OOST ISI
Launch vehicle · USA
Original archive entry. The text, images and links below are kept as they were written.
American SSTO orbital launch vehicle. Alternate version of OOST using Improved Specific Impulse approach: many engines feeding into single large nozzle.
LEO Payload: 454,500 kg (1,002,000 lb) to a 325 km orbit. Flyaway Unit Cost 1985$: 117.600 million.
Stage Data - OOST ISI
- Stage 1. 1 x OOST ISI. Gross Mass: 5,125,000 kg (11,298,000 lb). Empty Mass: 292,000 kg (643,000 lb). Thrust (vac): 85,386.000 kN (19,195,536 lbf). Isp: 455 sec. Burn time: 248 sec. Isp(sl): 365 sec. Diameter: 21.30 m (69.80 ft). Span: 21.30 m (69.80 ft). Length: 57.90 m (189.90 ft). Propellants: Lox/LH2. No Engines: 15. Engine: Chamber/single nozzle. Status: Study 1963.
Related
- Family
- orbital launch vehicle, SSTO
- Country
- USA
- Engines
- Chamber/single nozzle
- Stages
- OOST ISI stage
- Agency
- Douglas