| タイトル | Near-Optimal Operation of Dual-Fuel Launch Vehicles |
| 本文（外部サイト） | http://hdl.handle.net/2060/19970016839 |
| 著者（英） | Bowles, J. V.; Chou, H. C.; Ardema, M. D. |
| 著者所属（英） | NASA Ames Research Center |
| 発行日 | 1996-01-01
1996 |
| 言語 | eng |
| 内容記述 | A near-optimal guidance law for the ascent trajectory from earth surface to earth orbit of a fully reusable single-stage-to-orbit pure rocket launch vehicle is derived. Of interest are both the optimal operation of the propulsion system and the optimal flight path. A methodology is developed to investigate the optimal throttle switching of dual-fuel engines. The method is based on selecting propulsion system modes and parameters that maximize a certain performance function. This function is derived from consideration of the energy-state model of the aircraft equations of motion. Because the density of liquid hydrogen is relatively low, the sensitivity of perturbations in volume need to be taken into consideration as well as weight sensitivity. The cost functional is a weighted sum of fuel mass and volume; the weighting factor is chosen to minimize vehicle empty weight for a given payload mass and volume in orbit. |
| NASA分類 | Launch Vehicles and Space Vehicles |
| レポートNO | 97N19227
NASA-CR-204358
NAS 1.26:204358
AIAA Paper 96-3397 |
| 権利 | Copyright, Distribution as joint owner in the copyright |
