| タイトル | Extensions to analysis of ignition transients of segmented rocket motors |
| 本文（外部サイト） | http://hdl.handle.net/2060/19820012367 |
| 著者（英） | Caveny, L. H. |
| 著者所属（英） | Princeton Univ. |
| 発行日 | 1978-01-06 |
| 言語 | eng |
| 内容記述 | The analytical procedures described in NASA CR-150162 were extended for the purpose of analyzing the data from the first static test of the Solid Rocket Booster for the Space Shuttle. The component of thrust associated with the rapid changes in the internal flow field was calculated. This dynamic thrust component was shown to be prominent during flame spreading. An approach was implemented to account for the close coupling between the igniter and head end segment of the booster. The tips of the star points were ignited first, followed by radial and longitudinal flame spreading. |
| NASA分類 | SPACECRAFT PROPULSION AND POWER |
| レポートNO | 82N20241
NASA-CR-150632
NAS 1.26:150632 |
| 権利 | No Copyright |
| URI | https://repository.exst.jaxa.jp/dspace/handle/a-is/166669 |
