| タイトル | Design study of an integrated aerobraking orbital transfer vehicle |
| 本文（外部サイト） | http://hdl.handle.net/2060/19850012952 |
| 著者（英） | Knoll, K. R.; Li, C. P.; Scott, C. D.; Nagy, K.; Roberts, B. B.; Gamble, J. D.; Ceremeli, C. J.; Reid, R. C.; Taylor, P. |
| 著者所属（英） | NASA Johnson Space Center |
| 発行日 | 1985-03-01 |
| 言語 | eng |
| 内容記述 | An aerobraking orbital transfer vehicle (AOTV) concept, which has an aerobrake structure that is integrated with the propulsion stage, is discussed. The concept vehicle is to be assembled in space and is space-based. The advantages of aeroassist over an all propulsive vehicle are discussed and it is shown that the vehicle considered is very competitive with inflatable and deployable concepts from mass and performance aspects. The aerobrake geometry is an ellipsoidally blunted, raked-off, elliptical wide-angle cone with a toroidal skirt. Propellant tanks, engines, and subsystems are integrated into a closed, isogrid aerobrake structure which provides rigidity. The vehicle has two side-firing, gimbaled RL-10 type engines and carries 38,000 kg of useable propellant. The trajectory during aerobraking is determined from an adaptive guidance logic, and the heating is determined from engineering correlations as well as 3-D Navier-Stokes solutions. The AOTV is capable of placing 13,500 kg payload into geosynchronous Earth orbit (GEO) or carrying a LEO-GEO-LEO round-trip payload of 7100 kg. A two-stage version considered for lunar missions results in a lunar surface delivery capability of 18,000 kg or a round-trip capability of 6800 kg with 3860 kg delivery-only capability. |
| NASA分類 | SPACECRAFT PROPULSION AND POWER |
| レポートNO | 85N21262
NAS 1.15:58264
NASA-TM-58264
S-542 |
| 権利 | No Copyright |
| URI | https://repository.exst.jaxa.jp/dspace/handle/a-is/156952 |
|
