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Model: Helios A-1. Gross Mass: 200,000 kg (440,000 lb). Empty Mass: 10,000 kg (22,000 lb). Thrust (vac): 6,660.000 kN (1,497,220 lbf). Isp: 400 sec. Burn time: 110 sec. Propellants: Lox/LH2. Isp(sl): 340 sec. Diameter: 6.70 m (21.90 ft). Span: 10.10 m (33.10 ft). Length: 8.80 m (28.80 ft). Country: USA. No Engines: 4. Motor: Helios Stage 1. Status: Study 1960. Booster stage with Lox tanks only to take nuclear second stage to stratosphere. Model: Helios B-1. Gross Mass: 236,000 kg (520,000 lb). Empty Mass: 14,000 kg (30,000 lb). Thrust (vac): 7,786.000 kN (1,750,362 lbf). Isp: 400 sec. Burn time: 110 sec. Propellants: Lox/LH2. Isp(sl): 340 sec. Diameter: 6.70 m (21.90 ft). Span: 10.10 m (33.10 ft). Length: 8.80 m (28.80 ft). Country: USA. No Engines: 5. Motor: Helios Stage 1. Status: Study 1960. Booster stage with Lox tanks only to take nuclear second stage to stratosphere. Model: Helios C-1. Gross Mass: 395,000 kg (870,000 lb). Empty Mass: 18,000 kg (39,000 lb). Thrust (vac): 12,450.000 kN (2,798,870 lbf). Isp: 400 sec. Burn time: 117 sec. Propellants: Lox/LH2. Isp(sl): 340 sec. Diameter: 8.50 m (27.80 ft). Span: 12.20 m (40.00 ft). Length: 11.00 m (36.00 ft). Country: USA. No Engines: 8. Motor: Helios Stage 1. Status: Study 1960. Booster stage with Lox tanks only to take nuclear second stage to stratosphere. 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. |