| タイトル | Analysis of separation of a two-stage winged launch vehicle |
| 著者（英） | Naftel, J. C.; Wilhite, A. W.; Cruz, C. I. |
| 著者所属（英） | NASA Langley Research Center |
| 発行日 | 1986-01-01 |
| 言語 | eng |
| 内容記述 | The feasibility of separating a two-stage winged, parallel configured launch vehicle at Mach 3 has been determined. The two-stage fully-reusable launch vehicle is comprised of an orbiter, which can be used alone as a single-stage-to-orbit vehicle, and a booster which is identical to the baseline orbiter design. A three-degree-of-freedom analysis was conducted on the ascent trajectory of the two-stage concept to determine the optimum staging conditions. The booster provides all propellant for both stages using a crossfeed system until staging occurs. After staging, the empty booster glides back to the launch site for a horizontal landing. To analyze the separation maneuver, the six-degree-of-freedom equations of motion for both stages were numerically integrated using a computer program which incorporates analytically derived interference aerodynamic data. The necessary conditions for a successful separation were determined and required the use of active controls on both the orbiter and booster. Once the booster and orbiter were separated, a three-degree-of-freedom analysis was conducted on the booster's glideback trajectory. |
| NASA分類 | LAUNCH VEHICLES AND SPACE VEHICLES |
| レポートNO | 86A19742
AIAA PAPER 86-0195 |
| 権利 | Copyright |
|
