ROOST ISI
Launch vehicle · USA
Original archive entry. The text, images and links below are kept as they were written.
ROOST Improved Specific Impulse
Credit: © Mark Wade
American SSTO orbital launch vehicle. Bono's first design for a reusable single stage to orbit LH2/LOx booster, 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$: 154.000 million.
Stage Data - ROOST ISI
- Stage 1. 1 x ROOST ISI. Gross Mass: 6,218,000 kg (13,708,000 lb). Empty Mass: 435,000 kg (959,000 lb). Thrust (vac): 101,842.000 kN (22,894,992 lbf). Isp: 455 sec. Burn time: 249 sec. Isp(sl): 365 sec. Diameter: 21.30 m (69.80 ft). Span: 21.30 m (69.80 ft). Length: 67.10 m (220.10 ft). Propellants: Lox/LH2. No Engines: 18. Engine: Chamber/single nozzle. Status: Study 1963.
Related
- Family
- orbital launch vehicle, SSTO
- Country
- USA
- Engines
- Chamber/single nozzle
- Stages
- ROOST ISI stage
- Agency
- Douglas