| タイトル | Hybrid rocket combustion study |
| 著者（英） | Strand, L. D.; Ray, R. L.; Cohen, N. S. |
| 著者所属（英） | Jet Propulsion Lab., California Inst. of Tech. |
| 発行日 | 1993-06-01 |
| 言語 | eng |
| 内容記述 | The objectives of this study of 'pure' or 'classic' hybrids are to (1) extend our understanding of the boundary layer combustion process and the critical engineering parameters that define this process, (2) develop an up-to-date hybrid fuel combustion model, and (3) apply the model to correlate the regression rate and scaling properties of potential fuel candidates. Tests were carried out with a hybrid slab window motor, using several diagnostic techniques, over a range of motor pressure and oxidizer mass flux conditions. The results basically confirmed turbulent boundary layer heat and mass transfer as the rate limiting process for hybrid fuel decomposition and combustion. The measured fuel regression rates showed good agreement with the analytical model predictions. The results of model scaling calculations to Shuttle SRM size conditions are presented. |
| NASA分類 | SPACECRAFT PROPULSION AND POWER |
| レポートNO | 93A50173
AIAA PAPER 93-2412 |
| 権利 | Copyright |
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