） | NASA Marshall Space Flight Center|Jet Propulsion Lab., California Inst. of Tech. |
| 発行日 | 1981-07-01 |
| 言語 | eng |
| 内容記述 | A series of subscale tests are shown to suggest that a lower-cost ablative material than the rayon-based carbon ablative currently used in the Space Shuttle Solid Rocket Motor (SRM) may be used as a substitute. Six such ablatives with outstanding performance characteristics, using spun PAN and continuous pitch and PAN fibers instead of the present, continuous rayon, were identified in the course of tests with HTPB/AL/AP solid propellant grains with a burn time of 12 sec. The test nozzle features an initial throat diameter of 2.2 in. and a 6.1 expansion ratio. In addition to nozzle structural feature drawings, extensive test data tables and propellant formulation and properties tables are provided. |
| NASA分類 | SPACECRAFT PROPULSION AND POWER |
| レポートNO | 81A42201
AIAA PAPER 81-1461 |
| 権利 | Copyright |
| URI | https://repository.exst.jaxa.jp/dspace/handle/a-is/415775 |
