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Helios A

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Helios Helios Launch Vehicle Credit: � Mark Wade

Status: Study 1960. Payload: 73,400 kg (161,800 lb). Thrust: 5,670.00 kN (1,274,660 lbf). Gross mass: 441,080 kg (972,410 lb). Height: 81.00 m (265.00 ft). Diameter: 6.70 m (21.90 ft). Apogee: 556 km (345 mi).

LEO Payload: 73,400 kg (161,800 lb) to a 556 km orbit. Payload: 42,000 kg (92,000 lb) to a earth escape.

Stage Data - Helios A

• Stage 1. 1 x 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. 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). Propellants: Lox/LH2. No Engines: 4. Engine: Helios Stage 1. Status: Study, Ehricke, 1960. Comments: Booster stage with Lox tanks only to take nuclear second stage to stratosphere.

• Stage 2. 1 x Helios A-2. Gross Mass: 153,000 kg (337,000 lb). Empty Mass: 26,000 kg (57,000 lb). Thrust (vac): 2,892.000 kN (650,147 lbf). Isp: 830 sec. Burn time: 353 sec. Diameter: 6.70 m (21.90 ft). Span: 10.10 m (33.10 ft). Length: 67.10 m (220.10 ft). Propellants: Nuclear/LH2. No Engines: 1. Engine: Nuclear 12 Gw. Status: Study, Ehricke, 1960. Comments: Nuclear second stage.

Family: nuclear-powered, orbital launch vehicle. Country: USA. Engines: Helios Stage 1, Nuclear 12 Gw. Stages: Helios A-1, Helios A-2. Agency: Convair.