 | ROOST Improved
ROOST Improved Specific Impulse
Credit - © Mark Wade
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Model: OOST. Gross Mass: 7,982,000 kg (17,597,000 lb). Empty Mass: 431,000 kg (950,000 lb). Thrust (vac): 123,191.000 kN (27,694,438 lbf). Isp: 410 sec. Burn time: 242 sec. Propellants: Lox/LH2. Isp(sl): 345 sec. Diameter: 21.30 m (69.80 ft). Span: 21.30 m (69.80 ft). Length: 85.40 m (280.10 ft). Country: USA. No Engines: 4. Motor: 5 mlbf. Status: Study 1963.
Model: 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. Propellants: Lox/LH2. 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). Country: USA. No Engines: 15. Motor: Chamber/single nozzle. Status: Study 1963. Cost $ : 117.600 million.
Model: ROOST. Gross Mass: 10,898,000 kg (24,025,000 lb). Empty Mass: 608,000 kg (1,340,000 lb). Thrust (vac): 165,447.000 kN (37,193,965 lbf). Isp: 410 sec. Burn time: 246 sec. Propellants: Lox/LH2. Isp(sl): 345 sec. Diameter: 21.30 m (69.80 ft). Span: 21.30 m (69.80 ft). Length: 106.70 m (350.00 ft). Country: USA. No Engines: 4. Motor: 5 mlbf. Status: Study 1963.
Model: 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. Propellants: Lox/LH2. 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). Country: USA. No Engines: 18. Motor: Chamber/single nozzle. Status: Study 1963. Cost $ : 154.000 million.
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© Mark Wade, 1997 - 2008 except where otherwise noted.
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