|
Model: DAC Helios-1. Gross Mass: 1,660,000 kg (3,650,000 lb). Empty Mass: 149,000 kg (328,000 lb). Thrust (vac): 52,926.000 kN (11,898,238 lbf). Isp: 410 sec. Burn time: 113 sec. Propellants: Lox/LH2. Isp(sl): 345 sec. Diameter: 24.40 m (80.00 ft). Span: 29.00 m (95.00 ft). Length: 16.20 m (53.10 ft). Country: USA. No Engines: 4. Motor: Chamber/single nozzle. Status: Study 1963.
Model: DAC Helios ISI-1. Gross Mass: 1,333,000 kg (2,938,000 lb). Empty Mass: 120,000 kg (260,000 lb). Thrust (vac): 49,807.000 kN (11,197,059 lbf). Isp: 455 sec. Burn time: 107 sec. Propellants: Lox/LH2. Isp(sl): 365 sec. Diameter: 24.40 m (80.00 ft). Span: 29.00 m (95.00 ft). Length: 22.90 m (75.10 ft). Country: USA. No Engines: 4. Motor: Chamber/single nozzle. Status: Study 1963. Cost $ : 38.700 million.
Used on Launch Vehicles:
Contact us with any corrections, additions, or comments.
Conditions for use of drawings, pictures, or other materials from this site..
To contact astronauts or cosmonauts.
© Mark Wade, 1997 - 2008 except where otherwise noted.
|
|