Encyclopedia entry

Helios C

Launch vehicle · USA

Original archive entry. The text, images and links below are kept as they were written.

American nuclear-powered orbital launch vehicle.

LEO Payload: 86,200 kg (190,000 lb) to a 556 km orbit. Payload: 49,000 kg (108,000 lb) to a earth escape.

Stage Data - Helios C

Stage 1. 1 x 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. 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). Propellants: Lox/LH2. No Engines: 8. 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 C-2. Gross Mass: 309,000 kg (681,000 lb). Empty Mass: 54,000 kg (119,000 lb). Thrust (vac): 5,780.000 kN (1,299,390 lbf). Isp: 830 sec. Burn time: 355 sec. Diameter: 8.50 m (27.80 ft). Span: 12.20 m (40.00 ft). Length: 85.40 m (280.10 ft). Propellants: Nuclear/LH2. No Engines: 2. Engine: Nuclear 12 Gw. Status: Study, Ehricke, 1960. Comments: Nuclear second stage.

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