| タイトル | Heavy Lift Launch Vehicles for 1995 and Beyond |
| 本文（外部サイト） | http://hdl.handle.net/2060/19860001749 |
| 著者（英） | Toelle, R. |
| 著者所属（英） | NASA Marshall Space Flight Center |
| 発行日 | 1985-09-01 |
| 言語 | eng |
| 内容記述 | A Heavy Lift Launch Vehicle (HLLV) designed to deliver 300,000 lb to a 540 n mi circular polar orbit may be required to meet national needs for 1995 and beyond. The vehicle described herein can accommodate payload envelopes up to 50 ft diameter by 200 ft in length. Design requirements include reusability for the more expensive components such as avionics and propulsion systems, rapid launch turnaround time, minimum hardware inventory, stage and component flexibility and commonality, and low operational costs. All ascent propulsion systems utilize liquid propellants, and overall launch vehicle stack height is minimized while maintaining a reasonable vehicle diameter. The ascent propulsion systems are based on the development of a new liquid oxygen/hydrocarbon booster engine and liquid oxygen/liquid hydrogen upper stage engine derived from today's SSME technology. Wherever possible, propulsion and avionics systems are contained in reusable propulsion/avionics modules that are recovered after each launch. |
| NASA分類 | LAUNCH VEHICLES AND SPACE VEHICLES |
| レポートNO | 86N11216
NAS 1.15:86520
NASA-TM-86520 |
| 権利 | No Copyright |
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