| タイトル | Nuclear thermal rocket propulsion application to Mars missions |
| 著者（英） | Emrich, W. J., Jr.; Mulqueen, J. A.; Young, A. C. |
| 著者所属（英） | NASA Marshall Space Flight Center |
| 発行日 | 1991-01-01 |
| 言語 | eng |
| 内容記述 | Options for vehicle configurations are reviewed in which nuclear thermal rocket (NTR) propulsion is used for a reference mission to Mars. The scenario assumes an opposition-class Mars transfer trajectory, a 435-day mission, and the use of a single nuclear engine with 75,000 lbs of thrust. Engine parameters are examined by calculating mission variables for a range of specific impulses and thrust/weight ratios. The reference mission is found to have optimal values of 925 s for the specific impulse and thrust/weight ratios of 4.0 and 0.06 for the engine and total stage ratios respectively. When the engine thrust/weight ratio is at least 4/1 the most critical engine parameter is engine specific impulse for reducing overall stage weight. In the context of this trans-Mars three-burn maneuver the NTR engine with an expander engine cycle is considered a more effective alternative than chemical/aerobrake and other propulsion options. |
| NASA分類 | SPACECRAFT PROPULSION AND POWER |
| レポートNO | 92A39508 |
| 権利 | Copyright |
| URI | https://repository.exst.jaxa.jp/dspace/handle/a-is/326868 |
